Abstract

The disclosed embodiments relate to a method for repairing a damage to a thermoplastic composite element, in particular an aircraft component, wherein a socket is milled at the site of damage to the thermoplastic composite element. Then, in the socket a patch is formed from a thermosetting material containing a reinforcing phase of fabric layers and a matrix of thermosetting resin, the patch having a shape and size corresponding to the socket geometry. In the next step, the patch is cured, and finally the cured patch is glued into the socket by means of an adhesive.

IPC Classes  ?

• B29C 73/10 - 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 using preformed elements using patches sealing on the surface of the article
• B29C 37/00 - Component parts, details, accessories or auxiliary operations, not covered by group or

Abstract

A method of fabricating a composite structure includes laying at least one composite ply about a bladder, the bladder comprising a phase change material in a first phase having a first volume, positioning an outer mold about the bladder and the at least one composite ply, and curing the at least one composite ply to form the composite structure. Curing causes the phase change material contained within the bladder to change to a second phase to expand from the first volume to a second volume and apply a pressure to an interior surface of the composite ply and press an outer surface of the composite ply against the outer mold to form an interior cavity. The bladder is not removable from the formed interior cavity.

IPC Classes  ?

• B29C 33/00 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor
• B29C 70/34 - 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 and shaping or impregnating by compression
• B29C 43/36 - Moulds for making articles of definite length, i.e. discrete articles
• B29C 44/18 - Filling preformed cavities
• B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
• B29C 33/50 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling elastic

Abstract

A method of forming a balanced rotor blade assembly includes measuring a weight of a plurality of sub-components of the rotor blade assembly excluding a core. A configuration of a core of the rotor blade assembly is determined. In combination, the core and the plurality of sub-components achieve a target weight distribution and moment. The core is then fabricated and assembled with the plurality of sub-components to form a rotor blade sub-assembly.

IPC Classes  ?

• B64C 27/00 - Rotorcraft; Rotors peculiar thereto
• F03D 13/35 - Balancing static or dynamic imbalances
• F04D 29/66 - Combating cavitation, whirls, noise, vibration, or the like; Balancing
• F01D 5/02 - Blade-carrying members, e.g. rotors
• G01M 1/36 - Compensating unbalance by adjusting position of masses built-in the body to be tested
• G01M 1/14 - Determining unbalance
• F16F 15/34 - Fastening arrangements therefor
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 50/00 - Data acquisition or data processing for additive manufacturing
• B33Y 80/00 - Products made by additive manufacturing
• B29C 64/386 - Data acquisition or data processing for additive manufacturing
• B64C 27/473 - Constructional features

Abstract

An implant (1) for electric resistance welding of elements made of composites, with a frame made of thermoplastic materials, in particular reinforced with conductive fibres, in the form of a flat multilayered structure which has an upper and a lower surface, and comprising the following layers: an electrically resistant layer (2), which has the form of a flat sheet with openings, made of a conductive material, at least two additional layers made of the frame material (4), one of which covers the electrically resistant layer (2) from the top, and the other one from the bottom. The implant (1) additionally comprises at least two porous insulating layers (3) made of an electrically nonconductive material, one of which covers the implant (1) from the top, contacting the upper layer of the frame material (4), and the other one covers the implant (1) from the bottom, contacting the lower layer of the frame material (4). The implant (1) is characterised in that said layers (2, 3, 4) are merged with each other in the form of a flat, multilayered inset for placing between the welded elements (5), and in that the electrically resistant layer (2) has at least two electrical connections for connecting a source of electrical current. The invention also comprises a method of welding using the implant (1) according to the invention.

IPC Classes  ?

• B29C 65/34 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement"
• B29K 101/12 - Thermoplastic materials
• B29K 71/00 - Use of polyethers as moulding material
• B29K 81/00 - Use of polymers having sulfur, with or without nitrogen, oxygen or carbon only, in the main chain, as moulding material
• B29K 105/06 - Condition, form or state of moulded material containing reinforcements, fillers or inserts
• B29K 307/04 - Carbon

Goods & Services

Passenger ships; Space vehicles; Airships; Light aircraft; Monocoque structures for vehicles; Fuselages [aircraft parts]; Structural parts for aircraft; Aeronautical apparatus, machines and appliances; Automotive vehicles; Coachwork for motor vehicles; Body panels for vehicles. Repair, servicing and maintenance of vehicles and apparatus for locomotion by air; Motor vehicle maintenance and repair; Airplane maintenance and repair; Aeroplane repair; Maintenance and repair of chassis parts and bodies for vehicles; Airplane maintenance and repair; Maintenance and repair of spacecraft; Maintenance and repair of engines; Repairing construction works; Maintenance and repair services relating to the air transport industry. Airline transport; Aircraft handling; Arranging of flights; Vehicle rental; Aircraft rental. Blacksmithing; Treating [forging] of metal; Treating [embossing] of metal; Stamping [pressing]; Laminating; Powder coating; Application of protective surface coatings to machines and tools; Application of wear-resistant coatings on metals and plastics; Metal treating; Treatment of metal parts to prevent corrosion; Custom manufacture of tools for others; Custom manufacture of aircraft composite constructions. Occupationally orientated instruction relating to airports; Provision of training courses; Provision of training courses. Design of vehicles and vehicle parts and components; Engineering design and consultancy; Product research and development; Research and development of new products; Engineering services; Technical research; Technological engineering analysis; Technical data analysis services; Technical consultation in the field of aerospace engineering; Design of instruments; Research laboratories.

Abstract

Impact dissipating helmet liners (10, 110) and protective barriers (90) having internal cylindrical posts or pins (22, 97) are provided. The helmet liners (10) and protective barriers (90) include a flexible, fluid impermeable enclosure (12, 93) having an upper wall (14 94), an opposing lower wall (16, 96), and a sidewall (18) extending between the upper wall and the lower wall; a fluid (20, 98) contained in the enclosure; and cylindrical posts or pins (22, 97) extending from the lower wall to the upper wall, each of the cylindrical posts or pins at least partially restraining deflection of one of the upper wall and the lower wall. The helmet liners (10, 110) provided may include a central portion (44) and lobes (36, 38, 40, 42) radially extending from the central portion and are adapted to conform to the shape of a helmet shell.

IPC Classes  ?

• A42B 3/12 - Cushioning devices

Abstract

A method of determining structural health of an assembly includes determining a Margin of Safety (MSH) value for at least one of a plurality of components in the assembly when the assembly is healthy. The method includes determining if damage to the assembly has occurred. If damage to the assembly has occurred, the method includes determining a Margin of Safety (MSD) value for at least one of the plurality of components in the assembly when the assembly is damaged. The method includes determining a Structural Health Index (SHI) of the assembly based on the MSD value for the at least one undamaged component.

IPC Classes  ?

• G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for

Abstract

A method of mounting a replacement tip section to an exposed end of a rotor blade includes removing an existing tip section from the rotor blade to create the exposed end of the rotor blade, installing the rotor blade having the exposed end onto a holding fixture, assembling the replacement tip section about the exposed end of the rotor blade, positioning a bonding fixture about the replacement tip section, and curing the replacement tip section to the exposed end of the rotor blade.

IPC Classes  ?

• B64C 27/46 - Blades
• B29C 65/78 - Means for handling the parts to be joined, e.g. for making containers or hollow articles
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B29C 65/00 - Joining of preformed parts; Apparatus therefor

Abstract

The invention relates to a method of manufacturing composite components, consisting in laying plurality of sets (S) of unidirectional tapes (T) by automated tape or fiber laying technology. The essence of the method consists in that the unidirectional layers (1, 2, 3, 4) with the same orientation of tapes (T) or fibers are being laid with a lateral shift between said unidirectional layers (1, 2, 3, 4) so that the individual tapes (T) or fibers of at least two unidirectional layers (1, 2, 3, 4) with the same orientation are shifted relative to each other by the value (x) defined by the section running in the direction perpendicular to the tape or fiber laying direction and parallel to the plane of symmetry (P), wherein the value (x) is different than the multiple of the width of a single tape (T) or fiber.

IPC Classes  ?

• B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns

Abstract

The invention relates to a method for repairing a damage to a thermoplastic composite element, in particular an aircraft component, wherein a socket (14) is milled at the site of damage to the thermoplastic composite element (10). Then, in said socket a patch is formed from a thermosetting material containing a reinforcing phase of fabric layers and a matrix of thermosetting resin, said patch having a shape and size corresponding to the socket (14) geometry. In the next step, the patch is cured, and finally the cured patch (13) is glued into the socket (14) by means of an adhesive (9).

IPC Classes  ?

• B29C 73/10 - 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 using preformed elements using patches sealing on the surface of the article
• B29C 37/00 - Component parts, details, accessories or auxiliary operations, not covered by group or
• B29C 73/12 - Apparatus therefor, e.g. for applying
• B29C 73/26 - Apparatus or accessories not otherwise provided for for mechanical pretreatment

Abstract

Headgear, helmets, and related protective equipment having friction reducing interface elements are provided. The headgear (10, 50, 200) includes a helmet shell (12, 52, 202) having external surface and an internal surface; a headgear liner (16, 56, 206) shaped and adapted to be received by the helmet shell, the head gear liner having an external surface positioned to contact the internal surface of the helmet shell; and at least one interface element (22, 62, 78, 204) positioned between the external surface of the headgear liner and the internal surface of the helmet shell. The at least one interface element (22, 62, 78, 204) provides at least some reduction in friction between the external surface of the headgear liner and the internal surface of the helmet shell. The headgear liner may comprise a fluid-filled headgear liner. The interface elements may provide surfaces at multiple elevations.

