The Boeing Company

United States of America

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IPC Class
B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for 73
H04B 7/185 - Space-based or airborne stations 56
H04L 29/06 - Communication control; Communication processing characterised by a protocol 54
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding 43
G06Q 10/00 - Administration; Management 41
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1.

POLYMER WITH UPPER CRITICAL SOLUTION TEMPERATURE IN AQUEOUS SOLUTION

      
Application Number US2020031690
Publication Number 2020/231703
Status In Force
Filing Date 2020-05-06
Publication Date 2020-11-19
Owner THE BOEING COMPANY (USA)
Inventor
  • Monteiro, Michael
  • Hossain, Daloar

Abstract

Aspects generally relate to a temperature responsive polymer, more specifically to a polymer exhibiting an upper critical solution temperature (UCST) in an aqueous solution. In one aspect, a monomer compound includes one or more amide or thioamide groups; one or more ureido or thioureido groups; and one or more ethylenically unsaturated groups. In one aspect, a polymer, such as a homopolymer or a copolymer, is produced by polymerization of the monomer compound. The copolymer is produced by polymerization of the monomer compound and a comonomer, such as a hydrophobic comonomer, a hydrophilic comonomer, a pH responsive comonomer, a light responsive comonomer, and combinations thereof. The polymer exhibits a UCST from about 1°C to about 100°C in an aqueous solution at 1 atm.

IPC Classes  ?

  • C08F 120/36 - Esters containing nitrogen containing oxygen in addition to the carboxy oxygen
  • C08F 220/34 - Esters containing nitrogen

2.

A PERMEABLE PAVEMENT SYSTEM INCLUDING A PERMEABLE PAVEMENT COMPOSITION AND A RELATED METHOD

      
Application Number IB2020053620
Publication Number 2020/212910
Status In Force
Filing Date 2020-04-16
Publication Date 2020-10-22
Owner
  • THE BOEING COMPANY (USA)
  • WASHINGTON STATE UNIVERSITY (USA)
Inventor
  • Taege, Deborah Ann
  • Nassiri, Somayeh
  • Englund, Karl Richard
  • Zhang, Kun
  • Lim, Justin Yune-Te

Abstract

A permeable pavement system (100) including a permeable pavement composition and a related method are provided. The permeable pavement system includes a first layer (102) of a permeable pavement composition including a quantity of a first permeable pavement material (104) and a quantity of cured carbon fiber composite material CCFCM (106) incorporated therewith, the first layer defining a first surface (108); and a second layer (110) of a second permeable pavement material (112) deposited over a substantial entirety of and covering the first surface (108) of the first layer of the permeable pavement composition, wherein the first layer (102) interfaces with the second layer (110) to at least strengthen the permeable pavement system.

IPC Classes  ?

  • E01C 7/10 - Coherent pavings made in situ made of road-metal and binders of road-metal and cement or like binders
  • E01C 7/18 - Coherent pavings made in situ made of road-metal and binders of road-metal and bituminous binders
  • E01C 7/26 - Coherent pavings made in situ made of road-metal and binders of road-metal and bituminous binders mixed with other materials, e.g. cement, rubber, leather, fibre
  • E01C 11/22 - Gutters; Kerbs

3.

SYSTEMS AND METHODS FOR MEASURING GALVANIC CORROSION POTENTIAL

      
Application Number US2019014376
Publication Number 2020/149862
Status In Force
Filing Date 2019-01-18
Publication Date 2020-07-23
Owner THE BOEING COMPANY (USA)
Inventor
  • Kinlen, Patrick J.
  • Schuette, Waynie M.

Abstract

A system for measuring corrosion includes a first electrode configured to be connected to a first structure and a second electrode configured to be connected to a second structure. The first and second structures are galvanically-coupled together, and the first and second structures are made of different materials. A chamber is configured to run through one or more cycles while the first electrode, the first structure, the second electrode, and the second structure are positioned inside the chamber. A measurement device is configured to receive data from the first and second electrodes and to measure one or more parameters based at least partially upon the data. A level of corrosion on the first structure, the second structure, or both is configured to be determined based at least partially upon the one or more parameters.

IPC Classes  ?

  • G01N 17/02 - Electrochemical measuring systems for weathering, corrosion or corrosion-protection measurement
  • G01N 33/44 - Resins; Plastics; Rubber; Leather

4.

AIRCRAFT MODIFICATION MARKETPLACE

      
Application Number US2019059258
Publication Number 2020/092837
Status In Force
Filing Date 2019-10-31
Publication Date 2020-05-07
Owner THE BOEING COMPANY (USA)
Inventor
  • Fahey, Patrick C.
  • Gilley, Sheldon D.
  • Bowe, Mark A.

Abstract

Methods and systems for managing aircraft modifications. A link to a customer information database is established in response to receiving a launch input for a modification marketplace entered by a user via a graphical user interface. The customer information database includes identification information and customer information associated with the user. A determination is made as to whether the user is authorized to access the modification marketplace using the identification information. A link to an engineering database containing aircraft product information is established in response to a determination that the user is authorized to access the modification marketplace. A selected level of access to the aircraft product information in the engineering database is provided, via the graphical user interface, based on the customer information associated with the user.

IPC Classes  ?

  • B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for

5.

HIGH-STRENGTH TITANIUM ALLOY FOR ADDITIVE MANUFACTURING

      
Application Number RU2018000577
Publication Number 2020/046160
Status In Force
Filing Date 2018-08-31
Publication Date 2020-03-05
Owner
  • THE BOEING COMPANY (USA)
  • PUBLIC STOCK COMPANY VSMPO-AVISMA CORPORATION (Russia)
Inventor
  • Mitropolskaya, Natalia Georgievna
  • Leder, Michael Ottovich
  • Puzakov, Igor Yurievich
  • Zaitsev, Alexey Sergeevich
  • Tarenkova, Natalia Yuryevna
  • Briggs, Robert David
  • Ghabchi, Arash
  • Catherine, Jane Parrish
  • Matthew, Jon Crill

Abstract

eqeqeqeqeq = [Mo] + [V]/1.5 + [Cr]×1.25 + [Fe]x2.5.

IPC Classes  ?

  • C22C 14/00 - Alloys based on titanium
  • C22F 1/18 - High-melting or refractory metals or alloys based thereon
  • B33Y 10/00 - Processes of additive manufacturing

6.

HIGH STRENGTH FASTENER STOCK OF WROUGHT TITANIUM ALLOY AND METHOD OF MANUFACTURING THE SAME

      
Application Number RU2018000578
Publication Number 2020/046161
Status In Force
Filing Date 2018-08-31
Publication Date 2020-03-05
Owner
  • THE BOEING COMPANY (USA)
  • PUBLIC STOCK COMPANY VSMPO-AVISMA CORPORATION (Russia)
Inventor
  • Mitropolskaya, Natalia Georgievna
  • Leder, Michael Ottovich
  • Puzakov, Igor Yurievich
  • Zaitsev, Alexey Sergeevich
  • Tarenkova, Natalia Yuryevna
  • Briggs, Robert David

Abstract

This invention generally relates to the field of nonferrous metallurgy, namely to titanium alloy materials with specified mechanical properties for manufacturing the aircraft fasteners. A stock for high strength fastener is manufactured from wrought titanium alloy containing, in weight percentages, 5.5 to 6.5 Al, 3.0 to 4.5 V, 1.0 to 2.0 Mo, 0.3 to 1.5 Fe, 0.3 tol.5 Cr, 0.05 to 0.5 Zr, 0.15 to 0.3 O, 0.05 max. N, 0.08 max. C, 0.25 max. Si, balance titanium and inevitable impurities, having the value of aluminum structural equivalent [Al]eq in the range of 7.5 to 9.5, and the value of molybdenum structural equivalent [Mo]eq in the range of 6.0 to 8.5, where the equivalents are defined by the following equations: [Al]eq =[Al]+[O]x l0+ [Zr]/6; [Mo]eq =[Mo]+[V]/1.5+[Cr]xl.25+[Fe]x2.5. A manufacturing method for a stock for high strength fastener includes melting of titanium alloy ingot, production of forged billed from ingot at beta and/or alpha-beta phase field temperatures, hot rolling at a heating temperature of beta and/or alpha-beta phase field to produce a round stock, subsequent annealing of a rolled stock at a temperature of 550°C to 705°C (1022°F to 1300°F) for at least 0.5 hour followed by drawing to produce a wire with diameter up to 10 mm (0.394 inches) and subsequent annealing at a temperature of 550°C to 705°C (1022°F to 1300°F) for at least 0.5 hour. A technical result is production of a titanium alloy stock for high strength fastener having high ultimate tensile strength and double shear strength while maintaining a high level of plastic properties in the annealed condition.12 claims, 5 illustrations.

IPC Classes  ?

  • C22F 1/18 - High-melting or refractory metals or alloys based thereon
  • C22C 14/00 - Alloys based on titanium
  • F16B 33/00 - Features common to bolt and nut

7.

METHOD FOR REGENERATING COPPER-CONTAINING ALUMINUM ALLOY FROM ALUMINUM ALLOY SCRAP

      
Application Number US2019043333
Publication Number 2020/023689
Status In Force
Filing Date 2019-07-25
Publication Date 2020-01-30
Owner THE BOEING COMPANY (USA)
Inventor
  • Sun, Zhi
  • Liu, Chunwei
  • Wei, Xuan
  • Cao, Hongbin
  • Yan, Pengcheng

Abstract

A method for regenerating different types of copper-containing aluminum alloys using aluminum alloy scrap from aeronautical industry.

IPC Classes  ?

8.

STEEL ALLOY AND METHOD FOR HEAT TREATING STEEL ALLOY COMPONENTS

      
Application Number US2019041937
Publication Number 2020/018496
Status In Force
Filing Date 2019-07-16
Publication Date 2020-01-23
Owner THE BOEING COMPANY (USA)
Inventor
  • Sievers, Daniel, E.
  • Bocchini, Peter, J.

Abstract

A steel alloy including, by weight percent: Ni: 18 to 19%; Co: 11.5 to 12.5%; Mo: 4.6 to 5.2%; Ti: 1.3 to 1.6%; Al: 0.05 to 0.15%; Nb: 0.15 to 0.30%; B: 0.003 to 0.020%; Cr: max 0.25%; Mn: max 0.1%; Si: max 0.1%; C: max 0.03%; P: max 0.005%; and S: max 0.002%, the balance being iron plus incidental impurities.

IPC Classes  ?

  • C21D 6/00 - Heat treatment of ferrous alloys
  • C21D 6/02 - Hardening by precipitation
  • C21D 7/13 - Modifying the physical properties of iron or steel by deformation by hot working
  • C21D 8/00 - Modifying the physical properties by deformation combined with, or followed by, heat treatment
  • C22C 38/00 - Ferrous alloys, e.g. steel alloys
  • C22C 38/06 - Ferrous alloys, e.g. steel alloys containing aluminium
  • C22C 38/08 - Ferrous alloys, e.g. steel alloys containing nickel
  • C22C 38/10 - Ferrous alloys, e.g. steel alloys containing cobalt
  • C22C 38/12 - Ferrous alloys, e.g. steel alloys containing tungsten, tantalum, molybdenum, vanadium or niobium
  • C22C 38/14 - Ferrous alloys, e.g. steel alloys containing titanium or zirconium
  • C22C 38/32 - Ferrous alloys, e.g. steel alloys containing chromium with boron
  • C22C 38/44 - Ferrous alloys, e.g. steel alloys containing chromium with nickel with molybdenum or tungsten
  • C22C 38/52 - Ferrous alloys, e.g. steel alloys containing chromium with nickel with cobalt
  • C22C 33/02 - Making ferrous alloys by powder metallurgy

9.

SECURED MULTI-PAYLOAD ANTENNAS OPERATORS OPERATIONS

      
Application Number US2018031129
Publication Number 2019/212564
Status In Force
Filing Date 2018-05-04
Publication Date 2019-11-07
Owner THE BOEING COMPANY (USA)
Inventor
  • Chen, Yi-Feng James
  • Telkamp, Ryan R.
  • Ziegler, Heidi E.

Abstract

A disclosed method for secured multi-payload antennas operators operations comprises generating, by an antenna operations center (AOC), AOC commands using an antenna location pointing request for each of at least one antenna associated with each of at least one customer. The method further comprises transmitting, by a satellite operation center (SOC), the AOC commands and SOC commands to a vehicle via a ground antenna, where the SOC commands are related to at least one antenna associated with a host. Also, the method comprises generating customer antenna gimballing commands by using the AOC commands, and generating host antenna gimballing commands by using the SOC commands. Further, the method comprises gimballing respectively each of the antenna(s) associated with each of the customer(s) by using the customer antenna gimballing commands, and gimballing respectively each of the antenna(s) associated with the host by using the host antenna gimballing commands.

IPC Classes  ?

  • H04L 29/06 - Communication control; Communication processing characterised by a protocol
  • G06F 21/60 - Protecting data
  • H04B 7/185 - Space-based or airborne stations
  • H04W 84/06 - Airborne or Satellite Networks
  • H04N 21/61 - Network physical structure; Signal processing
  • H04W 12/00 - Security arrangements, e.g. access security or fraud detection; Authentication, e.g. verifying user identity or authorisation; Protecting privacy or anonymity

10.

HOSTED PAYLOAD OPERATIONS

      
Application Number US2018031200
Publication Number 2019/212571
Status In Force
Filing Date 2018-05-04
Publication Date 2019-11-07
Owner THE BOEING COMPANY (USA)
Inventor
  • Chen, Yi-Feng James
  • Krikorian, Haig F.
  • Winig, Robert J.
  • Fish, Jonathan
  • Benjamin, Craig

Abstract

A method for hosted payload operations comprises transmitting, by a hosted payload (HoP) operation center (HOC), encrypted hosted commands to a host spacecraft operations center (SOC). Also, the method comprises transmitting, by the host SOC, encrypted host commands and encrypted hosted commands to a vehicle. In addition, the method comprises reconfiguring a host payload according to unencrypted host commands, and reconfiguring a hosted payload according to unencrypted hosted commands. Additionally, the method comprises transmitting, by a host payload antenna, host payload data to a host receiving antenna. In addition, the method comprises transmitting, by a hosted payload antenna, hosted payload data to a hosted receiving antenna and/or host receiving antenna. Also, the method comprises transmitting, by a telemetry transmitter on the vehicle, encrypted host telemetry and encrypted hosted telemetry to the host SOC. Further, the method comprises transmitting, by the host SOC, the encrypted hosted telemetry to the HOC.

IPC Classes  ?

11.

PROTECTED MULTI-OPERATORS PAYLOAD OPERATIONS

      
Application Number US2018031222
Publication Number 2019/212573
Status In Force
Filing Date 2018-05-04
Publication Date 2019-11-07
Owner THE BOEING COMPANY (USA)
Inventor
  • Chen, Yi-Feng James
  • Krikorian, Haig F.
  • Winig, Robert J.

Abstract

Systems, methods, and apparatus for protected multi-operators payload operations are disclosed. In one or more embodiments, a disclosed method for protected multi-operators payload operations comprises transmitting, by a hosted payload (HoP) operation center (HOC), encrypted hosted commands to a host spacecraft operations center (SOC). Also, the method comprises transmitting, by the host SOC, encrypted host commands and the encrypted hosted commands to a vehicle. In addition, the method comprises reconfiguring a payload on the vehicle according to unencrypted host commands and unencrypted hosted commands. Additionally, the method comprises transmitting, by a payload antenna on the vehicle, payload data to a host receiving antenna and a hosted receiving antenna. Also, the method comprises transmitting, by a telemetry transmitter on the vehicle, encrypted host telemetry and encrypted hosted telemetry to the host SOC. Further, the method comprises transmitting, by the host SOC, the encrypted hosted telemetry to the HOC.

IPC Classes  ?

  • H04L 29/06 - Communication control; Communication processing characterised by a protocol
  • G06F 21/60 - Protecting data
  • H04B 7/185 - Space-based or airborne stations
  • H04N 21/61 - Network physical structure; Signal processing
  • H04W 84/06 - Airborne or Satellite Networks
  • H04B 7/06 - Diversity systems; Multi-antenna systems, i.e. transmission or reception using multiple antennas using two or more spaced independent antennas at the transmitting station
  • H04W 12/00 - Security arrangements, e.g. access security or fraud detection; Authentication, e.g. verifying user identity or authorisation; Protecting privacy or anonymity

12.

FIBROUS INTERLOCKING INTERLAYERS

      
Application Number US2019026542
Publication Number 2019/204084
Status In Force
Filing Date 2019-04-09
Publication Date 2019-10-24
Owner THE BOEING COMPANY (USA)
Inventor
  • Evans, Paul
  • Howe, Christopher A.
  • Martin, Kariza
  • Wilson, Thomas

Abstract

A three dimensional permeable thermoplastic tape useful for joining of layers of fiber tows (plies) together so as to form highly toughened resin infused structures. In one or more embodiments, the tape is manufactured using three dimensional printing and is applied between layers of fiber tows so as to tack the layers of fiber tows in place and prevent movement of the layers of fiber tows.

IPC Classes  ?

  • B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
  • B33Y 80/00 - Products made by additive manufacturing
  • B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
  • B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
  • B29C 70/02 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements and fillers incorporated in matrix material, forming one or more layers, with or without non-reinforced or non-filled layers
  • B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
  • B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
  • A61F 13/62 - Fabric strip fastener elements, e.g. hook and loop
  • B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
  • A44B 18/00 - Fasteners of the touch-and-close type; Making such fasteners
  • B29L 31/00 - Other particular articles

13.

POLYMER COATING COMPOSITIONS

      
Application Number AU2019050265
Publication Number 2019/183669
Status In Force
Filing Date 2019-03-26
Publication Date 2019-10-03
Owner
  • COMMONWEALTH SCIENTIFIC AND INDUSTRIAL RESEARCH ORGANISATION (Australia)
  • THE BOEING COMPANY (USA)
Inventor
  • Yang, Weidong
  • Simons, Ranya
  • Li, Sheng
  • Zhang, Xiaoqing
  • Seebergh, Jill E.
  • Berry, Douglas H.

Abstract

The present disclosure generally relates to adhesion promoting intercoating layers, selectively strippable coatings, coating compositions, and methods of making and using the compositions and coatings. A coating composition can be provided comprising an organic polymer containing acid functionalities, a metallic agent, and a boron agent, which may be used on a coated substrate as a selectively strippable and/or adhesion promoting intercoating layer. The coating compositions can be applied to coated substrates within a broad application window and used within multi layered coating systems.

IPC Classes  ?

  • C09D 5/20 - Coating compositions, e.g. paints, varnishes or lacquers, characterised by their physical nature or the effects produced; Filling pastes for coatings strippable as coherent films, e.g. temporary coatings strippable as coherent films
  • B05D 3/10 - Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by other chemical means
  • C08K 3/10 - Metal compounds
  • C08K 3/38 - Boron-containing compounds
  • C09D 133/02 - Homopolymers or copolymers of acids; Metal or ammonium salts thereof

14.

CORROSION RESISTANT SOL-GEL

      
Application Number US2019016338
Publication Number 2019/152834
Status In Force
Filing Date 2019-02-01
Publication Date 2019-08-08
Owner THE BOEING COMPANY (USA)
Inventor
  • Schuette, Waynie M.
  • Kinlen, Patrick J.

Abstract

Aspects described herein generally relate to a sol-gel that is the reaction product of an organosilane, a metal alkoxide, an acid, and chromium (III) salt and/or a lanthanide salt having a solubility of about 1 gram or greater per gram of sol-gel at 23oC. The lanthanide salt includes a cation and a ligand. The cation can be lanthanum, cerium, praseodymium, neodymium, promethium, samarium, europium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, lutetium, scandium, yttrium, cobalt, calcium, strontium, barium, and zirconium. A ligand can be a nitrate, a trifluoromethane sulfonate, a sulfate, a phosphate, a hydroxide, or hydrate forms thereof. The chromium (III) salt includes a cation and a ligand. The cation is chromium (III) and the ligand can be a nitrate, a trifluoromethane sulfonate, a sulfate, a phosphate, a hydroxide, or hydrate forms thereof.

IPC Classes  ?

  • C09D 5/08 - Anti-corrosive paints
  • C09D 183/06 - Polysiloxanes containing silicon bound to oxygen-containing groups
  • C09D 7/63 - Additives non-macromolecular organic
  • C08K 5/00 - Use of organic ingredients

15.

CORROSION RESISTANT SOL GEL COMPRISING A SOLUBLE THIO-LANTHANIDE SALT

      
Application Number US2019016396
Publication Number 2019/152871
Status In Force
Filing Date 2019-02-01
Publication Date 2019-08-08
Owner
  • THE BOEING COMPANY (USA)
  • COMMONWEALTH SCIENTIFIC AND INDUSTRIAL RESEARCH ORGANISATION (Australia)
Inventor
  • Schuette, Waynie M.
  • Kinlen, Patrick J.
  • White, Paul Andrew

Abstract

Aspects described herein generally relate to a sol-gel that is the reaction product of an organosilane, a metal alkoxide, an acid, and a thio-lanthanide salt having a solubility of about 1 gram or greater per gram of sol-gel at 23°C. The thio-lanthanide salt includes a cation and a thio-ligand. The cation can be lanthanum, cerium, praseodymium, neodymium, promethium, samarium, europium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, lutetium, scandium, yttrium, cobalt, calcium, strontium, barium, and zirconium. In another aspect, a component, such as a vehicle component, includes a metal substrate and a sol-gel disposed on the metal substrate. Methods can include forming a sol-gel by mixing a metal alkoxide and an acid to form a first mixture; mixing with the first mixture an organosilane to form a second mixture; and mixing with the second mixture a lanthanide salt to form a third mixture.

IPC Classes  ?

  • C09D 5/08 - Anti-corrosive paints
  • C09D 7/60 - Additives non-macromolecular
  • C09D 183/06 - Polysiloxanes containing silicon bound to oxygen-containing groups
  • C08K 5/00 - Use of organic ingredients

16.

METHODS, SYSTEMS AND APPARATUSES FOR DETERMINING COMPOSITE MATERIAL CHARACTERISTICS

      
Application Number US2019012125
Publication Number 2019/147397
Status In Force
Filing Date 2019-01-03
Publication Date 2019-08-01
Owner
  • THE BOEING COMPANY (USA)
  • WASHINGTON UNIVERSITY (USA)
Inventor
  • Thimsen, Elijah James
  • Oldham, Iii, Harold Eugene
  • Ferriell, Daniel Richard
  • Rubin, Alexander

Abstract

Methods, systems and apparatuses for determining the surface potential distribution of treated composite material surfaces, and for non-destructively predicting the fracture toughness of a composite material are disclosed herein.

IPC Classes  ?

17.

METHODS, SYSTEMS AND APPARATUSES FOR DETERMINING COMPOSITE MATERIAL CHARACTERISTICS

      
Application Number US2019012137
Publication Number 2019/147399
Status In Force
Filing Date 2019-01-03
Publication Date 2019-08-01
Owner
  • THE BOEING COMPANY (USA)
  • WASHINGTON UNIVERSITY (USA)
Inventor
  • Thimsen, Elijah James
  • Oldham, Iii, Harold Eugene
  • Ferriell, Daniel Richard
  • Rubin, Alexander

Abstract

Methods, systems and apparatuses for determining the surface potential distribution of treated composite material surfaces, and for non-destructively predicting the fracture toughness of a composite material are disclosed herein.

IPC Classes  ?

18.

COLD SPRAY METALLIC COATING AND METHODS

      
Application Number US2019015558
Publication Number 2019/148162
Status In Force
Filing Date 2019-01-29
Publication Date 2019-08-01
Owner THE BOEING COMPANY (USA)
Inventor
  • Bruton, Eric, A.
  • Gaydos, Stephen, P.

Abstract

The present disclosure relates to a cold spray metal process for imparting electromagnetic interference (EMI) resistance or lightning protection to the surface of a polymer, and a polymer with surface EMI resistance, or lightning protection, articles coated therefrom, and methods of reducing or eliminating electrochemical interactions between the metallic coating and components of the polymer.

IPC Classes  ?

  • C23C 24/04 - Impact or kinetic deposition of particles
  • C23C 24/08 - Coating starting from inorganic powder by application of heat or pressure and heat

19.

SPHERICAL METALLIC POWDER BLENDS AND METHODS FOR MANUFACTURING THE SAME

      
Application Number US2018067785
Publication Number 2019/143454
Status In Force
Filing Date 2018-12-28
Publication Date 2019-07-25
Owner THE BOEING COMPANY (USA)
Inventor
  • Parrish, Catherine, J.
  • Cotton, James, D.

Abstract

A method for manufacturing a spherical metallic powder blend using a metallic starting material, the method including steps of grinding the metallic starting material to yield an intermediate powder, spheroidizing the intermediate powder to yield a first spherical powder component, and mixing the first spherical powder component with a second spherical powder component, wherein the first spherical powder component and the second spherical powder component have substantially the same chemical composition.

IPC Classes  ?

  • B22F 1/00 - Special treatment of metallic powder, e.g. to facilitate working, to improve properties; Metallic powders per se, e.g. mixtures of particles of different composition
  • B22F 9/04 - Making metallic powder or suspensions thereof; Apparatus or devices specially adapted therefor using physical processes starting from solid material, e.g. by crushing, grinding or milling
  • B22F 9/14 - Making metallic powder or suspensions thereof; Apparatus or devices specially adapted therefor using physical processes using electric discharge
  • C22C 1/04 - Making non-ferrous alloys by powder metallurgy
  • B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
  • B22F 9/00 - Making metallic powder or suspensions thereof; Apparatus or devices specially adapted therefor

20.

DUAL RACK AND PINION ROTATIONAL INERTER SYSTEM AND METHOD FOR DAMPING MOVEMENT OF A FLIGHT CONTROL SURFACE OF AN AIRCRAFT

      
Application Number US2018055361
Publication Number 2019/139654
Status In Force
Filing Date 2018-10-11
Publication Date 2019-07-18
Owner THE BOEING COMPANY (USA)
Inventor
  • Fox, Michael Thomas
  • Roach, Jeffrey Michael
  • Howell, Eric Anton

Abstract

There is provided a dual rack and pinion rotational inerter system (500) for damping movement (694) of a flight control surface (122) of an aircraft (100). The system (500) has a flexible holding structure (506) disposed between the flight control surface (122) and a support structure (116) of the aircraft (100). The system (500) has a dual rack and pinion assembly (550) held by and between the flexible holding structure (506). The dual rack and pinion assembly (550) has a first rack (552a), a second rack (552b), and a pinion (596) engaged to and between the racks (552a, 552b). The system (500) has a first terminal (502) coupled to the first rack (552a) and coupled to the flight control surface (122), via a pivot element (127), and a second terminal (503) coupled to the second rack (552b), and coupled to the support structure (116). The system (500) has a pair of inertia wheels (660) adjacent the flexible holding structure (506). The system (500) has an axle element (612) inserted through the inertial wheels (660), the flexible holding structure (506), and the pinion (596).

IPC Classes  ?

  • B64C 9/02 - Mounting or supporting thereof
  • B64C 13/34 - Transmitting means without power amplification or where power amplification is irrelevant mechanical using toothed gearing
  • F16F 7/10 - Vibration-dampers; Shock-absorbers using inertia effect
  • B64C 13/40 - Transmitting means with power amplification using fluid pressure

21.

TRANSLATIONAL INERTER ASSEMBLY AND METHOD FOR DAMPING MOVEMENT OF A FLIGHT CONTROL SURFACE

      
Application Number US2018055344
Publication Number 2019/139653
Status In Force
Filing Date 2018-10-11
Publication Date 2019-07-18
Owner THE BOEING COMPANY (USA)
Inventor
  • Fox, Michael Thomas
  • Roach, Jeffrey Michael
  • Howell, Eric Anton

Abstract

There is provided a translational inerter assembly (500) for damping movement (606) of a flight control surface (122) of an aircraft (100). The assembly (500) has a press fit element (510) fixedly disposed within a first end (502a) of the flight control surface (122) and rotatably movable with the flight control surface (122). The assembly (500) further has an inertia element (512) coupled to and installed in the press fit element (510). The assembly (500) further has a torsion bar (514) having a torsion bar first end (564a) coupled to and installed in the inertia element (512), and having a torsion bar second end (564b) fixedly attached to a support structure (116) of the aircraft (100). Rotation of the flight control surface (122) causes translational movement (604) of the inertia element (512), via the press fit element (510), along a hinge axis (126) of the flight control surface (122) and along the torsion bar (514), resulting in the translational inerter assembly (500) damping movement (606) of the flight control surface (122).

IPC Classes  ?

  • B64C 9/02 - Mounting or supporting thereof
  • F16F 7/10 - Vibration-dampers; Shock-absorbers using inertia effect
  • F16F 15/14 - Suppression of vibrations in rotating systems by making use of members moving with the system using freely-swinging masses rotating with the system
  • F16F 7/116 - Vibration-dampers; Shock-absorbers using inertia effect the inertia member being resiliently mounted on metal springs
  • F16F 15/12 - Suppression of vibrations in rotating systems by making use of members moving with the system using elastic members or friction-damping members, e.g. between a rotating shaft and a gyratory mass mounted thereon
  • F16F 15/121 - Suppression of vibrations in rotating systems by making use of members moving with the system using elastic members or friction-damping members, e.g. between a rotating shaft and a gyratory mass mounted thereon using springs as elastic members, e.g. metallic springs
  • B64C 13/38 - Transmitting means with power amplification
  • B64C 13/40 - Transmitting means with power amplification using fluid pressure

22.

CONTINUOUS FLOW PROCESS FOR PREPARING CONDUCTING POLYMERS

      
Application Number AU2018051324
Publication Number 2019/113640
Status In Force
Filing Date 2018-12-12
Publication Date 2019-06-20
Owner
  • COMMONWEALTH SCIENTIFIC AND INDUSTRIAL RESEARCH ORGANISATION (Australia)
  • THE BOEING COMPANY (USA)
Inventor
  • Kohl, Thomas
  • Tsanaktsidis, John
  • Hornung, Christian
  • Kinlen, Patrick
  • Bruton, Eric
  • Flack, Matthew
  • Zweig, Andrew

Abstract

The present disclosure relates to a continuous flow process for preparing conducting polymers, for example polyaniline. The continuous flow process can 5 provide a controlled synthesis of a conducting polymer from an emulsion comprising a polymerizable organic monomer and a free radical initiator in flow within a temperature controlled continuous flow reactor comprising at least one mixing element. The present disclosure also relates to the conducting polymers prepared by the continuous flow process.

IPC Classes  ?

  • C08G 61/12 - Macromolecular compounds containing atoms other than carbon in the main chain of the macromolecule
  • H01B 1/24 - Conductive material dispersed in non-conductive organic material the conductive material comprising carbon-silicon compounds, carbon, or silicon
  • C08G 73/02 - Polyamines
  • C08F 12/28 - Amines
  • C08F 12/30 - Sulfur
  • B01J 19/18 - Stationary reactors having moving elements inside
  • C08K 5/42 - Sulfonic acids; Derivatives thereof
  • C08K 5/04 - Oxygen-containing compounds

23.

AN AUTOMATED AERO ALUMINIUM SCRAP SORTING SYSTEM BASED ON LASER INDUCED BREAKDOWN (LIBS) TECHNIQUE

      
Application Number US2018060932
Publication Number 2019/099453
Status In Force
Filing Date 2018-11-14
Publication Date 2019-05-23
Owner THE BOEING COMPANY (USA)
Inventor
  • Shen, Xuejing
  • Lin, Ying
  • Liu, Jia
  • Shen, Rui
  • Xu, Peng
  • Hu, Yanbin
  • Wu, Han
  • Wang, Hui
  • Zeng, Jiaqing
  • Yang, Libin
  • Zhao, Ge
  • Yao, Jun
  • Shi, Xiaoxia

Abstract

A fully automatic online aero aluminum sorting and recovery system based on LIBS (Laser Induced Breakdown Spectroscopy) technology, which belongs to the field of aero aluminum sorting and recovery technology, and is suitable for online sorting, detection and recovery of large batch of aero aluminum. The fully automatic online aero aluminum sorting system based on LIBS technology provided in the present invention consists of six portions: a sample feeding unit (1), a surface treatment unit (2), a material positioning unit (3), a LIBS analysis and detection unit (4), a transfer unit (5) and a sorting and recovery unit (6). The system according to the invention can be used to realize the automatic online detection, sorting and recovery of aero aluminum, and the system does not have requirements on the surface condition of the recovered aero aluminum samples. The sorting accuracy rate is greater than 90% and the sorting rate is not less than 1 block per second.