IPC Classes  ?

• A42B 3/12 - Cushioning devices
• A42B 3/14 - Suspension devices
• A42B 3/06 - Impact-absorbing shells, e.g. of crash helmets

Abstract

A vibration control assembly for an aircraft including a housing operatively coupled to the aircraft. Also included is a cage disposed within an interior region of the housing, the cage rotatable within the housing about a first axis. Further included is a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis, wherein a controllable moment is imposed on the aircraft upon rotation of the gyroscope wheel to counter vibratory moments produced by the vehicle.

IPC Classes  ?

• B64C 27/00 - Rotorcraft; Rotors peculiar thereto
• F16F 1/00 - Springs
• F16F 15/02 - Suppression of vibrations of non-rotating, e.g. reciprocating, systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating system

Goods & Services

Aircraft, helicopters

Abstract

A system for regenerating fastener holes in a replacement tip section of a rotor blade includes a first fixture, a second fixture, and a third fixture positionable adjacent a tip section of the rotor blade. The first fixture is used to verify a position of an opening formed in the spar. The second fixture includes a removable bushing having a drillable opening. The drillable opening is aligned with the at least one opening formed in the spar and defines at least one hole to be formed in the replacement tip section. The third fixture includes a countersink opening. The countersink opening is aligned with the at least one hole to be formed in the replacement tip section and the at least one opening formed in the spar to define a countersink feature to be formed in the at least one hole.

IPC Classes  ?

• B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
• B64C 27/473 - Constructional features
• B64F 5/40 - Maintaining or repairing aircraft
• B23B 35/00 - Methods for boring or drilling, or for working essentially requiring the use of boring or drilling machines; Use of auxiliary equipment in connection with such methods
• B23P 6/00 - Restoring or reconditioning objects
• B23B 47/28 - Drill jigs for workpieces
• B64C 27/46 - Blades

Abstract

A method of fabricating a composite structure includes laying at least one composite ply about a bladder, the bladder comprising a phase change material in a first phase having a first volume, positioning an outer mold about the bladder and the at least one composite ply, and curing the at least one composite ply to form the composite structure. Curing causes the phase change material contained within the bladder to change to a second phase to expand from the first volume to a second volume and apply a pressure to an interior surface of the composite ply and press an outer surface of the composite ply against the outer mold to form an interior cavity. The bladder is not removable from the formed interior cavity.

IPC Classes  ?

• B29C 33/00 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor
• B29C 70/34 - 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 and shaping or impregnating by compression
• B29C 43/36 - Moulds for making articles of definite length, i.e. discrete articles
• B29C 44/18 - Filling preformed cavities
• B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
• B29C 33/50 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling elastic

Abstract

A bond fixture includes a support structure and a first assembly coupled to the support structure. The first assembly includes a frame defining a chamber and a first pressure pad and second pressure pad coupled to the frame opposite one another and positioned within the chamber. The second pressure pad is movable to control a pressure applied by the first pressure pad and the second pressure pad.

IPC Classes  ?

• B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
• B64C 27/46 - Blades
• B64F 5/40 - Maintaining or repairing aircraft

Abstract

A bond fixture includes a first frame defining a chamber configured to receive a leading edge of a rotor blade and a second frame pivotally coupled to the first frame. The second frame is movable between a first position and a second position. In the second position, the second frame restricts movement of the bond fixture relative to the rotor blade. At least one supporting assembly extends from the first frame towards the chamber. The at least one supporting assembly is adjustable to apply a pressure to an adjacent surface of the rotor blade.

IPC Classes  ?

• B64C 27/473 - Constructional features
• B64D 15/00 - De-icing or preventing icing on exterior surfaces of aircraft
• B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
• B64F 5/40 - Maintaining or repairing aircraft
• B23K 37/04 - Auxiliary devices or processes, not specially adapted to a procedure covered by only one of the other main groups of this subclass for holding or positioning work

Abstract

Impact-dissipating liners (10, 116, 316), helmets (60, 111, 310) having an impact-dissipating liner, helmet liner retainers (114), and methods of protecting the head from impact are provided. The liners (10, 116, 316) include fluid impermeable enclosures (26, 28, 30, 32, 34, 142) having internal cavities, and a fluid (14) contained in the enclosures. The enclosures are in fluid communication via passages comprising a restriction (50) between the internal cavities of the enclosures that may restrict flow of the fluid between the enclosures. The helmet liner retainers (114) include a head strap (118) and at least one projection (124, 126, 128, 130) extending from the head strap sized to engage at least one recess (134, 136, 138, 140) in a headgear liner to retain the headgear liner. Though applicable to a broad range of protective headgear, the liners and liner retainers disclosed are uniquely adapted for use in construction helmets, that is, "hard hats."

IPC Classes  ?

• A42B 3/12 - Cushioning devices
• A42B 3/14 - Suspension devices

Abstract

Surface treatment devices (10, 40, 70) having a flexible, fluid impermeable enclosure (12, 42, 72) made of a synthetic amorphous silica; and a polydimethlysiloxane fluid (14, 44, 74) contained in the enclosure. The synthetic amorphous silica may be a liquid silicone rubber, for example, s CHT True Skin liquid silicone rubber. The polydimethlysiloxane fluid may be a CHT QM Diluent. The treatment device may be used for heating or cooling a surface, for example, the surface of the human body. The liquid silicone rubber may be a CHT True Skin 10 liquid silicone rubber, and the CHT QM Diluent may be a low viscosity CHT QM Diluent, for example, a CHT QM Diluent having a viscosity of at least 50 centipoise (cps), or at least 1,000 cps. Methods for treating a surface and methods for fabricating a surface treating device are also provided.

IPC Classes  ?

• A61F 7/00 - Heating or cooling appliances for medical or therapeutic treatment of the human body
• A61F 7/02 - Compresses or poultices for effecting heating or cooling
• A61F 7/08 - Warming pads, pans or mats; Hot-water bottles

Abstract

A unitary core panel for a composite sandwich structure includes a plurality of cell walls defining a plurality of core cells, the plurality of cell walls extending across a thickness of the core, the plurality of core cells including one or more defined structural nonuniformities resulting in nonuniform properties of the core panel. A method of forming a core panel for a composite sandwich structure includes determining structural requirements of the core panel, designing the core panel to satisfy the structural requirements with one or more local nonuniformities in the core panel, and manufacturing the core panel as a unitary core panel with the one or more local nonuniformities.

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
• B29D 24/00 - Producing articles with hollow walls

Abstract

A pressure tool for rotor blade repair including a mobile support system including a support surface, a first bladder support assembly including a first inflatable bladder fixedly mounted to the support surface, a second bladder support assembly including a second inflatable bladder pivotally mounted relative to the support surface, and an activation mechanism operatively coupled to the second bladder support assembly. The activation mechanism is operable to selectively shift the second bladder support assembly relative to the first bladder support assembly. A fluid delivery system is operable to direct a fluid into each of the first inflatable bladder and the second inflatable bladder.

IPC Classes  ?

• B23P 6/00 - Restoring or reconditioning objects
• F01D 5/00 - Blades; Blade-carrying members; Heating, heat-insulating, cooling, or antivibration means on the blades or the members
• B29C 73/10 - 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 using preformed elements using patches sealing on the surface of the article
• B29C 73/30 - Apparatus or accessories not otherwise provided for for local pressing or local heating
• F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing

Abstract

According to one aspect, a lubricant level sensing system for an actuator is provided. The lubricant level sensing system includes a pressure port in an outer housing of the actuator, a pressure sensor, and a pathway from the pressure port to the pressure sensor. The pathway establishes fluid communication between the pressure sensor and a free volume of an internal cavity of the outer housing relative to a lubricant level in the internal cavity such that the pressure sensor detects a pressure of the free volume used to derive the lubricant level.

IPC Classes  ?

• F16N 29/00 - Special means in lubricating arrangements or systems providing for the indication or detection of undesired conditions; Use of devices responsive to conditions in lubricating arrangements or systems
• B64C 27/615 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including flaps mounted on blades
• B64C 27/72 - Means acting on blades
• G01F 23/16 - Indicating, recording, or alarm devices being actuated by mechanical or fluid means, e.g. using gas, mercury, or a diaphragm as transmitting element, or by a column of liquid

Abstract

A method of bonding a blade cuff to a rotor blade includes installing the blade cuff to a root end of the rotor blade. The method includes mounting the rotor blade within a plurality of supports. The method includes coupling the blade cuff to a first fixture. The method includes installing a second fixture about the blade cuff. The method further includes applying localized and constant heat and pressure to the blade cuff via the second fixture.

IPC Classes  ?

• B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
• B23P 15/04 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
• B23P 6/00 - Restoring or reconditioning objects
• B64C 27/473 - Constructional features
• B23Q 3/06 - Work-clamping means
• B23Q 3/00 - Devices holding, supporting, or positioning, work or tools, of a kind normally removable from the machine
• B64C 27/48 - Root attachment to rotor head

Abstract

An assembly for removing a bushing is provided including a mandrel having a size and shape similar to the bushing and a receiver having a hollow interior cavity. A fastener extends through an opening formed in both the mandrel and the receiver. A socket attachment has a first opening configured to removably couple to a first end of the fastener and a second opening configured to removably couple to a torque delivery tool. A biasing mechanism arranged adjacent a second end of the fastener is configured to generate a biasing force to drive the mandrel against a bushing in response to a coupling of the socket attachment and the fastener.

IPC Classes  ?

• 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
• B25B 27/06 - 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 for connecting objects by press fit or detaching same inserting or withdrawing sleeves or bearing races
• B64F 5/40 - Maintaining or repairing aircraft
• B64C 27/06 - Helicopters with single rotor

Abstract

A fastener health monitoring system includes a structure including a first component and a second component, one or more fasteners securing the first component to the second component, and an optical fiber arranged adjacent to the one or more fasteners. The fiber is configured to detect strain on the structure from the one or more fasteners. Strain patterns are derivable from sensed data from the optical fiber, and any deviation in strain value greater than a threshold value at a particular fiber position along the optical fiber is indicative of a missing, damaged, or loosened fastener amongst the one or more of fasteners corresponding to that particular fiber position.

IPC Classes  ?

• G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings
• G01L 1/24 - Measuring force or stress, in general by measuring variations of optical properties of material when it is stressed, e.g. by photoelastic stress analysis

Abstract

A portable computerized device for an aircraft control system includes an input system for inputting commands, a device display for displaying information on the computerized device, a processor, a wireless communication module, and a non-transitory computer readable medium comprising computer executable instructions, the computer executable instructions configured to cause the processor to perform a method. The method can include detecting whether the portable computerized device is in a cockpit state such that the portable computerized device is in and/or docked to an aircraft cockpit or if the portable computerized device is in a remote state such that the portable computerized device is not in an aircraft cockpit or is not docked to an aircraft cockpit. If the portable computerized device is determined to be in a remote state, the method includes operating the remote device in a remote mode. If the portable computerized device is determined to be in a cockpit state, the method includes operating the device in a local mode.

IPC Classes  ?

• G05D 1/00 - Control of position, course, altitude, or attitude of land, water, air, or space vehicles, e.g. automatic pilot
• B64C 39/02 - Aircraft not otherwise provided for characterised by special use
• B64D 43/00 - Arrangements or adaptations of instruments
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• G08G 5/00 - Traffic control systems for aircraft

Abstract

A vibration control assembly for an aircraft includes a housing operatively coupled to the aircraft. Also included is a cage disposed within an interior region of the housing, the cage rotatable within the housing about a first axis. Further included is a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis, wherein a controllable moment is imposed on the aircraft upon rotation of the gyroscope wheel to counter vibratory moments produced by the vehicle. Yet further included is a control assembly at least partially surrounding the gyroscope wheel for controlling the controllable moment. The control assembly includes a structure having an inner surface, a track disposed along the inner surface, and an arm operatively coupled to the gyroscope wheel, the arm having an end disposed within the track, the gyroscope wheel angularly displaceable upon translation of the arm along the track.

IPC Classes  ?

• B64C 17/06 - Aircraft stabilisation not otherwise provided for by gravity or inertia-actuated apparatus by gyroscopic apparatus
• B64C 27/00 - Rotorcraft; Rotors peculiar thereto
• B64C 27/04 - Helicopters

Abstract

An aircraft includes an airframe, an extending tail, a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, and a translational thrust system positioned at the extending tail. The translational thrust system provides translational thrust to the airframe. An upper hub fairing is positioned at the upper rotor assembly. A lower hub fairing is positioned at the lower rotor assembly. A shaft fairing is disposed between the upper hub fairing and the lower hub fairing. The upper hub fairing is substantially sealed to the shaft fairing and the lower hub fairing is substantially sealed to the shaft fairing.

IPC Classes  ?

• B64C 27/10 - Helicopters with two or more rotors arranged coaxially
• B64C 7/00 - Structures or fairings not otherwise provided for

Abstract

A computer-implemented method and system for controlling an aircraft based on detecting and mitigating fatiguing conditions and aircraft damage conditions is disclosed. According to one example, a computer-implemented method includes detecting, by a processing system, a health condition of a component of the aircraft. The method further includes determining, by the processing system, whether the health condition is one of a fatigue condition or a damage condition. The method further includes implementing, by the processing system, a first action based at least in part on determining that the health condition is a fatigue condition to mitigate the fatigue condition. The method further includes implementing, by the processing system, a second action based at least in part on determining that the health condition is a damage condition to mitigate the damage condition.

IPC Classes  ?

• B64C 13/50 - Transmitting means with power amplification using electrical energy
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• B64D 31/06 - Initiating means actuated automatically
• B64C 13/16 - Initiating means actuated automatically, e.g. responsive to gust detectors

Abstract

Impact-dissipating liners (10, 140, 150), helmets (355) having an impact-dissipating liner, and methods of fabricating impact-dissipating liners are provided. The liners include a fluid impermeable enclosure (11, 141, 151) having cavities (17, 147, 157) with sidewalls, re-enforcing fabric sheets (20, 120, 222), and a fluid (24, 242) contained in the enclosure. The enclosure (11, 141, 151) may have a central portion (236) and lobes (228, 230, 232, 234) extending from the central portion, wherein the central portion and the lobes are adapted to conform to the shape of an internal surface of a helmet. The re-enforcing sheets (20, 120, 222) may be made from a broad materials and may enhance the structural support, structural integrity, and/or durability to the liner. Aspects of the invention are adapted for use as head protection; however, aspects of the invention can be adapted to provide impact-dissipation for any body part or surface.

IPC Classes  ?

• A42B 3/12 - Cushioning devices
• A41D 13/015 - Professional, industrial or sporting protective garments, e.g. surgeons' gowns or garments protecting against blows or punches with shock-absorbing means
• A42C 2/00 - Manufacturing helmets by processes not otherwise provided for
• B29C 39/10 - Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor for making articles of definite length, i.e. discrete articles incorporating preformed parts or layers, e.g. casting around inserts or for coating articles

Abstract

An impact dissipating helmet liner (10) comprising: a flexible, fluid impermeable enclosure ( 11) having an upper wall ( 12), an opposing lower wall (14 ), and a sidewall ( 18 ) extending between the upper wall and the lower wall; a fluid ( 24 ) contained in the enclosure (11 ); and a fabric sheet ( 20 ) positioned in at least one of the upper wall and the lower wall.

IPC Classes  ?

• A42B 3/12 - Cushioning devices
• A41D 13/015 - Professional, industrial or sporting protective garments, e.g. surgeons' gowns or garments protecting against blows or punches with shock-absorbing means
• B29C 39/10 - Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor for making articles of definite length, i.e. discrete articles incorporating preformed parts or layers, e.g. casting around inserts or for coating articles
• A42C 2/00 - Manufacturing helmets by processes not otherwise provided for

Abstract

A method of constructing a mandrel generally complementary to a spar cavity of a spar includes connecting a first component and a second component to form a central space there between and inserting a center component within the central space such that the center component retains the first component and second component in a desired position forming an outer surface of the mandrel which corresponds to an inner surface of the spar cavity.

IPC Classes  ?

• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B64C 27/473 - Constructional features
• B29C 70/32 - 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 on a rotating mould, former or core
• B29C 53/82 - Cores or mandrels
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
• B29C 53/42 - Bending and joining, e.g. for making hollow articles by bending sheets or strips at right angles to the longitudinal axis of the article being formed and joining the edges for articles of definite length, i.e. discrete articles using internal forming surfaces, e.g. mandrels
• B29C 33/48 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling
• 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
• B29C 70/34 - 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 and shaping or impregnating by compression
• B29C 45/44 - Removing or ejecting moulded articles for undercut articles
• B29C 65/56 - Joining of preformed parts; Apparatus therefor using mechanical means
• B29C 65/76 - Making non-permanent or releasable joints
• B32B 1/08 - Tubular products
• B32B 37/10 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using direct action of vacuum or fluid pressure

Abstract

A bond assembly includes a fixture having a first section movably coupled to a second section. The first section and the second section are disposed opposite one another. A bladder assembly is mounted to at least one of the first section and the second section. The bladder assembly is configured to apply controlled, localized pressure and heat to a component receivable between the first section and the second section.

IPC Classes  ?

• 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
• B64C 27/32 - Rotors
• B64C 27/46 - Blades
• B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
• B64F 5/40 - Maintaining or repairing aircraft
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
• B32B 37/10 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using direct action of vacuum or fluid pressure
• B32B 37/06 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method

Abstract

A method for securing an engine using an adjustable mounting assembly is provided including adjusting an extendible element of the adjustable mounted assembly from a first position to a second position. Another extendible element of the adjustable mounting assembly is adjusted from a third position to a fourth position. The engine is mounted using the adjustable mounted assembly with the extendible element in the second position and another extendible element in the fourth position.

IPC Classes  ?