IPC Classes  ?

  • G01N 21/71 - Systems in which the material investigated is excited whereby it emits light or causes a change in wavelength of the incident light thermally excited
  • B07C 5/342 - Sorting according to other particular properties according to optical properties, e.g. colour
  • B07C 5/38 - Collecting or arranging articles in groups
  • G01N 33/20 - Metals
  • G01B 11/00 - Measuring arrangements characterised by the use of optical means
  • G01N 35/00 - Automatic analysis not limited to methods or materials provided for in any single one of groups ; Handling materials therefor
  • G01N 35/04 - Automatic analysis not limited to methods or materials provided for in any single one of groups ; Handling materials therefor using a plurality of sample containers moved by a conveyor system past one or more treatment or analysis stations - Details of the conveyor system
  • B65G 27/00 - Jigging conveyors
  • G01N 21/84 - Systems specially adapted for particular applications
  • G01N 21/85 - Investigating moving fluids or granular solids

24.

FUEL BURN ADJUSTMENT BASED ON MEASURED LOWER HEATING VALUE

      
Application Number IB2018057936
Publication Number 2019/077457
Status In Force
Filing Date 2018-10-12
Publication Date 2019-04-25
Owner THE BOEING COMPANY (USA)
Inventor
  • Fregnani, Jose A.
  • Kinder, James D.
  • Andrade, Onofre

Abstract

An aircraft (100) is provided that includes a fuel storage tank (108) for aviation fuel, and avionics systems interconnected by an avionics bus. The fuel storage tank (108) receives aviation fuel during a fuel uplift for a flight according to a flight plan that includes and depends on a predicted fuel burn determined based on a reference lower heating value (LHV) of the aviation fuel. The avionics systems include temperature and density sensors, and a flight management system (FMS). The temperature and density sensors measure respectively the temperature and density of the aviation fuel. The FMS receives the measurements, estimates an actual LHV that is different from the reference LHV based on the measurements, and determines an adjusted predicted fuel burn for the flight based on the predicted fuel burn and the actual LHV. The FMS displays the adjusted predicted fuel burn and enable adjustment of the flight plan based thereon.

IPC Classes  ?

  • B64D 37/02 - Tanks
  • B64D 37/00 - Arrangements in connection with fuel supply for power plant
  • B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
  • G05D 1/00 - Control of position, course, altitude, or attitude of land, water, air, or space vehicles, e.g. automatic pilot
  • G08G 5/00 - Traffic control systems for aircraft
  • G01C 21/00 - Navigation; Navigational instruments not provided for in groups
  • G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed, acceleration

25.

VISUALIZATION SYSTEM FOR DEEP BRAIN STIMULATION

      
Application Number US2018046606
Publication Number 2019/040315
Status In Force
Filing Date 2018-08-14
Publication Date 2019-02-28
Owner THE BOEING COMPANY (USA)
Inventor
  • Laughlin, Brian
  • Laughlin, Dane
  • Laughlin, Madison

Abstract

A system, method, and apparatus for a visualization system for deep brain stimulation. The visualization system comprises a camera system, a display system, and an information analyzer. The information analyzer is configured to display a group of electrodes for the deep brain stimulation on a head of a patient on the display system such that a visualization of the group of electrodes is displayed overlaid on the head of the patient in real time in a position corresponding to an actual position of the group of electrodes in a brain in the head of the patient. An operation of the group of electrodes sending an electrical signal into the head of the patient is displayed in the visualization, enabling visualizing a physical reaction of the patient to the deep brain stimulation in conjunction with the visualization of the operation of the group of electrodes.

IPC Classes  ?

  • A61N 1/18 - Applying electric currents by contact electrodes
  • A61N 1/36 - Applying electric currents by contact electrodes alternating or intermittent currents for stimulation, e.g. heart pace-makers
  • A61N 1/05 - Electrodes for implantation or insertion into the body, e.g. heart electrode
  • A61B 34/00 - Computer-aided surgery; Manipulators or robots specially adapted for use in surgery

26.

ANTIMICROBIAL COMPOUNDS AND NANOSTRUCTURES

      
Application Number US2018037360
Publication Number 2018/232005
Status In Force
Filing Date 2018-06-13
Publication Date 2018-12-20
Owner THE BOEING COMPANY (USA)
Inventor
  • Monteiro, Michael
  • Armstrong, Jason W.

Abstract

The present disclosure provides compounds and nanostructures having one or more quaternary ammonium salts, compositions including the compounds and nanostructures, and methods useful for treating conditions using the compounds, nanostructures, and compositions. In at least one aspect, a compound is represented by formula (I): or a pharmaceutically acceptable salt thereof, wherein: Q is fluoro, chloro, bromo, or iodo; each of s, b, and n is independently an integer from about 10 to about 100; and each of v, j, p, z, q, x and m is independently an integer from 1 to about 20.

IPC Classes  ?

  • A61K 31/787 - Polymers containing nitrogen containing heterocyclic rings having nitrogen as a ring hetero atom
  • A61K 31/795 - Polymers containing sulfur
  • C08F 120/34 - Esters containing nitrogen
  • C08F 120/56 - Acrylamide; Methacrylamide

27.

TITANIUM ALLOY-BASED SHEET MATERIAL FOR LOW-TEMPERATURE SUPERPLASTIC DEFORMATION

      
Application Number RU2017000266
Publication Number 2018/199791
Status In Force
Filing Date 2017-04-25
Publication Date 2018-11-01
Owner
  • PUBLIC STOCK COMPANY "VSMPO-AVISMA CORPORATION" (Russia)
  • THE BOEING COMPANY (USA)
Inventor
  • Leder, Mikhail Ottovich
  • Puzakov, Igor Yurievich
  • Tarenkova, Natalia Yuryevna
  • Berestov, Alexander Vladimirovich
  • Mitropolskaya, Natalia Georgievna
  • Briggs, Robert David

Abstract

The technical result achieved by performing this invention is the production of sheets from a titanium alloy, the chemical composition of which is optimally balanced with the production capabilities of the known current technologies of the final product with the low-temperature superplastic deformation properties. The result is achieved by a sheet material for low-temperature superplastic deformation, which is based on a titanium alloy comprising, wt %: 4.5-5.5 Al; 4.5-5.5 V; 0.1-1.0 Mo; 0.8-1.5 Fe; 0.1-0.5 Cr, 0.1-0.5 Ni; 0.16-0.250 the remainder being titanium and impurities, wherein the value of the structural molybdenum equivalent, [Mo]eq. is higher than 5, and the aluminium structural equivalent, [Al]eq. is lower than 8; the equivalents are determined using the following formulae: [Mo]eq.=[Mo] + [V]/1.5 + [Cr]1.25 + [Fe]2.5 +[Ni]/0.8 [Al]eq.=[Al] + [O]10 + [Zr]/6.

IPC Classes  ?

  • C22C 14/00 - Alloys based on titanium
  • C22F 1/18 - High-melting or refractory metals or alloys based thereon

28.

METHOD FOR RECOVERING CARBON FIBERS FROM COMPOSITE MATERIAL WASTE

      
Application Number US2018025389
Publication Number 2018/183838
Status In Force
Filing Date 2018-03-30
Publication Date 2018-10-04
Owner
  • THE BOEING COMPANY (USA)
  • BEIJING UNIVERSITY OF CHEMICAL TECHNOLOGY (China)
Inventor
  • Gang, Sui
  • Xiaoping, Yang
  • Xin, Jin
  • Zhu, Ming
  • Zhandong, Wang

Abstract

A method for recovering carbon fibers from composite material waste includes coating a solid acid powder onto a surface of a composite material waste having carbon fibers and a resin matrix, pyrolyzing the resin matrix of the coated composite material waste in an inert environment, and oxidizing the pyrolyzed resin of the composite material waste in an air environment.

IPC Classes  ?

  • C10B 53/07 - Destructive distillation, specially adapted for particular solid raw materials or solid raw materials in special form of synthetic polymeric materials, e.g. tyres

29.

METHOD FOR RECOVERING CARBON FIBERS FROM COMPOSITE WASTE

      
Application Number US2018025404
Publication Number 2018/183847
Status In Force
Filing Date 2018-03-30
Publication Date 2018-10-04
Owner
  • THE BOEING COMPANY (USA)
  • BEIJING UNIVERSITY OF CHEMICAL TECHNOLOGY (China)
Inventor
  • Sui, Gang
  • Yang, Xiaoping
  • Jin, Xin
  • Ming, Zhu
  • Wu, Tianyu

Abstract

A method for recovering carbon fibers from composite waste includes coating a water-soluble catalyst powder on a surface of composite waste having carbon fibers and a resin matrix and pyrolyzing the resin matrix of the coated composite waste.

IPC Classes  ?

  • C10B 53/07 - Destructive distillation, specially adapted for particular solid raw materials or solid raw materials in special form of synthetic polymeric materials, e.g. tyres

30.

SYSTEMS AND METHODS OF CURING A THERMOSET COMPOSITE TO A TARGET STATE OF CURE

      
Application Number US2018022731
Publication Number 2018/170314
Status In Force
Filing Date 2018-03-15
Publication Date 2018-09-20
Owner
  • THE BOEING COMPANY (USA)
  • TORAY INDUSTRIES, INC. (Japan)
Inventor
  • Dalal, Hardik
  • Nelson, Karl M.
  • Sherwood, Travis James
  • Nguyen, Felix N.

Abstract

Systems and methods of curing a thermoset composite (TSC) to a target state of cure (SOC) are disclosed herein. The methods include heating the thermoset composite to greater than a threshold temperature. During the heating, the methods further include monitoring an actual temperature of the thermoset composite, determining a maximum temperature achieved by the thermoset composite, and determining an elapsed time that the actual temperature of the thermoset composite is greater than the threshold temperature. The methods further include ceasing the heating based, at least in part, on the maximum temperature of the TSC and the elapsed time. The systems include a heating assembly, a support mandrel, a thermoset composite, a temperature detector, and a controller programmed to perform the methods.

IPC Classes  ?

  • B29C 35/02 - Heating or curing, e.g. crosslinking or vulcanising

31.

METHODS OF CO-BONDING A FIRST THERMOSET COMPOSITE AND A SECOND THERMOSET COMPOSITE TO DEFINE A CURED COMPOSITE PART

      
Application Number US2018022748
Publication Number 2018/170330
Status In Force
Filing Date 2018-03-15
Publication Date 2018-09-20
Owner
  • THE BOEING COMPANY (USA)
  • TORAY INDUSTRIES, INC. (Japan)
Inventor
  • Nelson, Karl, M.
  • Sherwood, Travis, James
  • Dalal, Hardik
  • Nguyen, Felix, N.
  • Lee, Dongyeon
  • Yoshioka, Kenichi
  • Koyanagi, Hideo, Andrew

Abstract

Methods of co-bonding a first thermoset composite (TSC) and a second TSC to define a cured composite part are disclosed herein. The methods include partially curing the first TSC to a target state of cure (SOC) to define a first partially cured TSC. The partially curing is based, at least in part, on a maximum temperature of the first TSC during the partially curing and on an elapsed time that an actual temperature of the first TSC is greater than a threshold temperature. The methods further include combining the first partially cured TSC with the second TSC to define a partially cured TSC assembly and heating the partially cured TSC assembly to bond the first partially cured TSC to the second TSC, cure the partially cured TSC assembly, and produce a cured composite part.

IPC Classes  ?

  • B29C 65/02 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure
  • B29C 65/48 - Joining of preformed parts; Apparatus therefor using adhesives
  • B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof

32.

SURFACE REACTIVATION TREATMENT

      
Application Number IB2018051204
Publication Number 2018/158673
Status In Force
Filing Date 2018-02-27
Publication Date 2018-09-07
Owner THE BOEING COMPANY (USA)
Inventor
  • Simons, Ranya
  • Li, Sheng
  • Bateman, Stuart Arthur
  • Simmonds, Emma
  • Seebergh, Jill Elisabeth
  • Bolles, Jason A.
  • Berry, Douglas Henry

Abstract

The present disclosure relates to a method of reactivating the surface of an organic paint coating, a method of facilitating adhesion of a further coating to the organic paint coating, and a substrate having a reactivated organic paint coating. There is also disclosed a surface reactivation treatment for an organic paint coating. The reactivation method also facilitates adhesion of the organic paint coating to further coating(s) across a broad application window.

IPC Classes  ?

  • C09D 1/00 - Coating compositions, e.g. paints, varnishes or lacquers, based on inorganic substances
  • C09D 7/40 - Additives
  • B05D 3/10 - Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by other chemical means

33.

CALCIUM-BEARING MAGNESIUM AND RARE EARTH ELEMENT ALLOY AND METHOD FOR MANUFACTURING THE SAME

      
Application Number US2017050913
Publication Number 2018/132134
Status In Force
Filing Date 2017-09-11
Publication Date 2018-07-19
Owner
  • THE BOEING COMPANY (USA)
  • UNIVERSITY OF SCIENCE AND TECHNOLOGY BEIJING (China)
Inventor
  • Kang, Qiang
  • Zhang, Yun
  • Liu, Peng
  • Dong, Peng
  • Xu, Zhe
  • Liu, Chaomin
  • Jiang, Haitao

Abstract

A calcium-bearing magnesium and rare earth element alloy consists essentially of, in mass percent, zinc (Zn): 1 - 3%; aluminum (Al): 1 - 3%; calcium (Ca): 0.1 - 0.4%; gadolinium (Gd): 0.1 - 0.4%; yttrium (Y): 0 - 0.4%; manganese (Mn): 0 - 0.2%; and balance magnesium (Mg).

IPC Classes  ?

  • B21J 1/02 - Preliminary treatment of metal stock without particular shaping, e.g. salvaging segregated zones, forging or pressing in the rough
  • C22F 3/00 - Changing the physical structure of non-ferrous metals or alloys by special physical methods, e.g. treatment with neutrons
  • C22C 23/02 - Alloys based on magnesium with aluminium as the next major constituent

34.

SYSTEM AND METHOD FOR RECLAIMING CARBON FIBERS USING SOLAR ENERGY

      
Application Number US2017065332
Publication Number 2018/125540
Status In Force
Filing Date 2017-12-08
Publication Date 2018-07-05
Owner
  • THE BOEING COMPANY (USA)
  • QINGHAI UNIVERSITY (China)
Inventor
  • Shengwei, Mei
  • Qiang, Lu
  • Xiaodai, Xue
  • Xiaotao, Chen
  • Laijun, Chen
  • Yang, Si

Abstract

A system for reclaiming carbon fiber from carbon fiber containing material using solar energy includes a sunlight focusing system, a sample platform for placement of carbon fiber containing material to be treated by focused sunlight from the sunlight focusing system, the sample platform being provided with a gas absorption pipe, and a waste gas treatment system connected with the gas absorption pipe.

IPC Classes  ?

  • B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
  • B32B 5/24 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer
  • D04H 13/00 - Other non-woven fabrics

35.

SURFACE SENSING SYSTEMS AND METHODS FOR IMAGING A SCANNED SURFACE OF A SAMPLE VIA SUM-FREQUENCY VIBRATIONAL SPECTROSCOPY

      
Application Number US2017067028
Publication Number 2018/118779
Status In Force
Filing Date 2017-12-18
Publication Date 2018-06-28
Owner
  • THE BOEING COMPANY (USA)
  • FEMTOMETRIX, INC. (USA)
Inventor
  • Hunt, Jeffrey, H.
  • Shi, Jianing
  • Changala, John, Paul

Abstract

Surface sensing systems and methods for imaging a scanned surface (32) of a sample (30) via sum-frequency vibrational spectroscopy are disclosed herein. The systems include a sample holder (20), a visible light source (40) configured to direct a visible light beam (42) incident upon a sampled location (34) of the scanned surface (32) and a tunable IR source (50) configured to direct a tunable IR beam (52) coincident with the visible light beam (42) upon the sampled location (34). The systems also include a scanning structure (60) configured to scan the visible light beam (42) and the tunable IR beam (52) across the scanned surface (32), and a light filter (70) configured to receive an emitted beam (38) from the scanned surface (32) and to filter the emitted beam (38) to generate a filtered light beam (72). The systems further include a light detection system (80) configured to receive the filtered light beam (72), and an alignment structure (90). The methods include methods of operating the systems.