• B64D 27/26 - Aircraft characterised by construction of power-plant mounting
• B64D 27/14 - Aircraft characterised by the type or position of power plant of gas-turbine type within, or attached to, fuselage
• B64D 41/00 - Power installations for auxiliary purposes

Abstract

A gear box includes a casing having an interior. A rotating component is arranged in the interior of the casing. A bearing including a rotating element, and a fixed element is connected with the casing in the interior. A submersible pump is arranged in the interior of the casing. The submersible pump includes a first housing portion extending about the rotating component fixedly mounted to the casing at the interior. A second housing portion is fixedly mounted to the casing at the interior and is aligned with the first housing portion. The first and second housing portions form a lubricant reservoir which holds lubricant. An impeller is mounted to the rotating component and arranged in the lubricant reservoir. One of the first and second housing portions includes an outlet through which the pumped lubricant is directed toward the rotating element.

IPC Classes  ?

• F16H 57/04 - Features relating to lubrication or cooling
• F16N 7/36 - Arrangements for supplying oil or unspecified lubricant from a stationary reservoir or the equivalent in or on the machine or member to be lubricated with feed by pumping action of the member to be lubricated or of a shaft of the machine; Centrifugal lubrication
• B64C 27/78 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement in association with pitch adjustment of blades of anti-torque rotor
• B64D 35/04 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
• B64C 27/14 - Direct drive between power plant and rotor hub
• B64C 27/82 - Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft

Abstract

A method for providing adaptive control to a fly-by-wire aircraft includes measuring via at least one first sensor a characteristic of at least one component of the aircraft and measuring via at least one second sensor a state of the aircraft. Using the characteristic of at least one component and the state of the aircraft, a determination of at least one of an actual damage and remaining life of the at least one component is made. The operational envelope of the aircraft is adapted based on the at least one of actual damage and remaining life of the at least one component. Adapting the operational envelope includes adjusting an outer boundary thereof to prohibit operation exceeding a safe operation threshold and generating an intermediate boundary of the operational envelope. Operation of the aircraft within the intermediate boundaries minimizes further damage accrual of the at least one component.

IPC Classes  ?

• G05D 1/00 - Control of position, course, altitude, or attitude of land, water, air, or space vehicles, e.g. automatic pilot
• B64C 13/50 - Transmitting means with power amplification using electrical energy
• B64F 5/60 - Testing or inspecting aircraft components or systems
• B64D 43/00 - Arrangements or adaptations of instruments
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• G05D 1/10 - Simultaneous control of position or course in three dimensions

Abstract

A method of making bearings includes treating a metallic surface of a bearing raceway with a pulsed electrochemical processing nozzle to transform the amorphous oxide into a crystalline structure on the metallic surface electro-chemically and convert the metallic surface into a ceramic like hardness surface. Treating the metallic surface can include forming a gradient in material composition transitioning from a purely metallic material at a cross-sectional position within the bearing raceway to a purely crystalline structure material at the ceramic like hardness surface of the bearing raceway.

IPC Classes  ?

• F16C 33/62 - Selection of substances
• F16C 33/64 - Special methods of manufacture
• F16C 19/16 - Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with a single row of balls
• C25D 11/02 - Anodisation
• F16C 19/06 - Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for radial load mainly with a single row of balls
• F16C 33/30 - Parts of ball or roller bearings

Abstract

A method of mounting a replacement tip section to an exposed end of a rotor blade includes removing an existing tip section from the rotor blade to create the exposed end of the rotor blade, installing the rotor blade having the exposed end onto a holding fixture, assembling the replacement tip section about the exposed end of the rotor blade, positioning a bonding fixture about the replacement tip section, and curing the replacement tip section to the exposed end of the rotor blade.

IPC Classes  ?

• B29C 65/78 - Means for handling the parts to be joined, e.g. for making containers or hollow articles
• B29C 65/00 - Joining of preformed parts; Apparatus therefor
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
• B64C 27/46 - Blades
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B64C 27/473 - Constructional features

Abstract

A system for regenerating fastener holes in a replacement tip section of a rotor blade includes a first fixture, a second fixture, and a third fixture positionable adjacent a tip section of the rotor blade. The first fixture is used to verify a position of an opening formed in the spar. The second fixture includes a removable bushing having a drillable opening. The drillable opening is aligned with the at least one opening formed in the spar and defines at least one hole to be formed in the replacement tip section. The third fixture includes a countersink opening. The countersink opening is aligned with the at least one hole to be formed in the replacement tip section and the at least one opening formed in the spar to define a countersink feature to be formed in the at least one hole.

IPC Classes  ?

• B64F 5/40 - Maintaining or repairing aircraft
• B23P 6/00 - Restoring or reconditioning objects
• B23B 35/00 - Methods for boring or drilling, or for working essentially requiring the use of boring or drilling machines; Use of auxiliary equipment in connection with such methods
• B64C 27/46 - Blades
• B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor

Abstract

An aircraft is provided including at least one pilot input and a flight control system n communication with the at least one pilot input. The flight control system is operable in a manual mode and a pointing mode. In the manual mode, a velocity, position, and attitude of the aircraft are controlled manually, and in the pointing mode, at least one of the velocity and position of the aircraft is controlled by the flight control system and at least one of the attitude and heading of the aircraft is controlled manually.

IPC Classes  ?

• B64C 27/57 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
• B64D 43/02 - Arrangements or adaptations of instruments for indicating aircraft speed or stalling conditions

Abstract

A method of manufacturing a part is provided. The method includes heating a gear in the presence of carbon to carburize a material of the gear to create a carburized gear, the gear having a plurality of gear teeth and which comprises a selected material. Next, the carburized gear is high pressure gas quenched to drive the carbon into the material of the gear to create a quenched gear. Next, the quenched gear is at least one of cavitation peened and laser peened to create a peened gear. Finally, superfinishing is performed on surfaces of the peened gear.

IPC Classes  ?

• C21D 1/06 - Surface hardening
• C21D 7/06 - Modifying the physical properties of iron or steel by deformation by cold working of the surface by shot-peening or the like
• C21D 9/32 - Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for gear wheels, worm wheels, or the like
• F16H 55/06 - Use of materials; Use of treatments of toothed members or worms to affect their intrinsic material properties
• C23C 8/80 - After-treatment
• C23C 8/22 - Carburising of ferrous surfaces
• C23C 8/20 - Carburising

Abstract

An exhaust system for an engine includes an exhaust nozzle located adjacent an outlet end of the engine to receive a primary flow of exhaust gasses expelled from the engine, an inlet opening formed between the exhaust nozzle and the outlet end of the engine through which a secondary flow is provided to the exhaust nozzle, and a vortex generator arranged within the exhaust system at a position where both the primary flow and the secondary flow are present. The vortex generator interrupts at least one of the primary flow and the secondary flow.

IPC Classes  ?

• F02K 1/46 - Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
• F01D 9/02 - Nozzles; Nozzle boxes; Stator blades; Guide conduits

Abstract

A pitch control system configured to vary a pitch angle of at least one of a plurality of propeller blades of a propeller system is provided including a switch movable between a neutral position and a plurality of non-neutral positions. Movement of the switch to a first non-neutral position generates a command to move the propeller blades in a first direction. Movement of the switch to a second non-neutral position generates a command to move the propeller blades in a second direction. Movement of the switch to a third non-neutral position generates a command to move the propeller blades to a zero thrust position.

IPC Classes  ?

• B64C 27/57 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
• B64C 11/30 - Blade pitch-changing mechanisms
• B64C 27/82 - Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
• B64C 11/34 - Blade pitch-changing mechanisms mechanical automatic
• B64C 27/56 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated
• B64C 11/40 - Blade pitch-changing mechanisms fluid, e.g. hydraulic automatic

Abstract

A hybrid gear includes a first portion having a plurality of first engagement features formed from a first material and having a first stiffness and a second portion having a plurality of second engagement features in intermeshing arrangement with the plurality of first engagement features. The plurality of second engagement features is formed from a second material distinct from the first material and having a second stiffness. The first stiffness of the plurality of first engagement features is within 20% of the second stiffness of the plurality of second engagement features.

IPC Classes  ?

• F16H 55/17 - Toothed wheels
• F16H 55/06 - Use of materials; Use of treatments of toothed members or worms to affect their intrinsic material properties
• F16H 55/14 - Construction providing resilience or vibration-damping
• B64D 35/00 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions

Abstract

A control valve for a multi-stage hydraulic actuator includes a valve body defining a translation axis, a spool disposed within the valve body and movable along the translation axis, and a flange. The flange is fixed relative to the spool and has an aperture disposed externally of the valve body to removably fix the spool to a spool of a redundant control valve independently connected to the multi-stage hydraulic actuator for mitigating force fights between actuators coupled to the control valve.

IPC Classes  ?

• F16K 11/16 - Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves; Arrangement of valves and flow lines specially adapted for mixing fluid with two or more closure members not moving as a unit operated by one actuating member, e.g. a handle which only slides, or only turns, or only swings in one plane
• B64C 27/64 - Transmitting means, e.g. interrelated with initiating means or means acting on blades using fluid pressure, e.g. having fluid power amplification
• B64C 13/42 - Transmitting means with power amplification using fluid pressure having duplication or stand-by provisions
• B64C 27/605 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms
• F16K 31/08 - Operating means; Releasing devices magnetic using a magnet using a permanent magnet

Abstract

A bond fixture includes a frame that defines a chamber for receiving a component. At least one bladder assembly is mounted to the frame and extends into the chamber to apply a pressure to an adjacent surface of the component. A caul assembly is positionable about the component and receivable within the chamber. The caul assembly heats a localized portion of the component.

IPC Classes  ?

• B21D 53/78 - Making other particular articles turbine blades
• B29C 65/02 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure
• B64F 5/40 - Maintaining or repairing aircraft
• B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
• B64C 27/473 - Constructional features
• B29C 73/24 - Apparatus or accessories not otherwise provided for

Abstract

An aircraft rotor system includes a rotating pitch change shaft which rotates about an axis, a translating element disposed within the rotating pitch change shaft and movable along the axis and a pitch change bearing assembly which transfers movement of the translating element to the pitch change shaft. The pitch change bearing assembly includes a primary bearing and a secondary bearing coupled to the rotating pitch change shaft via the translating element when the primary bearing is in a first mode. A thrust shoulder is coupled to the translating element. The thrust shoulder is movable into engagement with the secondary bearing in response to failure of the primary bearing such that in a second mode, movement of the translating element is primarily transferred to the pitch change shaft via the secondary bearing.

IPC Classes  ?

• B64C 27/59 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
• B64C 11/06 - Blade mountings for variable-pitch blades
• B64C 27/78 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement in association with pitch adjustment of blades of anti-torque rotor
• F16C 19/54 - Systems consisting of a plurality of bearings with rolling friction
• F16C 19/52 - Bearings with rolling contact, for exclusively rotary movement with devices affected by abnormal or undesired conditions
• F16C 39/02 - Relieving load on bearings using mechanical means

Abstract

A holding fixture includes a first blade support assembly and a second blade support assembly. The second blade support assembly is spaced at a distance from the first blade support assembly and includes a base plate removably mounted to a milling machine, an adjustable conic support connectable to the base plate via a spacer block, and a blade adjustment assembly movable to control a pressure applied by the blade adjustment assembly.

IPC Classes  ?

• B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
• B23Q 3/06 - Work-clamping means
• B32B 43/00 - Operations specially adapted for layered products and not otherwise provided for, e.g. repairing; Apparatus therefor

Abstract

A bond fixture includes a frame defining a chamber for receiving a component. At least one bladder assembly is connected to the frame. The at least one bladder assembly includes a pad for contacting the component. A position of the pad relative to the component is controlled by a pressure of the bladder assembly. A caul assembly is adapted to thermally couple to the component to heat a localized portion of the component.

IPC Classes  ?

• B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
• B64F 5/40 - Maintaining or repairing aircraft
• B64C 27/46 - Blades
• B29C 73/24 - Apparatus or accessories not otherwise provided for

Abstract

A computer-implemented method and system for transmitting power and data together in a rotorcraft using a slip ring assembly is disclosed. According to one example, a computer-implemented method includes providing a slip ring assembly comprising a stationary element coupled to an airframe of a rotorcraft and a rotatable element rotatable relative to the stationary element and coupled to a rotor assembly of the rotorcraft. Power is transmitted from a power source associated with the airframe to an electronic device associated with the rotor assembly, the slip ring assembly being configured to complete an electrical circuit between the power source and the electronic device to provide power from the power source to the electronic device. Data is transmitted from a first data transceiver associated with the airframe to a second data transceiver associated with the rotor assembly via the electrical circuit completed by the slip ring assembly.

IPC Classes  ?

• B60R 16/03 - Electric or fluid circuits specially adapted for vehicles and not otherwise provided for; Arrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric for supply of electrical power to vehicle subsystems
• H01R 39/08 - Slip-rings
• H01R 39/34 - Connections of conductor to slip-ring
• B64C 27/32 - Rotors
• H02K 13/00 - Structural associations of current collectors with motors or generators, e.g. brush mounting plates or connections to windings; Disposition of current collectors in motors or generators; Arrangements for improving commutation
• B64C 27/04 - Helicopters
• H01R 39/18 - Contacts for co-operation with commutator or slip-ring, e.g. contact brush

Abstract

A method of fabricating a composite structure includes laying at least one composite ply about a bladder, the bladder comprising a phase change material in a first phase having a first volume, positioning an outer mold about the bladder and the at least one composite ply, and curing the at least one composite ply to form the composite structure. Curing causes the phase change material contained within the bladder to change to a second phase to expand from the first volume to a second volume and apply a pressure to an interior surface of the composite ply and press an outer surface of the composite ply against the outer mold to form an interior cavity. The bladder is not removable from the formed interior cavity.

IPC Classes  ?

• B29C 70/34 - 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 and shaping or impregnating by compression
• B29C 33/00 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor
• B29C 43/36 - Moulds for making articles of definite length, i.e. discrete articles
• B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
• B29C 33/50 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling elastic

Abstract

One aspect is a flight control system for a rotary wing aircraft that includes flight control computer configured to interface with a main rotor system, a translational thrust system, and an engine control system. The flight control computer includes processing circuitry configured to execute control logic. The control logic includes a primary flight control configured to produce flight control commands for the main rotor system and the translational thrust system. A main engine anticipation logic is configured to produce a rotor power demand associated with the main rotor system. A propulsor loads engine anticipation logic is configured to produce an auxiliary propulsor power demand associated with the translational thrust system. The flight control computer providing the engine control system with a total power demand anticipation signal based on a combination of the rotor power demand and the auxiliary propulsor power demand.

IPC Classes  ?

• B64D 31/06 - Initiating means actuated automatically
• B64C 27/22 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
• B64C 11/30 - Blade pitch-changing mechanisms
• B64C 27/10 - Helicopters with two or more rotors arranged coaxially
• B64C 27/82 - Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
• B64D 35/00 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
• B64C 27/57 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust

Abstract

An aircraft rotor blade assembly includes a rotor blade rotatable about an axis of rotation and a weighted assembly mounted to the aircraft rotor blade. The weighted assembly includes an actuator which moves a mass to adjust a moment of the rotor blade assembly when the rotor blade is rotated about the axis of rotation.

IPC Classes  ?

• B64C 27/00 - Rotorcraft; Rotors peculiar thereto
• B64C 27/473 - Constructional features

Abstract

A method of determining how to repair a damaged composite component includes generating a three-dimensional model of the damaged component, determining a configuration of a repair structure to be applied to the damaged component using the generated three-dimensional model and general design data for the component prior to being damaged, determining an operational feasibility of the determined repair structure using application specific information related to the damaged component and generating a repair procedure for forming the repair structure when the determined operational feasibility indicates that the damaged component can be successfully repaired.

IPC Classes  ?

• G05B 19/4099 - Surface or curve machining, making 3D objects, e.g. desktop manufacturing
• B64F 5/40 - Maintaining or repairing aircraft

Abstract

An actuator system for an aircraft includes an actuator, and a control valve system operatively connected to the actuator. The control valve system includes a first direct drive valve (DDV) mechanically connected to a second DDV. A backup valve system is operatively connected to the actuator. The backup valve system includes one of an electro-hydraulic servovalve (EHSV) and a DDV.

IPC Classes  ?

• F15B 20/00 - Safety arrangements for fluid actuator systems; Applications of safety devices in fluid actuator systems; Emergency measures for fluid actuator systems

Abstract

An aircraft and a method of operating an aircraft. The aircraft includes a processor and an interface for receiving an input from an operator. The processor is configured to calculate an expected state of the aircraft for a selected flight plan of the aircraft, display the expected state for the flight plan, alter the expected state in response to the input from an operator, and operate the aircraft according to the altered state.

IPC Classes  ?

• 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 or acceleration
• G01S 13/94 - Radar or analogous systems, specially adapted for specific applications for terrain-avoidance
• G05D 1/00 - Control of position, course, altitude, or attitude of land, water, air, or space vehicles, e.g. automatic pilot

Abstract

An assembly configured to prevent damage to an object during manufacture thereof is provided including a first housing having a substantially hollow interior. An exposed first planar surface of the first housing includes an inlet port and a plurality of small openings formed about the periphery. The inlet port, the hollow interior, and the plurality of small openings form a fluid flow path through the assembly. A second housing similar in size and shape to the first housing, has an exposed second planar surface. An intermediate layer is arranged between the first housing and the second housing. A cross-section of the intermediate layer is configured to change shape in response to a compression force applied thereto by the first housing and the second housing to form a seal separating an exterior portion of the objection exposed to the plurality of small openings from an interior surface of the object.

IPC Classes  ?

• B64F 5/40 - Maintaining or repairing aircraft
• B64C 27/473 - Constructional features
• B24C 3/00 - Abrasive blasting machines or devices; Plants
• B64C 27/467 - Aerodynamic features
• B64F 5/30 - Cleaning aircraft

Abstract

A rotor system includes a rotor hub, a plurality of rotor blades supported by the rotor hub, and a fairing mounted to the rotor hub. The fairing includes an external surface exposed to an external airflow and an internal surface defining an interior portion. One or more heat generating components are arranged in the interior portion. A cooling system is arranged in the interior portion. The cooling system includes a first heat exchanger thermally connected to each of the one or more heat generating components, a second heat exchanger mounted to the fairing, and at least one fluid conduit extending therebetween so as to remove heat generated by each of the one or more heat generating components.

IPC Classes  ?