IPC Classes  ?

  • G01N 21/65 - Raman scattering
  • G01J 3/10 - Arrangements of light sources specially adapted for spectrometry or colorimetry
  • G01N 21/63 - Systems in which the material investigated is excited whereby it emits light or causes a change in wavelength of the incident light optically excited

36.

MG-GD-Y-ZN-ZR ALLOY WITH HIGH STRENGTH AND TOUGHNESS, CORROSION RESISTANCE AND ANTI-FLAMMABILITY AND PROCESS FOR PREPARING THE SAME

      
Application Number CN2017114605
Publication Number 2018/103632
Status In Force
Filing Date 2017-12-05
Publication Date 2018-06-14
Owner
  • HARBIN INSTITUTE OF TECHNOLOGY (China)
  • THE BOEING COMPANY (USA)
Inventor
  • Zheng, Mingyi
  • Chi, Yuanqing
  • Sun, Ding
  • Qiao, Xiaoguang
  • Jiang, Hansi

Abstract

A Mg-Gd-Y-Zn-Zr alloy with high strength and toughness, corrosion resistance and anti-flammability and a process for preparation thereof are disclosed. The components and the mass percentages thereof in the Mg-Gd-Y-Zn-Zr alloy are: 3.0%≤Gd≤9.0%, 1.0%≤Y≤6.0%, 0.5%≤Zn≤3.0%, 0.2%≤Zr≤1.5%, the balance being Mg and inevitable impurities. The process for preparation thereof comprises: adding pure Mg into a smelting furnace for heating, then introducing mixed gases of CO 2 and SF 6 into the furnace for protection; adding other raw materials in sequence when the pure Mg is completely melted; preparing an ingot; conducting a homogenization treatment on the ingot prior to extrusion; conducting an aging treatment on the extruded alloy. A wrought magnesium alloy having superior overall performances and good fracture toughness, corrosion resistance and anti-flammability, with a small amount of rare earth element is obtained by adjusting the proportion of the alloy elements and by conventional casting, extrusion and heat treatment processes. The cost of the alloy is reduced while the strength of the alloy is maintained.

IPC Classes  ?

  • C22C 23/06 - Alloys based on magnesium with a rare earth metal as the next major constituent
  • C22C 1/03 - Making non-ferrous alloys by melting using master alloys

37.

A CARBON FIBER COMPOSITE, A MEDIUM INCORPORATING THE CARBON FIBER COMPOSITE, AND A RELATED METHOD

      
Application Number IB2017055117
Publication Number 2018/037377
Status In Force
Filing Date 2017-08-24
Publication Date 2018-03-01
Owner THE BOEING COMPANY (USA)
Inventor
  • Gross, Gwen Marie Lanphere
  • Blair, Lori Nelson
  • Taege, Deborah Ann

Abstract

Carbon fiber composite additives, media incorporating the carbon fiber composites, and related methods are provided herein. In some aspects, a composition includes at least one medium; and a carbon fiber composite incorporated with the at least one medium, the carbon fiber composite including one or more carbon fibers with an epoxy resin matrix applied thereto to produce a composition having improved characteristics and filtration performance.

IPC Classes  ?

  • B01D 39/20 - Other self-supporting filtering material of inorganic material, e.g. asbestos paper or metallic filtering material of non-woven wires
  • B01D 39/04 - Organic material, e.g. cellulose, cotton
  • B01J 20/20 - Solid sorbent compositions or filter aid compositions; Sorbents for chromatography; Processes for preparing, regenerating or reactivating thereof comprising inorganic material comprising carbon obtained by carbonising processes

38.

A PERMEABLE PAVEMENT AND CURED CARBON FIBER COMPOSITION AND A RELATED METHOD

      
Application Number IB2017055114
Publication Number 2018/037375
Status In Force
Filing Date 2017-08-24
Publication Date 2018-03-01
Owner
  • THE BOEING COMPANY (USA)
  • WASHINGTON STATE UNIVERSITY (USA)
Inventor
  • Englund, Karl Richard
  • Nassiri, Somayeh
  • Haselbach, Liv Martha
  • Li, Hui
  • Wen, Haifang
  • Fischer, Kenneth W.

Abstract

Shredded scrap cured carbon fiber composite material is recycled upon using this waste material in permeable, for example pervious, concrete which then exhibits improved mechanical and load bearing properties. The permeable pavement composition includes a quantity of pavement material, and a quantity of cured carbon fiber composite material (CCFCM) configured to be added to the pavement material to produce a reinforced composition having improved characteristics. An example of pavement material includes a pervious concrete material. The method includes providing a quantity of pavement material, and adding a quantity of cured carbon fiber composite material to the pavement material to produce a reinforced composition having improved characteristics.

IPC Classes  ?

  • C04B 28/02 - Compositions of mortars, concrete or artificial stone, containing inorganic binders or the reaction product of an inorganic and an organic binder, e.g. polycarboxylate cements containing hydraulic cements other than calcium sulfates
  • C04B 28/04 - Portland cements
  • E01C 7/14 - Concrete paving
  • E01C 11/22 - Gutters; Kerbs

39.

EPOXY RESIN

      
Application Number AU2017050748
Publication Number 2018/018070
Status In Force
Filing Date 2017-07-20
Publication Date 2018-02-01
Owner
  • THE BOEING COMPANY (USA)
  • COMMONWEALTH SCIENTIFIC AND INDUSTRIAL RESEARCH ORGANISATION (Australia)
Inventor
  • Varley, Russell John
  • Dao, Nguyen Buu
  • Tian, Wendy Wenjun
  • Christensen, Stephen
  • Tucker, Samuel
  • Wiggins, Jeffrey

Abstract

The present disclosure relates to epoxide containing compounds comprising three benzene units linked by bridging groups. The disclosure also relates to the production of curable epoxy resin formulations comprising said epoxide containing compounds, and their possible incorporation into composite materials such as fibre reinforced composites. Possible methods for formulating the compounds epoxide containing compounds, as described herein, are also disclosed.

IPC Classes  ?

  • C08G 59/32 - Epoxy compounds containing three or more epoxy groups
  • C08G 59/50 - Amines
  • C08K 7/02 - Fibres or whiskers
  • C08G 59/24 - Di-epoxy compounds carbocyclic
  • C08J 5/04 - Reinforcing macromolecular compounds with loose or coherent fibrous material
  • C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
  • C07D 303/02 - Compounds containing oxirane rings

40.

ULTRA-HIGH STRENGTH MARAGING STAINLESS STEEL WITH SALT-WATER CORROSION RESISTANCE

      
Application Number US2017040660
Publication Number 2018/022261
Status In Force
Filing Date 2017-07-05
Publication Date 2018-02-01
Owner
  • THE BOEING COMPANY (USA)
  • INSTITUTE OF METAL RESEARCH (China)
Inventor
  • Tian, Jialong
  • Yang, Ke
  • Wang, Wei
  • Shan, Yiyin
  • Yan, Wei

Abstract

An ultra-high strength maraging stainless steel with nominal composition (in mass) of C ≤ 0.03%, Cr: 13.0-14.0%, Ni: 5.5-7.0%, Co: 5.5-7.5%, Mo: 3.0-5.0%, Ti: 1.9-2.5%, Si: ≤ 0.1%, Mn: ≤ 0.1%, P: ≤ 0.01%, S: ≤ 0.01%, and Fe: balance. The developed ultra-high strength maraging stainless steel combines ultra-high strength (with σb ≥ 2000MPa, σ0.2≥1700MPa, δ ≥ 8% and ψ ≥ 40%), high toughness (KIC ≥ 83 MPa⋅m1/2) and superior salt water corrosion resistance (with pitting potential Epit ≥ 0.15 (vs SCE)). Therefore, this steel is suitable to make structural parts that are used in harsh corrosive environments like marine environment containing chloride ions, etc.

IPC Classes  ?

  • C22C 38/18 - Ferrous alloys, e.g. steel alloys containing chromium
  • C22C 38/22 - Ferrous alloys, e.g. steel alloys containing chromium with molybdenum or tungsten
  • C22C 38/28 - Ferrous alloys, e.g. steel alloys containing chromium with titanium or zirconium
  • C22C 38/30 - Ferrous alloys, e.g. steel alloys containing chromium with cobalt
  • C22C 38/40 - Ferrous alloys, e.g. steel alloys containing chromium with nickel
  • C22C 38/44 - Ferrous alloys, e.g. steel alloys containing chromium with nickel with molybdenum or tungsten
  • C21D 6/00 - Heat treatment of ferrous alloys
  • C22C 38/52 - Ferrous alloys, e.g. steel alloys containing chromium with nickel with cobalt
  • C21D 8/00 - Modifying the physical properties by deformation combined with, or followed by, heat treatment
  • C22C 38/50 - Ferrous alloys, e.g. steel alloys containing chromium with nickel with titanium or zirconium

41.

LOW RESOLUTION ADAPTIVE DISTANCE DISPLAY

      
Application Number AU2017050755
Publication Number 2018/014088
Status In Force
Filing Date 2017-07-21
Publication Date 2018-01-25
Owner
  • COMMONWEALTH SCIENTIFIC AND INDUSTRIAL RESEARCH ORGANISATION (Australia)
  • THE BOEING COMPANY (USA)
Inventor
  • Haddon, David
  • Wood, Brett
  • Kottege, Navinda
  • Flick, Paul

Abstract

Guide systems for indicating a distance between a first object and a second object and a method for visually representing a distance between two objects as the distance reduces are provided. A sensor measures a distance between the first object and the second object. A processor receives a distance measurement from the sensor and determines whether the distance measured by the sensor is within one of a plurality of distance intervals. Upon determining that the distance is within one of the plurality of distance intervals, the processor displays a distance indicator on the display. The distance indicator is located on the display based on the distance according to a scale for the distance interval, where a display area on the display represents the distance interval. The scale for the distance intervals becomes finer as the distance between the first object and the second object decreases.

IPC Classes  ?

  • G01S 7/64 - Luminous indications
  • G01S 7/51 - Display arrangements
  • G08G 5/06 - Traffic control systems for aircraft for control when on the ground

42.

POLYSILOXANE HYDRAULIC FLUIDS

      
Application Number AU2017050435
Publication Number 2017/193174
Status In Force
Filing Date 2017-05-11
Publication Date 2017-11-16
Owner
  • COMMONWEALTH SCIENTIFIC AND INDUSTRIAL RESEARCH ORGANISATION (Australia)
  • THE BOEING COMPANY (USA)
Inventor
  • Ballard, Mathew John
  • Casey, Philip Stephen
  • Holmes, Susan Wan-Yi
  • Way, Cameron David
  • Winzenberg, Kevin Norman
  • Hull, James

Abstract

The present disclosure relates to polysiloxanes, processes for preparing polysiloxanes, and hydraulic fluids comprising polysiloxanes. This disclosure also relates to hydraulic fluids comprising one or more polysiloxane compounds and diphosphonate compounds, and to the use of diphosphonate compounds in hydraulic fluids or as additives or components in various compositions, for example to provide fire retardant properties to a fluid or composition. This disclosure also relates to use of the compositions as hydraulic fluids, which may be used in various machines, vehicles and craft, including aircraft.

IPC Classes  ?

  • C08G 77/04 - Polysiloxanes
  • C08L 83/04 - Polysiloxanes
  • C10M 107/50 - Lubricating compositions characterised by the base-material being a macromolecular compound containing silicon
  • C10M 137/12 - Lubricating compositions characterised by the additive being an organic non-macromolecular compound containing phosphorus having a phosphorus-to-carbon bond

43.

POLYMERIC AGENTS AND COMPOSITIONS FOR INHIBITING CORROSION

      
Application Number AU2017050218
Publication Number 2017/152240
Status In Force
Filing Date 2017-03-10
Publication Date 2017-09-14
Owner
  • COMMONWEALTH SCIENTIFIC AND INDUSTRIAL RESEARCH ORGANISATION (Australia)
  • THE BOEING COMPANY (USA)
Inventor
  • Mardel, James Ivan
  • Cole, Ivan Stuart
  • White, Paul Andrew
  • Hughes, Anthony Ewart
  • Markley, Tracey Anne
  • Harvey, Timothy Graham
  • Osborne, Joseph
  • Sapper, Erik

Abstract

The present disclosure is directed to processes, compositions and agents for inhibiting corrosion in various substrates, for example metal substrates. The present disclosure is also directed to corrosion inhibitors comprising organometallic polymers such as metal-organic frameworks (MOFs), including compositions and processes comprising MOFs for inhibiting corrosion in metal substrates.

IPC Classes  ?

  • C09D 5/08 - Anti-corrosive paints
  • C09D 163/00 - Coating compositions based on epoxy resins; Coating compositions based on derivatives of epoxy resins
  • C07F 19/00 - Metal compounds according to more than one of main groups

44.

CARBON NANOMATERIAL COMPOSITE SHEET AND METHOD FOR MAKING THE SAME

      
Application Number US2016064789
Publication Number 2017/142610
Status In Force
Filing Date 2016-12-02
Publication Date 2017-08-24
Owner
  • THE BOEING COMPANY (USA)
  • GENERAL NANO, LLC (USA)
Inventor
  • Braley, Daniel, J.
  • Belk, John, H.
  • Battat, Jacob, I.
  • Truscello, Justine, M.
  • Ferriell, Daniel, R.
  • Sprengard, Joseph
  • Christy, Larry

Abstract

A carbon nanomaterial composite sheet and a method for making a carbon nanomaterial composite sheet may include a layer of a carbon nanomaterial structure being bonded to a carrier layer, the carrier layer being fabricated from a porous metalized nonwoven material.

IPC Classes  ?

  • C23C 24/08 - Coating starting from inorganic powder by application of heat or pressure and heat
  • C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
  • B32B 5/16 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by features of a layer formed of particles, e.g. chips, chopped fibres, powder
  • B32B 5/24 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer
  • B64C 3/20 - Integral or sandwich constructions

45.

SYSTEM AND METHOD FOR CONTACTLESS ENERGY TRANSFER TO A MOVING PLATFORM

      
Application Number US2016045969
Publication Number 2017/039961
Status In Force
Filing Date 2016-08-08
Publication Date 2017-03-09
Owner THE BOEING COMPANY (USA)
Inventor Jungwirth, Douglas R.

Abstract

A contactless energy transfer system has a first stationary platform (115, 310, 510, 610) and a second movable platform (100, 300, 500, 600). The first platform has at least one light source (120, 320, 520, 615, 650) coupled to a power source (210). The second separate platform has at least one photovoltaic module (130, 330, 530) mounted thereon. The at least one photovoltaic module is coupled to an energy storage system (140) mounted on the second platform such that any light received at the photovoltaic module is converted to electrical energy stored in the energy storage system. The second platform is configured to move in close proximity to the first platform along a predetermined pathway. The predetermined pathway may be linear or rotary. The light sources are positioned and configured to direct light at the photovoltaic modules during a predetermined interval when the second platform is in close proximity to the first platform (for the linear pathway) or constantly or at predetermined intervals.

IPC Classes  ?

  • H02J 50/30 - Circuit arrangements or systems for wireless supply or distribution of electric power using light, e.g. lasers

46.

COMPOSITIONS FOR INHIBITING CORROSION

      
Application Number AU2016050245
Publication Number 2016/154680
Status In Force
Filing Date 2016-03-31
Publication Date 2016-10-06
Owner
  • COMMONWEALTH SCIENTIFIC AND INDUSTRIAL RESEARCH ORGANISATION (Australia)
  • THE BOEING COMPANY (USA)
Inventor
  • Mardel, James Ivan
  • Cole, Ivan Stuart
  • White, Paul Andrew
  • Hughes, Anthony Ewart
  • Markley, Tracey Anne
  • Harvey, Timothy Graham
  • Osborne, Joseph
  • Sapper, Erik

Abstract

The present disclosure is directed to the agents, compositions, and methods for inhibiting corrosion in various substrates, for example in metal substrates. The compositions for inhibiting corrosion comprise at least one organic heterocyclic compound and at least one metal salt or mixed metal salt selected from rare earth, alkali earth and transition metals.

IPC Classes  ?

  • C09D 5/08 - Anti-corrosive paints
  • C23F 11/10 - Inhibiting corrosion of metallic material by applying inhibitors to the surface in danger of corrosion or adding them to the corrosive agent in other liquids using organic inhibitors
  • C23F 11/18 - Inhibiting corrosion of metallic material by applying inhibitors to the surface in danger of corrosion or adding them to the corrosive agent in other liquids using inorganic inhibitors
  • C04B 14/36 - Inorganic materials not provided for in groups
  • C04B 16/00 - Use of organic materials as fillers, e.g. pigments, for mortars, concrete or artificial stone; Treatment of organic materials specially adapted to enhance their filling properties in mortars, concrete or artificial stone
  • C09D 163/00 - Coating compositions based on epoxy resins; Coating compositions based on derivatives of epoxy resins
  • C08L 63/00 - Compositions of epoxy resins; Compositions of derivatives of epoxy resins
  • C23C 22/52 - Treatment of copper or alloys based thereon

47.

USE OF A DISULFIDE/DITHIOL COMPOUND IN A SEAL FOR ANODIZED ALUMINUM

      
Application Number US2015051722
Publication Number 2016/137533
Status In Force
Filing Date 2015-09-23
Publication Date 2016-09-01
Owner THE BOEING COMPANY (USA)
Inventor
  • Lawless, Lawrence, M.
  • Griffin, Bruce, M.

Abstract

Provided is a method for sealing an article with a non-chrome corrosion inhibitor seal. The method may include applying an aqueous-based suspension comprising a thiol-containing corrosion inhibitor on a surface of an anodized substrate.

IPC Classes  ?

48.

POLYVINYLBUTYRAL COATING CONTAINING THIOL CORROSION INHIBITORS

      
Application Number US2015065469
Publication Number 2016/100168
Status In Force
Filing Date 2015-12-14
Publication Date 2016-06-23
Owner THE BOEING COMPANY (USA)
Inventor
  • Kinlen, Patrick J.
  • Cremer, Melissa D.
  • Jackson, Eileen K.
  • Alves, Ofer

Abstract

Formulations, coatings and methods for coating a corrosion inhibiting formulation on a substrate are provided. The corrosion inhibiting formulation includes (a) at least one resin, (b) at least one Bronsted acid and (c) at least one thio-containing corrosion inhibitor

IPC Classes  ?

  • C09D 1/00 - Coating compositions, e.g. paints, varnishes or lacquers, based on inorganic substances
  • C09D 5/00 - Coating compositions, e.g. paints, varnishes or lacquers, characterised by their physical nature or the effects produced; Filling pastes
  • C09D 7/00 - Features of coating compositions, not provided for in group ; Processes for incorporating ingredients in coating compositions
  • C08K 5/00 - Use of organic ingredients

49.

PRE-FORMED THERMOPLASTIC FILLER FOR THERMOSET STRUCTURE

      
Application Number US2014043676
Publication Number 2016/089340
Status In Force
Filing Date 2014-06-23
Publication Date 2016-06-09
Owner THE BOEING COMPANY (USA)
Inventor
  • Forston, Gabriel Z.
  • Harris, Christopher G.
  • Tyndall, Joshua P.
  • Kwon, Hyukbong
  • Schmidt, Carolyn

Abstract

An apparatus includes a first thermoset layer (24A, 124A) that includes a first fibrous material embedded in a first thermoset matrix. The apparatus also includes a second thermoset layer (24B, 124B) that includes a second fibrous material embedded in a second thermoset matrix. The second thermoset layer (24B, 124B) is coupled to the first thermoset layer (24A, 124A) to form a joint (20, 120). Further, a gap (28, 128) is defined between the first thermoset layer (24A, 124A) and the second thermoset layer (24B, 124B). The apparatus also includes a thermoplastic filler (26, 126) that is made from a thermoplastic material. The thermoplastic filler (26, 126) is positioned within the gap (28, 128).

IPC Classes  ?

  • B29C 65/02 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure
  • B64C 1/06 - Frames; Stringers; Longerons
  • B64C 1/12 - Construction or attachment of skin panels
  • B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
  • B32B 3/06 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by features of form at particular places, e.g. in edge regions for attaching the product to another member, e.g. to a support
  • B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
  • B32B 7/04 - Interconnection of layers
  • B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
  • B29K 101/10 - Thermosetting resins
  • B29K 105/06 - Condition, form or state of moulded material containing reinforcements, fillers or inserts
  • B29K 307/04 - Carbon

50.

KICKED SPARS FOR RUDDER AND ELEVATOR APPLICATIONS

      
Application Number US2014058134
Publication Number 2016/053259
Status In Force
Filing Date 2014-09-29
Publication Date 2016-04-07
Owner THE BOEING COMPANY (USA)
Inventor Reusch, David, C.

Abstract

An aerodynamic structure incorporated in an aircraft control surface (10) provides a spar (16) extending along at least a portion of the control surface in a direction and the spar includes a plurality of bends along the direction of extension along the control surface to provide space to accommodate actuator fittings or other structural or operational requirements.

IPC Classes  ?

51.

COMPOSITIONS AND COATINGS WITH NON-CHROME CORROSION INHIBITOR PARTICLES

      
Application Number US2015051609
Publication Number 2016/049118
Status In Force
Filing Date 2015-09-23
Publication Date 2016-03-31
Owner THE BOEING COMPANY (USA)
Inventor
  • Kinlen, Patrick J.
  • Schultz, Karen A.
  • Krienke, Kenneth A.
  • Lawless, Lawrence M.
  • Schuette, Waynie M.

Abstract

Compositions are described for protecting a metal surface against corrosion. The composition includes a corrosion-inhibiting particle. The corrosion inhibiting particle may be usable in an epoxy resin-based coating or an olefin resin-based coating. The particle may include a core and a protectant. The core may include a water soluble corrosion inhibitor. The protectant may be disposed on at least a portion of a surface of the core and may be covalently or ionically bonded to a thiol group of the corrosion inhibitor. The protectant may be configured to reduce reaction between the core and the epoxy resin or the olefin resin

IPC Classes  ?

52.

HARMONIC DRIVE APPARATUS

      
Application Number US2015027711
Publication Number 2016/025039
Status In Force
Filing Date 2015-04-27
Publication Date 2016-02-18
Owner THE BOEING COMPANY (USA)
Inventor Jensen, Max Neal

Abstract

A harmonic drive apparatus (also known as a strain wave gear) is constructed with a circular, flexible spline disc having a generally flat configuration or a slightly conical configuration.

IPC Classes  ?

  • F16H 49/00 - Other gearing
  • F16H 1/32 - Toothed gearings for conveying rotary motion with gears having orbital motion in which the central axis of the gearing lies inside the periphery of an orbital gear

53.

HOLE-FILLING SLEEVE AND WASHER DESIGN FOR BOLT INSTALLATION

      
Application Number US2015027708
Publication Number 2016/022184
Status In Force
Filing Date 2015-04-27
Publication Date 2016-02-11
Owner THE BOEING COMPANY (USA)
Inventor
  • Achtner, Gerfried R.
  • Hall, Thomas D.
  • Mahn, Ryan M.
  • Manriquez, Javier

Abstract

A fastener assembly (100) which includes a sleeve (104) which includes a cylindrical construction having a first and second end portions and an outside diameter. The fastener assembly further includes a washer (110) associated with the sleeve wherein the washer includes a body which defines a first side (112) and an opposing second side (114) and defines an opening (120) which extends from the first side toward the second side. The opening defines a diameter greater than the outside diameter of the sleeve and the body defines a recess (122) which has a diameter greater than the diameter of the opening wherein the recess extends from the second side (114) towards the first side (112) such that the recess and the opening are in communication with one another. A method for using this fastener assembly is also provided.

IPC Classes  ?

  • B64D 45/02 - Lightning protectors; Static dischargers
  • F16B 19/02 - Bolts or sleeves for positioning of machine parts, e.g. notched taper pins, fitting pins, sleeves, eccentric positioning rings

54.

SHAPE MEMORY ALLOY ACTUATOR SYSTEM FOR COMPOSITE AIRCRAFT STRUCTURES

      
Application Number US2015024070
Publication Number 2016/018477
Status In Force
Filing Date 2015-04-02
Publication Date 2016-02-04
Owner THE BOEING COMPANY (USA)
Inventor
  • Dilligan, Matthew A.
  • Calkins, Frederick T.
  • Zimmerman, Tyler J.
  • Mabe, James H.
  • Blohowiak, Kay Y.

Abstract

Method and apparatus for controlling a shape of a composite structure. A shape memory structure associated with the composite structure is activated. The shape memory structure changes from a buckled shape to an original shape and causes the composite structure to change from an undeployed shape to a deployed shape. The shape memory structure is deactivated. The shape memory structure changes from the original shape to the buckled shape in response to a load from the composite structure and causes the composite structure to change from the deployed shape to the undeployed shape.

IPC Classes  ?

  • B64C 3/48 - Varying camber by relatively-movable parts of wing structures
  • B64C 3/44 - Varying camber
  • B64C 9/02 - Mounting or supporting thereof
  • B64C 9/16 - Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
  • B64C 13/50 - Transmitting means with power amplification using electrical energy

55.

CARGO COMPARTMENT INDICATION SYSTEM AND METHOD FOR TIE DOWN RESTRAINT LOCATIONS

      
Application Number US2015013207
Publication Number 2015/191115
Status In Force
Filing Date 2015-01-28
Publication Date 2015-12-17
Owner THE BOEING COMPANY (USA)
Inventor
  • Noe, Darrin M.
  • Stevens, Robert A.

Abstract

A system and method for identifying tie down restraint locations in a cargo compartment or other storage area is disclosed. The system includes labeling or otherwise highlighting the tie down locations on a floor (100) where the cargo is to be secured. The labeling is based on a reference coordinate system that is associated with a tie down plan. Additionally or alternatively, a tie down locator device (300) is mounted above the floor (100) that highlights or otherwise illuminates a tie down location. As a cargo handler completes a connection, the device highlights the next tie down location.

IPC Classes  ?

  • B64D 9/00 - Equipment for handling freight; Equipment for facilitating passenger embarkation or the like

56.

DISTORTION PREDICTION AND MINIMISATION IN ADDITIVE MANUFACTURING

      
Application Number AU2015000341
Publication Number 2015/184495
Status In Force
Filing Date 2015-06-05
Publication Date 2015-12-10
Owner
  • COMMONWEALTH SCIENTIFIC AND INDUSTRIAL RESEARCH ORGANISATION (Australia)
  • THE BOEING COMPANY (USA)
Inventor
  • Nguyen, Vu, Thua
  • Lathabai, Srinivasarao
  • Feng, Yuqing
  • Miller, Anthony
  • Barnes, John
  • Coleman, Gary
  • Helvey, Amy, Marie

Abstract

A method of minimising distortion in a workpiece is described that includes utilizing a computer system to carry out finite element analysis on a finite element thermo- mechanical model of the workpiece during and after fabrication by additive manufacturing to predict shape distortion and residual stress development in the workpiece, wherein the fabrication includes the fabrication step of depositing multiple layers of a material melted by a heat source along a deposit path on a substrate, and introducing alterations to the workpiece prior to or during fabrication to compensate for the predicted distortion.

IPC Classes  ?

  • G01B 21/32 - Measuring arrangements or details thereof in so far as they are not adapted to particular types of measuring means of the other groups of this subclass for measuring the deformation in a solid
  • G06F 17/50 - Computer-aided design
  • B33Y 50/00 - Data acquisition or data processing for additive manufacturing

57.

ICE ADHESION REDUCING PREPOLYMERS AND POLYMERS

      
Application Number AU2015000323
Publication Number 2015/179902
Status In Force
Filing Date 2015-05-29
Publication Date 2015-12-03
Owner
  • COMMONWEALTH SCIENTIFIC AND INDUSTRIAL RESEARCH ORGANISATION (Australia)
  • THE BOEING COMPANY (USA)
Inventor
  • Bateman, Stuart Arthur
  • Simons, Ranya
  • Li, Sheng
  • Russell, Lee
  • Bilyk, Alexander
  • Berry, Douglas Henry
  • Seebergh, Jill Elisabeth

Abstract

The present disclosure relates to an FPOSS prepolymer which may be reacted with a reactive coating or a polyisocyanate and/ or one or more of a polysiloxane, a polyol, a polyamine and a reactive coating; an FPOSS polyisocyanate prepolymer which may be reacted with one or more of a polysiloxane, a polyol, a polyamine or a reactive coating; and an FPOSS siloxane prepolymer which may be reacted with a polyisocyanate and/or one or more of a polyol, a polyamine or a reactive coating to form cross-linked polymers capable of reducing the ability of ice to adhere to the surface of an object, in particular aircraft or other vehicles, methods of producing the prepolymers and polymers and their use in coating surfaces.

IPC Classes  ?

  • C07F 7/21 - Cyclic compounds having at least one ring containing silicon but no carbon in the ring
  • C08G 18/61 - Polysiloxanes
  • C08G 77/04 - Polysiloxanes
  • C09D 5/16 - Anti-fouling paints; Underwater paints
  • C09D 183/10 - Block or graft copolymers containing polysiloxane sequences
  • C08F 220/22 - Esters containing halogen
  • C08F 283/12 - Macromolecular compounds obtained by polymerising monomers on to polymers provided for in subclass on to polysiloxanes
  • B05D 5/00 - Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures
  • C08L 83/10 - Block- or graft-copolymers containing polysiloxane sequences
  • C09K 3/18 - Materials not provided for elsewhere for application to surface to minimize adherence of ice, mist or water thereto; Thawing or antifreeze materials for application to surfaces

58.

ICE ADHESION REDUCING POLYMERS

      
Application Number AU2015000324
Publication Number 2015/179903
Status In Force
Filing Date 2015-05-29
Publication Date 2015-12-03
Owner
  • COMMONWEALTH SCIENTIFIC AND INDUSTRIAL RESEARCH ORGANISATION (Australia)
  • THE BOEING COMPANY (USA)
Inventor
  • Bateman, Stuart Arthur
  • Simons, Ranya
  • Li, Sheng
  • Russell, Lee
  • Berry, Douglas Henry
  • Seebergh, Jill Elisabeth

Abstract

The present disclosure relates to polymers which are cross-linked reaction products of a reactive siloxane and/or a polyisocyanate and/or a polyol, a polyamine and/or reactive coating capable of reducing the ability of ice to adhere to the surface of an object, in particular aircraft or other vehicles, methods of producing the polymers and their use in coating surfaces.

IPC Classes  ?

  • C08G 18/61 - Polysiloxanes
  • C08G 77/04 - Polysiloxanes
  • C09K 3/18 - Materials not provided for elsewhere for application to surface to minimize adherence of ice, mist or water thereto; Thawing or antifreeze materials for application to surfaces
  • C09D 183/04 - Polysiloxanes
  • C09D 183/10 - Block or graft copolymers containing polysiloxane sequences
  • C08F 283/02 - Macromolecular compounds obtained by polymerising monomers on to polymers provided for in subclass on to polycarbonates or saturated polyesters
  • C08L 83/04 - Polysiloxanes
  • B05D 5/00 - Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures

59.

SANDWICH PANEL JOINTS AND METHODS FOR JOINING SANDWICH PANELS

      
Application Number US2014039672
Publication Number 2015/183248
Status In Force
Filing Date 2014-05-28
Publication Date 2015-12-03
Owner THE BOEING COMPANY (USA)
Inventor Engquist, Bryan S.

Abstract

Joints for joining panels (60, 62) together, such as for joining honeycomb sandwich panels used in aerospace applications, and methods of joining said panels are disclosed. In some examples of disclosed joints, a first panel and a second panel can be joined together to form a joint. The first panel (60) can be a flat panel that includes a rabbet (80) formed along a first longitudinal edge, and the second panel (62) can be a curved panel that includes a notch (86) formed along a second longitudinal edge. In forming the joint, a portion of the rabbet (80) can be positioned within the notch (86), and the flat panel (60) and curved panel (62) can be oriented at a non- parallel and non-perpendicular angle to one another. Adhesive (99) is applied along the rabbet (80) and/or the notch (86) in order to secure the joint.