• B64C 27/10 - Helicopters with two or more rotors arranged coaxially
• F28D 15/02 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes
• B64C 27/72 - Means acting on blades
• B64C 27/59 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
• B64D 29/00 - Power-plant nacelles, fairings, or cowlings
• B64C 27/58 - Transmitting means, e.g. interrelated with initiating means or means acting on blades
• B64C 27/04 - Helicopters
• B64C 7/00 - Structures or fairings not otherwise provided for
• F28D 21/00 - Heat-exchange apparatus not covered by any of the groups

Abstract

A water separator (108) includes a tube (112) defining a longitudinal axis, wherein the tube (112) includes a tube wall separating an interior (114) of the tube from an exterior (116) thereof. A tube insert (118) is mounted within the tube (112). The tube insert (118) includes a sheet (119) that is helically twisted about the longitudinal axis. An environmental control system (100) includes an air conditioner (102) with a discharge duct (104) for providing cooled air to an air conditioned space. A water separator (108) as described above is connected in line with the discharge duct (104) for passage of cooled air therethrough.

IPC Classes  ?

• B01D 45/00 - Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces
• B01D 45/16 - Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces by centrifugal forces generated by the winding course of the gas stream
• B01D 53/26 - Drying gases or vapours
• B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
• B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
• B04C 5/103 - Bodies or members, e.g. bulkheads, guides, in the vortex chamber
• F22B 37/32 - Steam-separating arrangements using centrifugal force

Abstract

In accordance with at least one aspect of this disclosure, a structure can include a body, and one or more thermal sheet sensors disposed on or within the body. The one or more thermal sheet sensors can be configured to receive heat from the body to allow sensing of thermal flux through the body to monitor and/or determine a condition of the structure.

IPC Classes  ?

• G01N 25/72 - Investigating presence of flaws
• G01K 17/00 - Measuring quantity of heat
• G01K 1/00 - MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR - Details of thermometers not specially adapted for particular types of thermometer
• B64F 5/60 - Testing or inspecting aircraft components or systems
• B64C 27/46 - Blades
• G01K 1/14 - Supports; Fastening devices; Arrangements for mounting thermometers in particular locations
• G01K 11/12 - Measuring temperature based on physical or chemical changes not covered by group , , , or using changes in colour, translucency or reflectance

Abstract

A flexible coupling includes a first disc and a second disc arranged along a rotation axis. The first disc and the second disc each include a radially inner hub portion, a radially outer rim portion, and a diaphragm portion extending between the hub portion and the rim portion. The first disc rim portion is connected to the second disc rim portion and the first disc has a diametral response mode that is different than a diametral response mode of the second disc to limit deformation in the flexible coupling when communicating rotation between a drive member and a driven member connected to one another by the flexible coupling. Drive trains and methods of making flexible couplings are also described.

IPC Classes  ?

• F16D 3/72 - Yielding couplings, i.e. with means permitting movement between the connected parts during the drive with the coupling parts connected by one or more intermediate members with axially-spaced attachments to the coupling parts
• B64D 35/00 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions

Abstract

An aircraft tail rotor system includes a rotating pitch change shaft, a translating element, and a pitch change bearing assembly including a first bearing and a second bearing. The pitch change bearing assembly is operable to transmit movement of the translating element to the rotating pitch change shaft via the first bearing or the second bearing. A failure section is formed at an interface between the first bearing and the translating element. When the failure section decouples the first bearing from the translating element such that the first bearing does not transmit movement of the translating element to the rotating pitch change shaft, the second bearing transmits movement of the translating element to the rotating pitch change shaft.

IPC Classes  ?

• B64C 27/58 - Transmitting means, e.g. interrelated with initiating means or means acting on blades
• F16C 19/49 - Bearings with both balls and rollers
• B64C 27/82 - Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft

Abstract

An axial preloading device can include a shell having an inner surface that defines a radially interior channel, the inner channel defining an axial direction, one or more moveable housing members disposed at least partially within the interior channel and configured to move relative to the shell in the axial direction, and a wedge assembly connected to the shell and disposed in contact with the one or more housing members. The wedge assembly can be configured to be moved radially relative to the shell and the one or more housing members to push the one or more housing members axially. The wedge assembly and the one or more housing members define a shaft opening when installed on the shell.

IPC Classes  ?

• F16B 2/14 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening using wedges
• F16B 7/18 - Connections of rods or tubes, e.g. of non-circular section, mutually, including resilient connections using screw-thread elements

Abstract

A hoisting system for hoisting a load relative to a body includes a hoisting cable, a hoisting mechanism selectively operable to deploy and retract the hoisting cable, and a guide mechanism movably mounted to the body at a position between the body and the hoisting cable. The guide mechanism includes at least one locking device that selectively locks the guide mechanism against movement in a first direction.

IPC Classes  ?

• B66D 3/26 - Other details, e.g. housings
• B64D 1/22 - Taking-up articles from earth's surface
• B66D 1/36 - Guiding, or otherwise ensuring winding in an orderly manner, of ropes, cables, or chains

Abstract

A solid lubricant-carrying gear which is lubricated by a liquid lubricant communicated to the gear by a primary lubrication system includes a gear body and a solid lubricant body. The gear body is arranged along a rotation axis and has a first surface, an axially opposite second surface, and an outward radial face extending about the rotation axis having gear teeth and lubricant directing features. The solid lubricant body is coupled to the gear body and includes a lubricant which melts at a melting temperature above that of the liquid lubricant to provide secondary lubrication to the gear via the lubricant directing features. Gearboxes, aircraft having transmissions employing solid lubricant-carrying gears, and methods of lubricating gears are also described.

IPC Classes  ?

• F16H 1/06 - Toothed gearings for conveying rotary motion without gears having orbital motion involving only two intermeshing members with parallel axes
• F16H 55/17 - Toothed wheels
• F16H 57/04 - Features relating to lubrication or cooling

Abstract

A method of retrofitting a gear box assembly with an emergency lubrication system includes removing plugs from visual inspection ports of a gearbox housing, removing a breather from a breather port of the gearbox housing, and installing jet plugs into the respective visual inspection ports and breather port, wherein each jet plug includes a respective jet tube.

IPC Classes  ?

• F16H 57/04 - Features relating to lubrication or cooling
• F16H 57/027 - Gearboxes; Mounting gearing therein characterised by means for venting gearboxes, e.g. air breathers
• F16H 57/02 - Gearboxes; Mounting gearing therein
• B64C 27/14 - Direct drive between power plant and rotor hub
• B64C 27/12 - Rotor drives

Abstract

A gearbox assembly having a driven assembly includes a drive hub having gear posts, the drive hub being rotatable about an axis. The gearbox assembly additionally includes a plurality of planetary gears and an intermediate component coupling one of the plurality of planetary gears to a corresponding gear post. The intermediate component has sufficient flexibility to maintain the planetary gears in meshing engagement with the driven assembly within the gearbox assembly when one of the planetary gears is misaligned with the corresponding gear post.

IPC Classes  ?

• F16H 1/28 - Toothed gearings for conveying rotary motion with gears having orbital motion
• F16H 57/08 - General details of gearing of gearings with members having orbital motion
• B64C 27/14 - Direct drive between power plant and rotor hub
• F16H 57/12 - Arrangements for adjusting or for taking-up backlash not provided for elsewhere
• F16H 57/021 - Shaft support structures, e.g. partition walls, bearing eyes, casing walls or covers with bearings
• F16H 57/04 - Features relating to lubrication or cooling

Abstract

An active vibration control system for an aircraft includes a gearbox operably coupling a power source and a component rotatable about an axis. The gearbox includes a flexible region which allows flexure between a first stage and a second stage. At least one active vibration control actuator is arranged in vibrational communication with the flexible region to counteract vibrations transmitted between the power source and the rotatable component.

IPC Classes  ?

• B64C 27/00 - Rotorcraft; Rotors peculiar thereto
• F16H 57/028 - Gearboxes; Mounting gearing therein characterised by means for reducing vibration or noise

Abstract

A landing assembly and method of landing an aircraft. The landing assembly includes a landing gear, a charging circuit, a sampling circuit and a processor. The charging circuit applies a charge to the landing gear and the sampling circuit measures a discharge rate of the electrical charge from the landing gear. The processor determines a contact between the landing gear and a surface from the discharge rate.

IPC Classes  ?

• B64D 45/04 - Landing aids; Safety measures to prevent collision with earth's surface
• B64C 25/36 - Arrangements or adaptations of wheels, tyres or axles in general
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• B64C 25/32 - Alighting gear characterised by elements which contact the ground or similar surface

Abstract

A bond fixture for bonding a component includes a frame defining a chamber for receiving the component. A first pad and a second pad are mounted to the frame. At least one of the first pad and the second pad is movable relative to the frame to adjust a pressure applied to the component. A caul assembly is adapted to be disposed in thermal communication with the component. The caul assembly heats a localized portion of the component.

IPC Classes  ?

• B64C 27/46 - Blades
• B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
• B64F 5/40 - Maintaining or repairing aircraft
• B29C 73/24 - Apparatus or accessories not otherwise provided for

Abstract

A bond fixture includes a first fixture having a heater and a plurality of clamps. Each of the plurality of clamps includes a first member and a second member rotatable between a first position and a second position. A second fixture includes a root end lift translatable vertically between a retracted position and an extended position and a root end clamp translatable along a horizontal axis. The root end clamp is configured to cooperate with the root end.