IPC Classes  ?

  • B29C 65/48 - Joining of preformed parts; Apparatus therefor using adhesives

60.

POSITIONING IN INDOOR LOCATIONS AND OTHER GPS-DENIED ENVIRONMENTS

      
Application Number US2015022550
Publication Number 2015/183390
Status In Force
Filing Date 2015-03-25
Publication Date 2015-12-03
Owner THE BOEING COMPANY (USA)
Inventor
  • Soto, Ely, V.
  • Weigand, Daniel

Abstract

Methods for: (1) determining range, velocity, and acceleration estimates with associated confidences; and (2) extracting range estimates using channel estimation are disclosed. These methods can be used to improve positioning solutions obtained by positioning systems used in indoor locations and other GPS-denied environments.

IPC Classes  ?

  • G01S 5/02 - Position-fixing by co-ordinating two or more direction or position-line determinations; Position-fixing by co-ordinating two or more distance determinations using radio waves

61.

LIGHTING AND DATA COMMUNICATION SYSTEM USING A REMOTELY LOCATED LIGHTING ARRAY

      
Application Number US2015017148
Publication Number 2015/178981
Status In Force
Filing Date 2015-02-23
Publication Date 2015-11-26
Owner THE BOEING COMPANY (USA)
Inventor Krug, William P.

Abstract

A lighting system for transmitting light to a plurality of specific locations is disclosed. The lighting system includes at least one source lighting array and a plastic optical fiber (POF). The source lighting array comprises a plurality of lighting elements. The plurality of lighting elements are each configured to generate visible light. The POF cable has an end in communication with the source lighting array. The POF cable transmits visible light generated by the source lighting array to the plurality of specific locations.

IPC Classes  ?

62.

AIRCRAFT INTERIOR MONITORING

      
Application Number US2015028905
Publication Number 2015/175245
Status In Force
Filing Date 2015-05-01
Publication Date 2015-11-19
Owner THE BOEING COMPANY (USA)
Inventor
  • Kumar, Anil
  • Lui-Kwan, Gerald D.

Abstract

A system for monitoring an aircraft interior may include a multiplicity of sensors each placed at a selected location of a plurality of locations within the aircraft interior. Each sensor is configured to monitor a condition in an associated area of the aircraft interior. The system may also include a server onboard the aircraft. The onboard server is configured to receive data from each of the multiplicity of sensors and to control operation of each of the multiplicity of sensors. The system may also include a router onboard the aircraft. The onboard router is configured to communicate with a router off-board the aircraft and to transfer data from the onboard server to the off-board router. The off-board router is associated with a ground monitoring facility configured to analyze data from each of the multiplicity of sensors, compare the data to reference data and an appropriate alert may be generated.

IPC Classes  ?

  • G08B 13/196 - Actuation by interference with heat, light, or radiation of shorter wavelength; Actuation by intruding sources of heat, light, or radiation of shorter wavelength using passive radiation detection systems using image scanning and comparing systems using television cameras

63.

OPTICAL FILTERING SYSTEM FOR SOLAR CELL TESTING

      
Application Number US2015020701
Publication Number 2015/175088
Status In Force
Filing Date 2015-03-16
Publication Date 2015-11-19
Owner THE BOEING COMPANY (USA)
Inventor Jungwirth, Douglas R.

Abstract

A method and apparatus for simulating light (133). A first light (124) from a first filterer (120) is output to a solar cell (106). The first light (124) output by the first filterer (120) has a coarse spectrum (128) that simulates the light (133) in a selected environment (134). A second light (126) from a second filterer (122) is output to the solar cell (106) while the first light (124) is output by the first filterer (120). The second light (126) output by the second filterer (122) has a fine spectrum (130) selected for a group of junctions (108) in the solar cell (106).

IPC Classes  ?

  • G01J 1/04 - Optical or mechanical part
  • G01J 1/08 - Arrangements of light sources specially adapted for photometry
  • F21S 8/00 - Lighting devices intended for fixed installation

64.

STRUCTURAL BONDED PATCH WITH TAPERED ADHESIVE DESIGN

      
Application Number US2015012897
Publication Number 2015/167630
Status In Force
Filing Date 2015-01-26
Publication Date 2015-11-05
Owner THE BOEING COMPANY (USA)
Inventor Dan-Jumbo, Eugene, A.

Abstract

A method and apparatus for reworking a composite structure. A composite rework patch system comprises a composite rework patch and a plurality of adhesive layers. The composite rework patch includes a first side having a contour conforming to an inconsistent area on the composite structure. The composite re patch comprises a plurality of regions having different structural properties. The plurality of adhesive layers is on the first side of the composite rework patch. The plurality of adhesive layers change in thickness within at least one region of the composite rework patch to form tapered adhesive sections.

IPC Classes  ?

  • B29C 73/00 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass
  • B32B 7/02 - Physical, chemical or physicochemical properties
  • B32B 5/14 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by a layer differing constitutionally or physically in different parts, e.g. denser near its faces
  • B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
  • F16B 11/00 - Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding

65.

HITLESS REARRANGEMENT OF A SATELLITE-HOSTED SWITCH VIA PROPAGATED SYNCHRONIZATION

      
Application Number US2015028012
Publication Number 2015/168138
Status In Force
Filing Date 2015-04-28
Publication Date 2015-11-05
Owner THE BOEING COMPANY (USA)
Inventor
  • Scott, James, P.
  • Hoffmeyer, Mark, A.
  • Nichols, Harry, E.
  • Miller, Kristina

Abstract

An apparatus includes an analog front end to receive an analog input including user data, and an analog-to-digital converter to convert the analog input to digital signals including the user data. A digital channelizer may process the digital signals to generate frequency slices of user data, and a digital combiner may assemble the frequency slices to form output sub-bands of user data. A digital switch may route the frequency slices from the digital channelizer to the digital combiner according to a selected map of a plurality of available maps. The apparatus also includes a map selector to communicate map select data that indicates the selected map. The digital channelizer may receive and insert the map select data into the frequency slices in-band with the user data thereof. And the digital switch may interpret the map select data inserted into and route the frequency slices according to the selected map.

IPC Classes  ?

66.

OPTICAL SCANNER AND PROJECTION APPARATUS FOR THERMAL MANAGEMENT OF COMPOSITE REPAIRS AND METHOD OF THERMAL MANAGEMENT

      
Application Number US2015011410
Publication Number 2015/160395
Status In Force
Filing Date 2015-01-14
Publication Date 2015-10-22
Owner THE BOEING COMPANY (USA)
Inventor
  • Spalding, John F.
  • Sharp, Kristen
  • Bird, Meredith M.
  • Lutz, Melissa

Abstract

An apparatus for thermal management of a composite plies and adhesive applied to a repair area on a composite structure uses a combination of an optical scanner and projection system, coded photogrammetric targets, a coded two-dimensional thermocouple array and a coded heat blanket that all communicate with a computerized control system that develops spatial relationships between the composite structure being repaired, the repair area of the composite structure, the thermocouples used to monitor the temperatures in the repair area and the heat blanket used to heat the repair area. The optical scanner and projection system projects identifications of the thermocouples and the real time temperatures of the thermocouples at the positions of the thermocouples over the repair area on the composite structure.

IPC Classes  ?

  • G01K 1/02 - Special applications of indicating or recording means, e.g. for remote indications
  • G01K 7/21 - Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat using resistive elements the element being a linear resistance, e.g. platinum resistance thermometer in a specially-adapted circuit, e.g. bridge circuit for modifying the output characteristic, e.g. linearising
  • B29C 35/02 - Heating or curing, e.g. crosslinking or vulcanising
  • B29C 73/12 - Apparatus therefor, e.g. for applying
  • B29C 73/34 - Apparatus or accessories not otherwise provided for for local pressing or local heating for local heating
  • B29C 73/30 - Apparatus or accessories not otherwise provided for for local pressing or local heating

67.

MODULAR ANTENNA ASSEMBLY

      
Application Number US2015011644
Publication Number 2015/160397
Status In Force
Filing Date 2015-01-15
Publication Date 2015-10-22
Owner THE BOEING COMPANY (USA)
Inventor
  • Hafenrichter, Joseph L.
  • Urcia, Manny S.
  • Marshall, Joseph A.
  • Manry, Charles W.
  • Adeeyo, Mohammed-Nasar M.

Abstract

Embodiments of the present disclosure provide an antenna assembly (10) that includes a plurality of separate and distinct antenna modules (22) that are interconnected together to form an antenna layer (14). Each of the antenna modules may include a support structure including a core frame connected to a core support, and a backskin connected to one or both of the core frame and the core support. The antenna assembly may also include an alignment grid (16) configured to receive and align each of the antenna modules, and/or a matching layer (18) configured to receive and align each of the antenna modules.

IPC Classes  ?

  • H01Q 21/00 - Antenna arrays or systems
  • H01Q 1/40 - Radiating elements coated with, or embedded in, protective material
  • H01Q 21/06 - Arrays of individually energised antenna units similarly polarised and spaced apart

68.

STRUCTURAL ARRANGEMENT AND METHOD OF FABRICATING A COMPOSITE TRAILING EDGE CONTROL SURFACE

      
Application Number US2015010967
Publication Number 2015/156857
Status In Force
Filing Date 2015-01-12
Publication Date 2015-10-15
Owner THE BOEING COMPANY (USA)
Inventor Reusch, David C.

Abstract

The present disclosure is generally directed to a composite trailing edge control surface (600) including a contiguous one-piece composite control surface skin (200) wrapped around a plurality of stiffening cores (300), a plurality of hinge fittings (400), and a plurality of substantially parallel ribs (500). The contiguous one-piece composite control surface skin provides a control surface on opposing sides of the trailing edge control surface and substantially distributes bending, shear and torsion loads of the trailing edge control surface to the plurality of hinge fittings and the plurality of substantially parallel ribs. A method of manufacturing the trailing edge control surface includes positioning a contiguous one-piece composite control surface skin (200) on a substantially flat tool. A plurality of stiffener cores (300) having a plurality of thin covering skins are positioned on the contiguous one-piece composite control surface skin and are cured to create a laminate sandwich composite structure skin (350) that is trimmed and has fastener apertures and hinge fitting access apertures (210) provided there-through.

IPC Classes  ?

  • B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
  • B64C 3/20 - Integral or sandwich constructions
  • B64C 9/02 - Mounting or supporting thereof
  • B64C 9/16 - Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
  • B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
  • B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces, or the like

69.

AIRCRAFT BODY MOUNTED ENERGY ABSORBING RUB STRIP

      
Application Number US2015010964
Publication Number 2015/156856
Status In Force
Filing Date 2015-01-12
Publication Date 2015-10-15
Owner THE BOEING COMPANY (USA)
Inventor
  • Cottet, Justin D.
  • Kepner, Roger S.
  • Drake, Michael L.

Abstract

An energy absorbing rub strip having a core material and a fairing positioned over the core material. The core material may be configured to buckle under the application of a predetermined amount of force and the fairing may be configured to be attached to a fuselage of an aircraft. The fairing may be made out of an abrasive-resistant material such as titanium or a nickel-based metal. The core material may be comprised of an aluminum honeycomb. The core material may be comprised of a dual density material. The length of the rub strip may extend beyond potential contact points on the fuselage during landing and takeoff. Upon a ground contact event, the thickness of deformed/buckled core material may be measured to determine if the ground contact event may have caused structural damage to the aircraft.

IPC Classes  ?

  • B32B 3/12 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
  • B32B 15/01 - Layered products essentially comprising metal all layers being exclusively metallic
  • B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces, or the like
  • B64C 25/06 - Undercarriages fixed
  • B64C 25/58 - Arrangements or adaptations of shock-absorbers or springs
  • B64D 45/06 - Landing aids; Safety measures to prevent collision with earth's surface mechanical
  • F16F 7/12 - Vibration-dampers; Shock-absorbers using plastic deformation of members

70.

AUTONOMOUS POWER GENERATION IN SUBMERSIBLE ENVIRONMENTS

      
Application Number US2015011018
Publication Number 2015/156860
Status In Force
Filing Date 2015-01-12
Publication Date 2015-10-15
Owner THE BOEING COMPANY (USA)
Inventor
  • Cantwell, Jeffrey Richard
  • Conniff, James D.

Abstract

Embodiments provide for safely and reliably operating a generator in a submersible environment utilizing an autonomous control system. One embodiment is a power generation system that includes a generator, a water-tight enclosure surrounding the generator, an intake valve, an exhaust valve, and a controller. The intake valve couples an air intake on the generator to an outside surface of the enclosure. The exhaust valve couples an exhaust port on the generator to the outside surface. If the controller determines that the enclosure will submerge, then the controller stops the generator and closes the intake valve and the exhaust valve. After detecting that the enclosure has surfaced, the controller opens the intake valve, opens the exhaust valve, and starts the generator.

IPC Classes  ?

  • B63G 8/12 - Propulsion using internal-combustion engines
  • B63G 8/36 - Adaptations of ventilation, cooling, heating, or air-conditioning
  • B63H 21/14 - Use of propulsion power plant or units on vessels the vessels being motor-driven relating to internal-combustion engines
  • B63H 21/17 - Use of propulsion power plant or units on vessels the vessels being motor-driven by electric motor

71.

DIELECTRIC SLAB CIRCULAR WAVEGUIDE POLARIZER

      
Application Number US2015012939
Publication Number 2015/156895
Status In Force
Filing Date 2015-01-26
Publication Date 2015-10-15
Owner THE BOEING COMPANY (USA)
Inventor
  • Adams, Alec
  • Blaser, Bruce L.

Abstract

A circular dielectric polarizer can have a cylindrical shape and include a dielectric slab, a dielectric core, and at least one air cutouts portions of the dielectric core. The dielectric slab can include a first dielectric material and have a thickness centered about an axis of the cylindrical shape. The dielectric core can include a second dielectric material. Portions of the dielectric core can be located on different sides of the dielectric slab. The dielectric core and the dielectric slab can form the cylindrical shape. The dielectric constant of the first dielectric material can be higher than a dielectric constant of the second dielectric material. Parameters of the circular dielectric polarizer, the dielectric slab, the dielectric core, and the at least one air cutout are selected to obtain approximately a 90 degree difference in phase in a signal passing through the circular dielectric polarizer at a target frequency.

IPC Classes  ?

  • H01P 1/17 - Auxiliary devices for rotating the plane of polarisation for producing a continuously rotating polarisation, e.g. circular polarisation

72.

POSITIONING SYSTEM FOR AN ELECTROMECHANICAL ACTUATOR

      
Application Number US2015011634
Publication Number 2015/152981
Status In Force
Filing Date 2015-01-15
Publication Date 2015-10-08
Owner THE BOEING COMPANY (USA)
Inventor
  • Blanding, David E.
  • Wijaya, Suzanna
  • Singh, Niharika

Abstract

Provided is a shaft positioning system for an electromechanical actuator. According to various examples, the positioning system includes a shaft coupled to an electromechanical actuator. The shaft moves along a linear axis and the electromechanical actuator is free to translate during normal operation. An electromagnetic coil positioned around at least a portion of the shaft. The electromagnetic coil produces a magnetic field when electrical current is applied. A metal housing surrounds at least a portion of the electromagnetic coil. The shaft is placed in a predetermined position when the metal housing is in contact with a first magnet and translational motion of the electromechanical actuator is restricted when the shaft is placed in the predetermined position.

IPC Classes  ?

  • H01F 7/06 - Electromagnets; Actuators including electromagnets
  • H01F 7/122 - Guiding or setting position of armatures, e.g. retaining armatures in their end position by permanent magnet
  • H01F 7/16 - Rectilinearly-movable armatures
  • H01F 7/123 - Guiding or setting position of armatures, e.g. retaining armatures in their end position by ancillary coil

73.

STAND-OFF DELIVERY OF UNMANNED UNDERWATER VEHICLES

      
Application Number US2015011603
Publication Number 2015/147970
Status In Force
Filing Date 2015-01-15
Publication Date 2015-10-01
Owner THE BOEING COMPANY (USA)
Inventor Stowers, Kyle

Abstract

A projectile (100) that includes a guidance kit (102,103) that directs the projectile in flight. The projectile further includes a shell and a hollow nose cone (106). The shell mates with the guidance kit and the nose cone couples with the shell. The nose cone includes an interior surface configured to house a UUV (202). The projectile further includes a controller (108) that identifies a condition for deploying the UUV in flight, and detaches the nose cone from the shell in response to determining that the condition is satisfied.

IPC Classes  ?

  • F42B 15/22 - Missiles having a trajectory finishing below water surface
  • F42B 19/46 - Marine torpedoes, e.g. launched by surface vessels or submarines; Sea mines having self-propulsion means adapted to be launched from aircraft
  • F42B 17/00 - Rocket torpedoes, i.e. missiles provided with separate propulsion means for movement through air and through water
  • F42B 22/44 - Marine mines, e.g. launched by surface vessels or submarines adapted to be launched from aircraft

74.

SPACECRAFT DOCKING SYSTEM

      
Application Number US2014066553
Publication Number 2015/142390
Status In Force
Filing Date 2014-11-20
Publication Date 2015-09-24
Owner THE BOEING COMPANY (USA)
Inventor
  • Ghofranian, Siamak
  • Chuang, Li-Ping, Christopher
  • Motaghedi, Pejmun

Abstract

A method and apparatus for docking a spacecraft. The apparatus comprises elongate members (300), movement systems (302, 504), and force management systems (304, 610). The elongate members are associated with a docking structure for a spacecraft. The movement systems are configured to move the elongate members axially such that the docking structure for the spacecraft moves. Each of the elongate members is configured to move independently. The force management systems connect the movement systems to the elongate members and are configured to limit a force applied by the each of the elongate members to a desired threshold during movement of the elongate members.

IPC Classes  ?

  • B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements

75.

HYBRID STRUCTURE INCLUDING BUILT-UP SANDWICH STRUCTURE AND MONOLITHIC SPF/DB STRUCTURE

      
Application Number US2014069820
Publication Number 2015/142394
Status In Force
Filing Date 2014-12-11
Publication Date 2015-09-24
Owner THE BOEING COMPANY (USA)
Inventor
  • Runyan, Max R.
  • Sanders, Daniel G.
  • Mauldin, Jack W.
  • Ludwig, Brent C.
  • Comfort, John M.
  • Hefti, Larry D.
  • Joel, Jason F.

Abstract

A hybrid structure comprises a metallic built-up sandwich structure, and a monolithic superplastic formed and diffusion bonded structure joined to the built-up sandwich structure.

IPC Classes  ?

  • B32B 15/14 - Layered products essentially comprising metal next to a fibrous or filamentary layer
  • B32B 15/01 - Layered products essentially comprising metal all layers being exclusively metallic
  • B32B 15/18 - Layered products essentially comprising metal comprising iron or steel
  • B64C 7/02 - Nacelles
  • B64D 29/06 - Attaching of nacelles, fairings, or cowlings
  • F02K 1/82 - Jet pipe walls, e.g. liners
  • F02C 7/24 - Heat or noise insulation
  • B32B 7/04 - Interconnection of layers

76.

SHORT LANDING WARNING

      
Application Number US2015017145
Publication Number 2015/142481
Status In Force
Filing Date 2015-02-23
Publication Date 2015-09-24
Owner THE BOEING COMPANY (USA)
Inventor Henderson, Mark H.

Abstract

A method can include determining that an aircraft is on approach to a runway. The method can include determining a flight path vector (FPV) location of the aircraft based at least in part on a projected landing location with respect to the runway and determining a current airspeed of the aircraft. The method can also include performing at least one of the following: issuing a landing short alert to a pilot of the aircraft if the FPV location is at or before the runway threshold, issuing an airspeed caution alert if the FPV location is between the runway threshold and the target runway location and if the current airspeed is below a landing short envelope, and determining not to issue an alert if the FPV location is between the runway threshold and the target runway location and if the current airspeed is at or above the landing short envelope.

IPC Classes  ?

  • B64D 45/04 - Landing aids; Safety measures to prevent collision with earth's surface
  • G05D 1/06 - Rate of change of altitude or depth

77.

INTEGRATED ARMOR FOR HYPERVELOCITY IMPACTS

      
Application Number US2014065154
Publication Number 2015/138011
Status In Force
Filing Date 2014-11-12
Publication Date 2015-09-17
Owner THE BOEING COMPANY (USA)
Inventor
  • Albert, Jeremie J.
  • Laverty, Richard R.
  • Gabrys, Jonathan W.
  • Graves, Russell F.

Abstract

A structural armor (302) includes two armor facesheets (306,308), with an angular member core (304) disposed between. The angular member core (304) may include a number of nodes (312) abutting the armor facesheets (306,308), with angular members (310) intersecting at the nodes (312) at acute node angles from the armor facesheets (306,308) and extending between the armor facesheets (306,308). The acute node angles correspond with estimated spread angles of a debris field resulting from an impact of an object with an armor facesheet while moving at hypervelocity speed.

IPC Classes  ?

  • F41H 5/02 - Plate construction
  • F41H 5/04 - Plate construction composed of more than one layer

78.

CALIBRATION OF SENSOR ARRAYS

      
Application Number US2015011030
Publication Number 2015/138046
Status In Force
Filing Date 2015-01-12
Publication Date 2015-09-17
Owner THE BOEING COMPANY (USA)
Inventor Soohoo, Kie L.

Abstract

An exemplary system measures a distance to a target object with the sensors. The system calculates a first position of the target object based on measurements from a first pair of the sensors and calibrated sensor coordinates for the first pair, calculates a second position of the target object based on measurements from a second pair of the sensors and the calibrated sensor coordinates for the second pair, and calculates a third position of the target object based on measurements from a third pair of the sensors and the calibrated sensor coordinates for the third pair. The system then compares the first position, the second position, and the third position calculated for the target object, and determines that the calibrated sensor coordinates for one or more of the sensors are inaccurate if a difference between the first, second, and third positions exceeds a threshold.

IPC Classes  ?

  • G01S 17/87 - Combinations of systems using electromagnetic waves other than radio waves
  • G01S 7/40 - Means for monitoring or calibrating
  • G01S 7/497 - Means for monitoring or calibrating
  • G01S 7/52 - RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES - Details of systems according to groups , , of systems according to group
  • G01S 13/87 - Combinations of radar systems, e.g. primary radar and secondary radar
  • G01S 15/87 - Combinations of sonar systems

79.

GRAPHENE COATED ELECTRONIC COMPONENTS

      
Application Number US2015015630
Publication Number 2015/138080
Status In Force
Filing Date 2015-02-12
Publication Date 2015-09-17
Owner THE BOEING COMPANY (USA)
Inventor
  • Li, Angela W.
  • Hunt, Jeffrey H.
  • Howe, Wayne R.

Abstract

In one aspect, coated electrical components are described herein. In some implementations, a coated electrical component comprises an electrical component and a graphene coating layer disposed on a surface of the electrical component. The graphene coating layer, in some implementations, has a thickness of about 300 nm or less. In another aspect, methods of increasing the service life of an electronic apparatus are disclosed herein. In some implementations, such a method comprises disposing a graphene coating layer on an environment-facing surface of an electronic component of the apparatus, wherein the electronic apparatus exhibits at least a 10 percent improvement in environmental testing performance compared to an otherwise equivalent electronic apparatus not comprising a graphene coating layer, the environmental testing performance comprising performance in a waterproofness test, acetic acid test, sugar solution test, or methyl alcohol test described herein.

IPC Classes  ?

  • H01L 23/29 - Encapsulation, e.g. encapsulating layers, coatings characterised by the material
  • B82Y 30/00 - Nanotechnology for materials or surface science, e.g. nanocomposites
  • H01L 21/56 - Encapsulations, e.g. encapsulating layers, coatings

80.

METHOD AND SYSTEM FOR PRODUCING ELECTRICITY FROM ACOUSTICAL ENERGY

      
Application Number US2015019166
Publication Number 2015/138236
Status In Force
Filing Date 2015-03-06
Publication Date 2015-09-17
Owner THE BOEING COMPANY (USA)
Inventor Toh, Chin H.

Abstract

A system and method for generating electricity from acoustic energy from an aircraft on a runway. Acoustic wave collectors mounted along the runway collect the acoustic energy and direct such acoustic energy to an associated acoustic converter assembly. A vibrating element is mounted within a housing of the acoustic converter assembly. The vibrating element moves in response to the acoustic energy. This movement draws air into the housing below the vibrating element and then forces the air downward to form an output air flow. The output air flow is directed to an associated turbine assembly to cause a shaft to rotate at a rate proportional to the magnitude of the received output air flow. An associated generator that is coupled to the shaft generates electricity proportionally to the rate of rotation of the shaft. The electricity from each generator is converted and sent to a substation for distribution

IPC Classes  ?

  • F03G 7/00 - Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for
  • F03D 9/00 - Adaptations of wind motors for special use; Combinations of wind motors with apparatus driven thereby; Wind motors specially adapted for installation in particular locations

81.

GRAPHENE-BASED THERMAL MANAGEMENT SYSTEMS

      
Application Number US2015017043
Publication Number 2015/138110
Status In Force
Filing Date 2015-02-23
Publication Date 2015-09-17
Owner THE BOEING COMPANY (USA)
Inventor
  • Li, Angela W.
  • Hunt, Jeffrey H.
  • Howe, Wayne R.

Abstract

In one aspect, thermally managed electronic components are described herein. In some implementations, a thermally managed electronic component comprises an electronic component and a thermal management coating disposed on a surface of the electronic component. The thermal management coating comprises a graphene coating layer disposed on the surface of the component. The graphene coating layer may comprise a layer of aligned carbon nanoparticles. Moreover, the thermal management coating may further comprise an additional layer of aligned carbon nanoparticles disposed on the graphene coating layer. In another aspect, methods of applying a thermal management coating on an electronic component are disclosed. In some implementations, such a method comprises disposing a graphene coating layer on a surface of an electronic component. The graphene coating layer may comprise a layer of aligned carbon nanoparticles. Such a method may further comprise disposing an additional layer of aligned carbon nanoparticles on the graphene coating layer

IPC Classes  ?

  • H01L 23/373 - Cooling facilitated by selection of materials for the device

82.

WIRELESSLY POWERED ELECTRIC MOTOR

      
Application Number US2014069154
Publication Number 2015/134077
Status In Force
Filing Date 2014-12-08
Publication Date 2015-09-11
Owner THE BOEING COMPANY (USA)
Inventor
  • Zeng, Peng
  • Tillotson, Brian J

Abstract

A method and apparatus for controlling an electric motor. Power is transmitted to windings of the electric motor by wireless magnetic coupling between transmission coils and the windings.

IPC Classes  ?

  • H02P 27/04 - Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage
  • H02J 5/00 - Circuit arrangements for transfer of electric power between ac networks and dc networks
  • H04B 5/00 - Near-field transmission systems, e.g. inductive loop type

83.

SYSTEMS AND METHODS FOR GROUND COLLISION AVOIDANCE

      
Application Number US2014069163
Publication Number 2015/134078
Status In Force
Filing Date 2014-12-08
Publication Date 2015-09-11
Owner THE BOEING COMPANY (USA)
Inventor
  • Baer, Joshua J
  • Thoreen, Adam M.
  • Wyckoff, Peter N.

Abstract

A system for displaying guidance aids to a crew for ground obstacle avoidance, particularly wingtip clearance. Perspective areas are drawn representing the current locations of the wingtips over the ground and predicted locations out into the future for a specified time or a specified distance. A flight crew may use these displayed guidance aids to determine the proximity of any perceived threat to the airplane. This capability addresses the costly problem of wingtip/airplane ground collisions. The disclosed graphical cue systems are specifically targeted toward aircraft that have a large wing span/size and/or folding wingtips.

IPC Classes  ?

  • G08G 5/04 - Anti-collision systems
  • G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed, acceleration
  • G08G 5/00 - Traffic control systems for aircraft
  • G08G 5/06 - Traffic control systems for aircraft for control when on the ground

84.

SYSTEM AND METHOD TO PREDICT WHETHER A PROTECTION CIRCUIT IS LIKELY TO PREVENT A LATENT FAILURE WITHIN A MONITORED CIRCUIT

      
Application Number US2015010989
Publication Number 2015/134116
Status In Force
Filing Date 2015-01-12
Publication Date 2015-09-11
Owner THE BOEING COMPANY (USA)
Inventor
  • Chesnut, Kay
  • Le, Anthony C.
  • Dooley, Maryanne

Abstract

A method includes measuring a plurality of latchup release parameter values of a monitored circuit to generate data. Each latchup release parameter value of the plurality of latchup release parameter values is associated with the monitored circuit exiting a latchup state. The method also include predicting, based on the data and based on one or more characteristic values of a protection circuit coupled to the monitored circuit, whether the protection circuit is likely to prevent an occurrence of a latent failure within the monitored circuit in particular latchup conditions.

IPC Classes  ?

  • G01R 31/28 - Testing of electronic circuits, e.g. by signal tracer
  • G01R 31/311 - Contactless testing using non-ionising electromagnetic radiation, e.g. optical radiation of integrated circuits

85.

BUNG PLUG EXTRACTOR AND METHODS FOR TRANSFERRING FLUID WITH A PRESSURIZED TANK

      
Application Number US2014066548
Publication Number 2015/130357
Status In Force
Filing Date 2014-11-20
Publication Date 2015-09-03
Owner THE BOEING COMPANY (USA)
Inventor Holthaus, Mark J.

Abstract

An apparatus for exchanging fluid with a tank through a tank port includes a bung extractor casing that has a first end configured to removably couple to a tank port. The tank port is configured to be sealingly coupled to a bung plug. The bung extractor casing also includes a second end opposite the first end, a hose connector configured to removably couple to a hose, and a channel defined between the first end and the hose connector. The apparatus also includes a bung extractor coupled to the extractor casing second end. The bung extractor includes a tip portion configured to releasably engage the bung plug. The bung extractor is operable to selectively uncouple the bung plug from the tank port such that a sealed flow path is formed through the tank port and the channel.

IPC Classes  ?

  • B67B 7/04 - Cork-screws
  • B67B 7/42 - Devices for removing barrel bungs
  • B67B 7/02 - Hand- or power-operated devices for opening closed containers for removing stoppers
  • B67D 1/08 - Apparatus or devices for dispensing beverages on draught - Details
  • B25B 27/00 - Hand tools or bench devices, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for

86.

TWO-DIMENSIONAL MODEL OF TRIANGULAR SECTORS FOR USE IN GENERATING A MESH FOR FINITE ELEMENT ANALYSIS

      
Application Number US2015011756
Publication Number 2015/130411
Status In Force
Filing Date 2015-01-16
Publication Date 2015-09-03
Owner THE BOEING COMPANY (USA)
Inventor Grip, Robert E.

Abstract

A method and apparatus for analyzing a joint (201). The apparatus comprises a graph generator (220) and a model generator (224). The graph generator (220) forms a first graph (226) based on a plurality of points (215) within a region (217). The plurality of points (215) represent a plurality of locations relative to a structure (202) for a plurality of fastener devices (204) configured to be installed in the structure (202) to form a joint (201). The graph generator (220) is configured to identify primary points (234) and secondary points (236) based on the first graph (226). The graph generator (220) is further configured to form a second graph (238) using the primary points (234), the secondary points (236), and the first graph (226). The model generator (224) is configured to generate a two-dimensional model (212) comprised of triangular sectors (213) using vertices (252) of the second graph (238). The two-dimensional model (212) is configured for use in forming a mesh (214) for use in performing finite element analysis (216) for the joint (201).

IPC Classes  ?

  • G06T 17/20 - Wire-frame description, e.g. polygonalisation or tessellation
  • G06F 17/50 - Computer-aided design

87.

REMOTE DATA DELIVERY SYSTEM

      
Application Number US2015013181
Publication Number 2015/130421
Status In Force
Filing Date 2015-01-28
Publication Date 2015-09-03
Owner THE BOEING COMPANY (USA)
Inventor
  • Kasik, David Joseph
  • Briggs, David D.