IPC Classes  ?

• B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
• B64C 27/473 - Constructional features
• B29C 73/24 - Apparatus or accessories not otherwise provided for

Abstract

A rotor system of an aircraft includes a rotor hub rotatable about an axis of rotation, and a power generation system. The power generation system includes a generator stator and a generator rotor. The generator rotor is coupled to the rotor hub. At least one induction type magnet is mounted to at least one of the generator stator and the generator rotor. A control unit is operably coupled to the at least one induction type magnet to selectively deliver power to the at least one induction type magnet to alter a torque of the rotor hub without decreasing a rotational speed of the rotor hub.

IPC Classes  ?

• B64C 27/14 - Direct drive between power plant and rotor hub
• B64C 27/32 - Rotors
• H02K 7/14 - Structural association with mechanical loads, e.g. with hand-held machine tools or fans
• B64D 35/02 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the type of power plant
• B64C 27/10 - Helicopters with two or more rotors arranged coaxially

Abstract

A method of manufacturing a gear, the method includes applying a first charge to a workpiece and applying a second, opposite charge to an electrochemical machining (ECM) attachment, the ECM attachment having a pattern. The method further includes simultaneously forming a plurality of surfaces of a gear tooth in the workpiece using the pattern of the ECM attachment while applying the first charge to the workpiece and applying the second charge to the ECM attachment and turning the workpiece and the ECM attachment in opposite rotational directions. The plurality of surfaces includes at least one end face and a top land of the gear tooth.

IPC Classes  ?

• B23H 3/04 - Electrodes specially adapted therefor or their manufacture
• B23H 9/00 - Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects
• B23H 11/00 - Auxiliary apparatus or details, not otherwise provided for
• B23F 17/00 - Special methods or machines for making gear teeth, not covered by groups
• B23H 5/08 - Electrolytic grinding
• B23H 7/26 - Apparatus for moving or positioning electrode relatively to workpiece; Mounting of electrode

Abstract

A spherical bearing which extends from and connects to a deformable component includes an outer member and an inner member. The inner member is pivotable relative to the outer member about an axis. The inner member has an opening formed therein that defines a plurality of coplanar contact surfaces shaped to accommodate and contact the component. The plurality of contact surfaces are movable to accommodate deformation of the component positioned within the opening.

IPC Classes  ?

• F16C 25/04 - Sliding-contact bearings self-adjusting
• F16C 23/04 - Sliding-contact bearings self-adjusting
• B64C 27/32 - Rotors
• B64C 27/605 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms
• F16C 27/02 - Sliding-contact bearings
• B64C 27/12 - Rotor drives

Abstract

A gear train includes a first gear having teeth meshed with teeth of a second gear. Each tooth of the first gear includes a coast side and a drive side opposed to the coast side. The drive side has a pressure angle that is greater than that of the coast side. The gear train can be part of a powertrain system for a rotorcraft, and can replace a traditional gear train in a retrofit or new build. The first gear is a planet gear and the second gear is a ring gear wherein the planet gear and ring gear are in a planetary gear train configuration.

IPC Classes  ?

• F16H 55/08 - Profiling
• B64D 35/00 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
• F16H 57/08 - General details of gearing of gearings with members having orbital motion
• B64C 27/14 - Direct drive between power plant and rotor hub
• B64C 27/06 - Helicopters with single rotor
• B64C 27/12 - Rotor drives
• F16H 1/28 - Toothed gearings for conveying rotary motion with gears having orbital motion
• F16H 57/01 - Monitoring wear or stress of gearing elements, e.g. for triggering maintenance
• F16H 57/00 - General details of gearing

Abstract

A retractable landing gear system for a vertical takeoff and landing (VTOL) aircraft includes a rotational strut rotatably coupled to a fuselage of the VTOL aircraft. The rotational strut includes a first end, a second end, and an intermediate portion extending therebetween. A drag strut includes a first end portion pivotally connected to the rotational strut and a second end portion. A locking link includes a first end section pivotally connected relative to the fuselage, a second end section pivotally connected to the drag strut and an intermediate section having a hinge element. A retraction system is operatively connected to the rotational strut and the locking link. The retraction system is operable to pivot the drag strut about a first axis and rotate the rotational strut about a second axis that is distinct from the first axis.

IPC Classes  ?

• B64C 25/20 - Operating mechanisms mechanical
• B64C 25/12 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
• B64C 25/26 - Control or locking systems therefor
• B64C 25/32 - Alighting gear characterised by elements which contact the ground or similar surface

Abstract

A corrosion management method is provided and includes storing an asset fleet at a location, generating a corrosion rate stressor by reference to models for any component of an asset of the asset fleet corresponding to the location and storage practice of the asset, predicting an accumulated corrosion stressor severity from the generated corrosion rate stressor, measuring an actual corrosion rate stressor at the location and revising the models in accordance with a difference between the predicted accumulated corrosion stressor severity and the measured actual corrosion rate stressor.

IPC Classes  ?

• G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
• B64F 5/60 - Testing or inspecting aircraft components or systems
• G01N 17/00 - Investigating resistance of materials to the weather, to corrosion or to light
• G07C 5/00 - Registering or indicating the working of vehicles
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for

Abstract

A gearbox includes a housing including a lubricant reservoir, at least one gear system arranged in the housing, at least one lubricant delivery passage operable to direct a flow of lubricant from a lubricant reservoir onto the at least one gear system, at least one lubricant return passage operable to guide the flow of lubricant to the lubricant reservoir, and a lubricant-out sensor fluidically connected to the at least one lubricant return passage. The lubricant-out sensor is operable to detect a non-pressure based parameter of the lubricant.

IPC Classes  ?

• F16N 29/02 - Special means in lubricating arrangements or systems providing for the indication or detection of undesired conditions; Use of devices responsive to conditions in lubricating arrangements or systems for influencing the supply of lubricant
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• F16H 57/04 - Features relating to lubrication or cooling
• F16N 29/04 - Special means in lubricating arrangements or systems providing for the indication or detection of undesired conditions; Use of devices responsive to conditions in lubricating arrangements or systems enabling moving parts to be stopped
• B64C 27/14 - Direct drive between power plant and rotor hub
• F16N 29/00 - Special means in lubricating arrangements or systems providing for the indication or detection of undesired conditions; Use of devices responsive to conditions in lubricating arrangements or systems
• F16N 7/00 - Arrangements for supplying oil or unspecified lubricant from a stationary reservoir or the equivalent in or on the machine or member to be lubricated
• B64C 27/16 - Drive of rotors by means, e.g. propellers, mounted on rotor blades
• G01N 33/28 - Oils
• G01F 23/22 - Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water
• G01F 23/24 - Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water by measuring variations of resistance of resistors due to contact with conductor fluid

Abstract

An aircraft includes an airframe having an aircraft longitudinal axis and a main rotor system supported by the airframe. The main rotor system is rotatable about an axis of rotation. The airframe is tiltable relative to a ground surface to form a non-zero tilt angle between the aircraft longitudinal axis and the ground surface.

IPC Classes  ?

• G05D 1/00 - Control of position, course, altitude, or attitude of land, water, air, or space vehicles, e.g. automatic pilot
• B64C 25/34 - Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
• B64C 27/10 - Helicopters with two or more rotors arranged coaxially
• B64C 25/00 - Alighting gear
• B64C 25/32 - Alighting gear characterised by elements which contact the ground or similar surface
• B64C 25/08 - Undercarriages non-fixed, e.g. jettisonable

Abstract

A cuff-blade attachment bushing removal tool system includes an alignment plate comprising alignment holes defined through the alignment plate in a pattern of a plurality of bushing holes of a blade root, a bladder plate connected to the alignment plate, and a bladder positioned on the bladder plate such that a gap is formed between the bladder and the alignment plate to receive a blade root to align the alignment holes and the bushing holes of the blade root, wherein the bladder is transitionable between an uninflated position where the blade root can be inserted into the gap and an inflated position where the blade root is clamped between the bladder and the alignment plate.

IPC Classes  ?

• B32B 43/00 - Operations specially adapted for layered products and not otherwise provided for, e.g. repairing; Apparatus therefor
• B25B 27/28 - 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 for assembling objects other than by press fit or detaching same positioning or withdrawing resilient bushings or the like
• C09J 5/06 - Adhesive processes in general; Adhesive processes not provided for elsewhere, e.g. relating to primers involving heating of the applied adhesive
• B25B 5/00 - Clamps
• B25B 5/06 - Arrangements for positively actuating jaws
• B25B 27/06 - 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 for connecting objects by press fit or detaching same inserting or withdrawing sleeves or bearing races
• B32B 38/10 - Removing layers, or parts of layers, mechanically or chemically
• B64F 5/40 - Maintaining or repairing aircraft

Abstract

A rotor blade disassembly method includes applying spanwise support to a rotor blade body and heating a bond disposed on an end of the rotor blade body. The method also includes removing the spanwise support from the rotor blade body and exerting shear stress on the bond using weight of the rotor blade body. A blade disassembly system is also described.

IPC Classes  ?

• B64C 27/46 - Blades
• F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing
• B64C 27/48 - Root attachment to rotor head
• B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
• B64F 5/40 - Maintaining or repairing aircraft
• B25B 27/28 - 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 for assembling objects other than by press fit or detaching same positioning or withdrawing resilient bushings or the like

Abstract

A flow management system for delivering air to a heat load of an aircraft includes a cover having an opening for receiving and directing an airflow, and a duct defining a non-linear fluid flow path. The fluid flow path operably couples the opening and the heat load. A configuration of the fluid flow path reduces a velocity of the airflow therein while minimizing a pressure drop of the airflow.

IPC Classes  ?

• B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
• B64C 7/00 - Structures or fairings not otherwise provided for
• B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
• B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
• B64C 27/04 - Helicopters

Abstract

MSHH MSDD )MSDD D value for the at least one undamaged component.

IPC Classes  ?

• G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings
• G06F 19/00 - Digital computing or data processing equipment or methods, specially adapted for specific applications (specially adapted for specific functions G06F 17/00;data processing systems or methods specially adapted for administrative, commercial, financial, managerial, supervisory or forecasting purposes G06Q;healthcare informatics G16H)
• G06F 17/50 - Computer-aided design

Abstract

An airspeed indicator display for an aircraft having a main rotor system and a translational thrust system includes a first indicator operable to display an actual airspeed of the aircraft and a second indicator positioned adjacent the first indicator. The second indicator is operable to display an actual pitch angle of the translational thrust system.

IPC Classes  ?

• G01D 7/02 - Indicating value of two or more variables simultaneously
• G01L 3/08 - Rotary-transmission dynamometers wherein the torque-transmitting element comprises a torsionally-flexible shaft involving optical means for indicating
• B64C 27/08 - Helicopters with two or more rotors
• B64D 43/02 - Arrangements or adaptations of instruments for indicating aircraft speed or stalling conditions
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• 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 or acceleration
• G05D 1/08 - Control of attitude, i.e. control of roll, pitch, or yaw
• B64C 27/22 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft

Abstract

A torque indicator for an aircraft having a main rotor system and a translational thrust system driven by at least one engine includes a first indicator operable to display an actual torque of an engine of the aircraft relative to an engine torque limit, a second indicator operable to display an actual torque of the translational thrust system of the aircraft relative to a translational thrust system torque limit, and a third indicator operable to display an actual torque of the main rotor system of the aircraft relative to a main rotor system torque limit.

IPC Classes  ?

• G01L 3/08 - Rotary-transmission dynamometers wherein the torque-transmitting element comprises a torsionally-flexible shaft involving optical means for indicating
• B64C 27/00 - Rotorcraft; Rotors peculiar thereto
• B64C 27/08 - Helicopters with two or more rotors
• B64D 43/02 - Arrangements or adaptations of instruments for indicating aircraft speed or stalling conditions
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• 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 or acceleration
• G05D 1/08 - Control of attitude, i.e. control of roll, pitch, or yaw
• B64C 27/22 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft

Abstract

A fastener health monitoring system includes a structure including a first component and a second component, one or more fasteners securing the first component to the second component, and an optical fiber arranged adjacent to the one or more fasteners. The fiber is configured to detect strain on the structure from the one or more fasteners. Strain patterns are derivable from sensed data from the optical fiber, and any deviation in strain value greater than a threshold value at a particular fiber position along the optical fiber is indicative of a missing, damaged, or loosened fastener amongst the one or more of fasteners corresponding to that particular fiber position.

IPC Classes  ?

• G01L 1/24 - Measuring force or stress, in general by measuring variations of optical properties of material when it is stressed, e.g. by photoelastic stress analysis

Abstract

A portable computerized device for an aircraft control system includes an input system for inputting commands, a device display for displaying information on the computerized device, a processor, a wireless communication module, and a non-transitory computer readable medium comprising computer executable instructions, the computer executable instructions configured to cause the processor to perform a method. The method can include detecting whether the portable computerized device is in a cockpit state such that the portable computerized device is in and/or docked to an aircraft cockpit or if the portable computerized device is in a remote state such that the portable computerized device is not in an aircraft cockpit or is not docked to an aircraft cockpit. If the portable computerized device is determined to be in a remote state, the method includes operating the remote device in a remote mode. If the portable computerized device is determined to be in a cockpit state, the method includes operating the device in a local mode.

IPC Classes  ?

• B64D 43/00 - Arrangements or adaptations of instruments
• G06F 3/484 -
• G06F 3/14 - Digital output to display device
• G06F 1/16 - Constructional details or arrangements

Abstract

An integrated inlet particle separator (IPS) blower/engine starter including a housing having an inlet and an outlet. A turbine member is rotatably supported in the housing. A geared member operatively connected to the turbine member extends outward from the housing. The integrated IPS blower/engine starter is operable in a first configuration receiving a first fluid flow to rotate the geared member and in a second configuration generating a fluid flow through powered rotation of the geared member.

IPC Classes  ?

• F02C 7/277 - Mechanical drives the starter being a turbine
• F02C 7/275 - Mechanical drives
• F01D 19/00 - Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
• F02C 7/05 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
• F02C 7/052 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with dust-separation devices
• B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
• F02C 7/26 - Starting; Ignition
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user

Abstract

A computer-implemented method and system for controlling an aircraft based on detecting and mitigating fatiguing conditions and aircraft damage conditions is disclosed. According to one example, a computer-implemented method includes detecting, by a processing system, a health condition of a component of the aircraft. The method further includes determining, by the processing system, whether the health condition is one of a fatigue condition or a damage condition. The method further includes implementing, by the processing system, a first action based at least in part on determining that the health condition is a fatigue condition to mitigate the fatigue condition. The method further includes implementing, by the processing system, a second action based at least in part on determining that the health condition is a damage condition to mitigate the damage condition.

IPC Classes  ?

• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• G01M 17/007 - Wheeled or endless-tracked vehicles
• G06F 17/00 - Digital computing or data processing equipment or methods, specially adapted for specific functions
• H04N 5/33 - Transforming infrared radiation

Abstract

A rotary-wing aircraft and system for flying a rotary-wing aircraft. The aircraft includes a servo system for actuating a rotor of the aircraft. A hydraulic system provides hydraulic power to the servo system, and a sensor measures a parameter of the hydraulic system. A processor determines a condition of the hydraulic system from the parameter and enforces an effective flight envelop based on the condition of the hydraulic system in order to fly the aircraft within the effective flight envelope.

IPC Classes  ?

• G05D 1/00 - Control of position, course, altitude, or attitude of land, water, air, or space vehicles, e.g. automatic pilot
• B64C 27/56 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated
• B64C 27/64 - Transmitting means, e.g. interrelated with initiating means or means acting on blades using fluid pressure, e.g. having fluid power amplification
• B64C 27/57 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
• G05D 1/08 - Control of attitude, i.e. control of roll, pitch, or yaw
• B64C 13/50 - Transmitting means with power amplification using electrical energy

Abstract

A tail rotor blade for a helicopter includes a blade body defining a longitudinally extending spar cavity, a leading edge forward of the spar cavity, and a trailing edge aft of the spar cavity. Upper and lower airfoil surfaces extend from the leading edge to the trailing edge on opposite sides of the spar cavity. The upper and lower airfoil surfaces define between one another a constant airfoil segment and transition airfoil segments disposed longitudinally adjacent to the constant airfoil segment on inboard and outboard sides of the constant airfoil segment.

IPC Classes  ?

• B64C 27/473 - Constructional features
• B64C 27/467 - Aerodynamic features
• B64C 27/04 - Helicopters

Abstract

A computer implemented method for displaying aircraft systems information on an aircraft display relating to and facilitating operation of an aircraft are disclosed herein. The method can include displaying a plurality of system indicators in a system indicator region of an aircraft display. At least two of the indicators of the plurality of system indicators in the system indicator region are disposed in a structurally approximated relationship relative to each other to increase system recognition and/or interpretation of status of a corresponding physical system indicated by each indicator.

IPC Classes  ?

• B64F 5/60 - Testing or inspecting aircraft components or systems
• G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time

Abstract

A replacement vibration absorbing device for replacing a wear wrap on a flexbeam includes a sleeve having a plurality of layers of vibration absorbing material, wherein an edge of the sleeve is cut so that the sleeve may be installed around a generally central portion of a flexbeam.

IPC Classes  ?

• B64F 5/40 - Maintaining or repairing aircraft
• B29C 53/42 - Bending and joining, e.g. for making hollow articles by bending sheets or strips at right angles to the longitudinal axis of the article being formed and joining the edges for articles of definite length, i.e. discrete articles using internal forming surfaces, e.g. mandrels
• B64C 27/33 - Rotors having flexing arms
• B64C 27/51 - Damping of blade movements
• B64C 27/00 - Rotorcraft; Rotors peculiar thereto
• B29C 65/48 - Joining of preformed parts; Apparatus therefor using adhesives
• B29C 65/00 - Joining of preformed parts; Apparatus therefor
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers

Abstract

A structural health monitoring system includes a first component and a second component associated at a joint. At least one sensor is embedded within the joint to monitor a health of at least one of the first component, the second component, and the joint.

IPC Classes  ?

• G01D 5/353 - 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 infrared, visible or ultraviolet light with attenuation or whole or partial obturation of beams of light the beams of light being detected by photocells influencing the transmission properties of an optical fibre
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• B64C 1/12 - Construction or attachment of skin panels
• B64C 1/06 - Frames; Stringers; Longerons
• B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like