Abstract

A method and apparatus for delivering engineering data (352) to a portable device (232)for use in performing an operation. Engineering data for each part in a set of parts (226) is stored in a file system (324) on the portable device (232). A set of entries (330), each entry including a part identifier (334) and a target locator (335) for a part, is created for the set of parts (226) to form a table (328). An initial locator (344) constructed by a visualization tool (306 is matched to a target locator (350) in the table (328) for a selected part (336). The target locator (350) identifies a physical location in the file system (324) of requested engineering data (352) for the selected part (336). A local server (316) on the portable device (232) retrieves(406) the requested engineering data (352) based on the target locator (350). The local server (316) serves (408) the requested engineering data (352) to a browser (342), which displays the requested engineering data (352) for use in performing the operation on the selected part (336).

IPC Classes  ?

88.

SYSTEM AND METHOD FOR SURFACE CLEANING

      
Application Number US2015014451
Publication Number 2015/126628
Status In Force
Filing Date 2015-02-04
Publication Date 2015-08-27
Owner THE BOEING COMPANY (USA)
Inventor Ponomarev, Sergey

Abstract

A system (10) for cleaning an object (18) includes an acoustic device (20) configured to deliver acoustic waves (28) to the object (18), a cleaning medium dispenser (22) configured to deliver a cleaning medium (30) to a surface (16) of the object (18), a rinsing medium dispenser (24) configured to deliver a rinsing medium (32) to the surface (16), a vacuum (26) configured to deliver a vacuum airflow (34) proximate the surface (16), wherein the acoustic waves (28) generate acoustic vibrations in the object (18) to dislodge debris (14) from the surface (16), acoustically treat the cleaning medium (30) and the rinsing medium (32), and atomize the cleaning medium (30), the debris (14) collected by the cleaning medium (30) and the rinsing medium (32).

IPC Classes  ?

  • B08B 3/12 - Cleaning involving contact with liquid with additional treatment of the liquid or of the object being cleaned, e.g. by heat, by electricity, by vibration by sonic or ultrasonic vibrations
  • B08B 7/02 - Cleaning by methods not provided for in a single other subclass or a single group in this subclass by distortion, beating, or vibration of the surface to be cleaned

89.

ELECTRONICS OPERATION FOR TEMPERATURE CONTROLLED SYSTEMS

      
Application Number US2015011562
Publication Number 2015/126541
Status In Force
Filing Date 2015-01-15
Publication Date 2015-08-27
Owner THE BOEING COMPANY (USA)
Inventor Bernhardt, Roger David

Abstract

An apparatus and method of controlling temperatures of a plurality of locations on a structure. A temperature at each of the plurality of locations is identified. A desired temperature for each of the plurality of locations is identified. Processing of a workload by a processor at each of the plurality of locations is controlled to control the temperature at each of the plurality of locations to match the corresponding desired temperature for each of the plurality of locations.

IPC Classes  ?

  • G05D 23/19 - Control of temperature characterised by the use of electric means
  • G06F 1/20 - Cooling means
  • G06F 9/50 - Allocation of resources, e.g. of the central processing unit [CPU]

90.

SYSTEM AND METHOD FOR SURFACE CLEANING

      
Application Number US2015013211
Publication Number 2015/126585
Status In Force
Filing Date 2015-01-28
Publication Date 2015-08-27
Owner THE BOEING COMPANY (USA)
Inventor Ponomarev, Sergey

Abstract

A system for cleaning (10) an object (18) may include a cleaning medium dispenser (22) configured to deliver a cleaning medium (26) to a surface (16) of the object, wherein the cleaning medium dislodges and captures debris from the surface, an ultrasonic device (20) configured to deliver ultrasonic waves (28) to the object, wherein the ultrasonic waves generate ultrasonic vibrations in the object to atomize the cleaning medium from the surface and a vacuum (24) configured to provide a vacuum airflow, wherein the vacuum airflow collects atomized cleaning medium and debris from the surface.

IPC Classes  ?

  • B08B 3/12 - Cleaning involving contact with liquid with additional treatment of the liquid or of the object being cleaned, e.g. by heat, by electricity, by vibration by sonic or ultrasonic vibrations
  • B08B 7/02 - Cleaning by methods not provided for in a single other subclass or a single group in this subclass by distortion, beating, or vibration of the surface to be cleaned

91.

AIRCRAFT FUSELAGE CONSTRUCTED OF AIRCRAFT FUSELAGE SECTIONS SCREWED TOGETHER

      
Application Number US2014061824
Publication Number 2015/122939
Status In Force
Filing Date 2014-10-22
Publication Date 2015-08-20
Owner THE BOEING COMPANY (USA)
Inventor Guerquin, Kris G.

Abstract

An aircraft fuselage is constructed of a plurality of cylindrical semi-monocoque fuselage sections that are each constructed with mirrored screw threads on either their interior or exterior surfaces. The screw threads of adjacent fuselage sections are secured together end-to-end by a sleeve having complementary screw threads. The sleeve is positioned between adjacent fuselage sections that are held against rotation, but are free to move in translation towards each other. The sleeve is engaged with the screw threads of the adjacent fuselage sections and is rotated, causing the adjacent fuselage sections to move toward each other and into secure engagement in response to the rotating sleeve.

IPC Classes  ?

  • B29C 65/56 - Joining of preformed parts; Apparatus therefor using mechanical means
  • B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for

92.

FIBER-REINFORCED RESIN COMPOSITES AND METHODS OF MAKING THE SAME

      
Application Number US2014061818
Publication Number 2015/119676
Status In Force
Filing Date 2014-10-22
Publication Date 2015-08-13
Owner THE BOEING COMPANY (USA)
Inventor
  • Schneider, Terrence Lee
  • Christensen, Stephen
  • Gosse, Jonathan Henry

Abstract

A fiber-reinforced resin composite and method of making the same. The fiberreinforced resin composite includes a polymeric resin matrix and a plurality of fibers coated with a first distortional polymeric resin. The polymeric resin matrix has a first von Mises strain. The first distortional polymeric resin has a second von Mises strain in a range of approximately 0.25 to approximately 0.45. The plurality of fibers coated with the first distortional polymeric resin are disposed in the polymeric resin matrix. The second von Mises strain is greater than the first von Mises strain.

IPC Classes  ?

  • C08J 5/06 - Reinforcing macromolecular compounds with loose or coherent fibrous material using pretreated fibrous materials
  • C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
  • C08L 63/00 - Compositions of epoxy resins; Compositions of derivatives of epoxy resins

93.

METHOD AND SYSTEM FOR SECURELY ESTABLISHING CRYPTOGRAPHIC KEYS FOR AIRCRAFT-TO-AIRCRAFT COMMUNICATIONS

      
Application Number US2014064399
Publication Number 2015/119679
Status In Force
Filing Date 2014-11-06
Publication Date 2015-08-13
Owner THE BOEING COMPANY (USA)
Inventor Sampigethaya, Radhakrishna G.

Abstract

A method and system for encrypting communications between two aircraft on the ground at an airport. Each aircraft is coupled to a ground network via a broadband over power line communications (BPL) network, which may be provided via the respective ground power connectors for each aircraft. A mutually authenticated communications channel is established between each aircraft via the ground network. A shared pairwise key is established at each aircraft. The shared pairwise key may be separately established based upon channel state characteristics such as channel attenuation, bandwidth or delay. In the alternative, the shared pairwise key may be shared from one aircraft to the other or may be generated from public keys based upon a predetermined protocol such as Diffie Hellman. Data encrypted using the shared pairwise key may then be transmitted from one aircraft to the other aircraft. The encrypted data may be transmitted via the PBL network or a separate wireless network.

IPC Classes  ?

  • H04L 29/06 - Communication control; Communication processing characterised by a protocol
  • H04L 9/08 - Key distribution
  • H04B 3/54 - Systems for transmission via power distribution lines

94.

AUTOMATED MOBILE BOOM SYSTEM FOR CRAWLING ROBOTS

      
Application Number US2014062338
Publication Number 2015/119677
Status In Force
Filing Date 2014-10-27
Publication Date 2015-08-13
Owner THE BOEING COMPANY (USA)
Inventor
  • Troy, James J.
  • Lea, Scott W.
  • Georgeson, Gary E.
  • Nelson, Karl E.
  • Wright, Daniel J.

Abstract

A system comprising a multi-functional boom subsystem integrated with a holonomic-motion boom base platform. The boom base platform may comprise: Mecanum wheels with independently controlled motors; a pair of sub-platforms coupled by a roll-axis pivot to maintain four-wheel contact with the ground surface; and twist reduction mechanisms to minimize any yaw-axis twisting torque exerted on the roll-axis pivot. A computer with motion control software may be embedded on the boom base platform. The motion control function can be integrated with a real-time tracking system. The motion control computer may have multiple platform motion control modes: (1) a path following mode in which the boom base platform matches the motion path of the surface crawler (i.e., integration with crawler control); (2) a reactive mode in which the boom base platform moves based on the pan and tilt angles of the boom arm; and (3) a collision avoidance mode using sensors distributed around the perimeter of the boom base platform to detect obstacles

IPC Classes  ?

  • B66C 13/48 - Automatic control of crane drives for producing a single or repeated working cycle; Programme control
  • B66C 23/72 - Counterweights or supports for balancing lifting couples
  • G01N 29/00 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object

95.

REMOVAL OF IDLE TIME IN VIRTUAL MACHINE OPERATION

      
Application Number US2014064618
Publication Number 2015/119682
Status In Force
Filing Date 2014-11-07
Publication Date 2015-08-13
Owner THE BOEING COMPANY (USA)
Inventor
  • Hotra, Jonathan N.
  • Esrig, Jerry A.

Abstract

A computer system 100 for providing virtualization services may execute computer programs 122 by a virtual processor 118 in a virtual machine 114. The computer programs 122 may be executed as tasks 206 scheduled for execution at respective points in an apparent time tracked by an apparent-time reference. During execution of the computer programs 122, the computer system 100 may detect a current point in apparent time at which all tasks scheduled for repeated execution at a given frequency have been executed, or at which the virtual processor 118 is idle. And in response, the computer system 100 may advance the apparent time to a subsequent point with a frequency greater than that with which the apparent time is tracked by the apparent-time reference.

IPC Classes  ?

  • G06F 9/455 - Emulation; Interpretation; Software simulation, e.g. virtualisation or emulation of application or operating system execution engines
  • G06F 9/48 - Program initiating; Program switching, e.g. by interrupt

96.

ESTABLISHING AVAILABILITY OF A TWO-ENGINE AIRCRAFT FOR AN ETOPS FLIGHT

      
Application Number US2015010428
Publication Number 2015/119733
Status In Force
Filing Date 2015-01-07
Publication Date 2015-08-13
Owner THE BOEING COMPANY (USA)
Inventor Heinzerling, Daryl W.

Abstract

A method is provided for establishing availability of a two-engine aircraft for a predefined ETOPS flight 100. The method may include calculating a probability of a dual independent engine shutdown sequence1608 for each of a climb phase 106, a plurality of cruise 110, 114 phases including an ETOPS phase 112, and a descent phase 108 into which the predefined ETOPS flight 100 is divisible. The shutdown sequence may be composed of events 400, 500, 600, 700, 800 that for each phase may include events having respective, conditional probabilities specific to a model of the two-engine aircraft, product of which is the probability of the shutdown sequence for the respective phase. The method may include calculating the risk of the shutdown sequence 1610 as a function of a sum of the probabilities for the phases, and establishing availability of the aircraft based on the risk and a preexisting baseline. A similar method is provided for establishing availability of an ETOPS flight 100 path.

IPC Classes  ?

  • G01C 21/20 - Instruments for performing navigational calculations

97.

WIRELESSLY CONNECTING AN AIRCRAFT AT AN AIRPORT

      
Application Number US2014062940
Publication Number 2015/116263
Status In Force
Filing Date 2014-10-29
Publication Date 2015-08-06
Owner THE BOEING COMPANY (USA)
Inventor Shi, Fong

Abstract

Disclosed are ways for wirelessly connecting an aircraft at an airport. For example, a method for wirelessly communicating with an aircraft may include determining a proximity of an aircraft of a directional antenna system for wireless communication, determining availability of the directional antenna system for wireless communication with the aircraft, selecting the directional antenna system based on the determined proximity and availability, and providing instructions for the directional antenna system to communicate with the aircraft.

IPC Classes  ?

  • H04B 7/06 - Diversity systems; Multi-antenna systems, i.e. transmission or reception using multiple antennas using two or more spaced independent antennas at the transmitting station
  • H04B 7/08 - Diversity systems; Multi-antenna systems, i.e. transmission or reception using multiple antennas using two or more spaced independent antennas at the receiving station
  • H04B 7/04 - Diversity systems; Multi-antenna systems, i.e. transmission or reception using multiple antennas using two or more spaced independent antennas
  • H04B 7/185 - Space-based or airborne stations

98.

AUGMENTED SITUATION AWARENESS

      
Application Number US2014061735
Publication Number 2015/108590
Status In Force
Filing Date 2014-10-22
Publication Date 2015-07-23
Owner THE BOEING COMPANY (USA)
Inventor
  • Kinderman, Merian
  • Puentes, Antonio
  • Kneuper, Nils
  • Lutz, Andre

Abstract

Methods and systems for augmenting situational awareness using a controllable window are described. An environmental condition within a field of view of the controllable window is determined. Light transmissivity of the controllable window is selectively changed based on the determined environmental condition. In some implementations, multiple points of view can be provided to multiple viewers

IPC Classes  ?

  • B64C 1/14 - Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens
  • B64D 43/00 - Arrangements or adaptations of instruments

99.

ELECTRONIC GAGE APPARATUS

      
Application Number US2014052229
Publication Number 2015/105532
Status In Force
Filing Date 2014-08-22
Publication Date 2015-07-16
Owner THE BOEING COMPANY (USA)
Inventor
  • Bumgardner, Mark, D.
  • Schweiger, Jonathan, A.
  • Gorsh, Christopher, M.

Abstract

A gage apparatus includes a probe, a processor, and a memory. The probe includes a plurality of transmitters and a plurality of receivers both aligned in an axial direction along the probe. The processor is in electronic communication with the plurality of transmitters and the plurality of receivers. The memory is in electronic communication with the processor. The memory includes programming code for execution by the processor. The programming code is configured to determine a length of a structure disposed adjacent to the probe based on which of the plurality of receivers receive signals transmitted by the plurality of transmitters and reflected off the structure.

IPC Classes  ?

  • G01B 11/02 - Measuring arrangements characterised by the use of optical means for measuring length, width, or thickness
  • G01B 11/22 - Measuring arrangements characterised by the use of optical means for measuring depth
  • G01D 5/34 - Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable using optical means, i.e. using infra-red, visible or ultra-violet light with attenuation or whole or partial obturation of beams of light the beams of light being detected by photocells

100.

SYSTEMS AND METHODS FOR CREATING ALTERED ADHESIVE BONDS

      
Application Number US2014055572
Publication Number 2015/105538
Status In Force
Filing Date 2014-09-15
Publication Date 2015-07-16
Owner THE BOEING COMPANY (USA)
Inventor
  • Slocum, Allan Joshua
  • Watson, Megan Nicole
  • Baldwin, Joel P.
  • Dan-Jumbo, Eugene A.
  • Evens, Michael W.
  • Greene, Kelly M.
  • Keller, Russell Lee
  • Spalding, John F.

Abstract

Disclosed are systems and methods of creating altered adhesive bonded joints between metal or composite substrates, including bonds that are weaker in strength than selected reference bonds. One method of creating an altered adhesive bond includes providing a first substrate and a second substrate, selecting a manufacturing process having a plurality of steps designed to produce a desired, or reference, adhesive bond having a desired strength, and selectively altering at least one of the plurality of steps during performance of the manufacturing process to produce an altered bond between the first substrate and the second substrate, the altered bond having an altered strength that is weaker than the strength of the desired adhesive bond. The systems may include systems that may be utilized to create the altered adhesive bonds and/or test standards.

IPC Classes  ?

  • G01N 19/04 - Measuring adhesive force between materials, e.g. of sealing tape, of coating
  • C09J 7/02 - on carriers
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