Abstract

A gap cover (3) for a device component (1), preferably for a cabin attendant seat, for visually closing a gap (2) relative to a further cabin component (6) in a passenger cabin (7) is provided. The gap cover (3) has at least one covering element (29) composed of flexible material for spanning the gap (2), wherein a frame body, which has a frame base element and a flexible frame element, is arranged on the rear wall (13) of the device component (1), wherein the frame body also contains at least one functionally coupled spring element which is designed to push the flexible frame element into a state which increases the depth of the frame body.

IPC Classes  ?

• B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for
• B64D 11/06 - Arrangements or adaptations of seats

Abstract

The present disclosure relates to an aircraft seat and an aircraft. The aircraft seat includes: a headrest; a backrest; and a seat plate pivotably mounted to the backrest and configured to be pivotable relative to the backrest from a seat plate stowed position to a seat plate expanded position for seating by a user and to be automatically pivotable from the seat plate expanded position to the seat plate stowed position in response to the user's departure. The aircraft seat is further provided with a display configured to displace as the seat plate pivots. The aircraft includes the above aircraft seat. The aircraft seat and the aircraft according to the present disclosure can facilitate the cabin crew to observe the situation in the cabin compartment when sitting on the aircraft seat, and ensure the utilization rate of the compartment space.

IPC Classes  ?

• B64D 11/06 - Arrangements or adaptations of seats
• B64C 1/10 - Bulkheads
• A47C 1/121 - Theatre, auditorium, or similar chairs having tipping-up seats

Abstract

A system for cleaning a waste tank (4) in an aircraft is proposed, comprising a service device, at least one spray nozzle, and a first adaptor (12) for each of the at least one spray nozzle, wherein the service device comprises a descaling fluid tank (14), a service device outlet, a service device inlet and a pump in fluid communication with the service device outlet, wherein the at least one spray nozzle is coupled with the service device outlet or the pump through a first conduit (30), wherein the at least one spray nozzle is adapted for ejecting at least one descaling fluid jet into the waste tank, wherein the service device inlet is coupled with a second conduit (38) attachable to a waste tank outlet, wherein the first adaptor is couplable with the respective spray nozzle and comprises fastening means to attach the first adaptor to an opening of the waste tank in a substantially fluid-tight manner, and wherein the service device is designed to continuously circulate the descaling fluid through the service device outlet, the first conduit, the at least one spray nozzle, the waste tank outlet, the second conduit and the service device inlet.

IPC Classes  ?

• B08B 3/02 - Cleaning by the force of jets or sprays
• B08B 9/08 - Cleaning of containers, e.g. tanks
• B08B 9/093 - Cleaning of containers, e.g. tanks by the force of jets or sprays
• B08B 9/032 - Cleaning the internal surfaces; Removal of blockages by the mechanical action of a moving fluid, e.g. by flushing
• B05B 13/06 - Machines or plants for applying liquids or other fluent materials to surfaces of objects or other work by spraying, not covered by groups specially designed for treating the inside of hollow bodies
• B08B 3/04 - Cleaning involving contact with liquid
• B61D 35/00 - Sanitation
• B64D 11/02 - Toilet fittings
• B08B 3/08 - Cleaning involving contact with liquid the liquid having chemical or dissolving effect

Abstract

A filling level monitoring device (100) for monitoring a filling level (210) of a fluid in a container (200) includes exciter(s) (10), sensor(s) (20), a signal source (30) connected to the exciter(s) (10), a processor (40), at least one spatial orientation and acceleration sensor (60), and a filling level indicator (50). The device (100) uses the signal source (30) and the exciter(s) (10) to couple vibrational loads having multiple frequency components into the container (200). Sensors (20) measure vibrations in the container (200) after the exciters (10) transmit the vibrational loads into the container (200). The processor (40) performs spectral analysis of the input signal (31) and of vibration signals (21) from the sensors (20), comparing these respective spectral functions to extract resonance frequencies of the container (200), which are based on the spatial orientation of the container (200). The filling level indicator (50) calculates a current filling level (210) of the container (200) from the extracted resonance frequencies and a spatial orientation signal from a spatial orientation sensor (60) by correlating the collected data with reference data.

IPC Classes  ?

• G01F 23/296 - Acoustic waves
• B64D 37/04 - Arrangement thereof in or on aircraft
• B64D 37/30 - Fuel systems for specific fuels
• G01F 23/2962 - Measuring transit time of reflected waves
• G01F 23/80 - Arrangements for signal processing
• B64D 37/02 - Tanks

Abstract

The present disclosure relates to an in-flight entertainment system kit and an installation method thereof, a passenger seat and an aircraft. The in-flight entertainment system kit includes a display assembly, and the display assembly includes a flexible support board and a flexible display screen installed on a passenger side surface of the flexible support board. The passenger seat includes the in-flight entertainment system kit. The aircraft includes the in-flight entertainment system kit or the passenger seat. The in-flight entertainment system kit and the installation method thereof, the passenger seat and the aircraft can improve the in-flight safety, and provide a compact design, which can provide the necessary auxiliary functions without occupying the available space of the passenger, and can further realize the quick assembly and disassembly of the in-flight entertainment system kit.

IPC Classes  ?

• B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for
• B60R 11/02 - Arrangements for holding or mounting articles, not otherwise provided for for radio sets, television sets, telephones, or the like; Arrangement of controls thereof

Abstract

An inventory management system for managing consumer products on a vehicle, in particular an aircraft, comprises a portable product-identification device configured to identify a consumer product presented to the product-identification device, wherein the product-identification device is configured to communicatively connect to a wireless network of the vehicle to update a central inventory of the vehicle based on the identified consumer product; and a detachable holder having a clamping arm configured to releasably clamp the holder to a service device within the vehicle and having a mounting plate configured to releasably attach to the product-identification device to mount the product-identification device on the holder and thereby on the respective service device within the vehicle.

IPC Classes  ?

• G06Q 10/08 - Logistics, e.g. warehousing, loading or distribution; Inventory or stock management
• G06Q 50/30 - Transportation; Communications

Abstract

An interface system for cabin trolleys for a vehicle is proposed, comprising a first interface device attachable to a monument inside the cabin, a second interface device attachable to a cabin trolley, wherein the first interface device comprises at least one of a first electrical port, a first hot water port and a first cold water port, wherein the first interface device comprises a first guide element and a first locking element, wherein the second interface device comprises at least one of a second electrical port, a second hot water port and a second cold water port, wherein the second interface device comprises a second guide element and a second locking element, wherein the first interface device and the second interface device are designed complementary to each other, such that the at least one of a first electrical port, a first hot water port and a first cold water port, and the at least one of a second electrical port, a second hot water port and a second cold water port connect to each other in a connecting position, wherein the first guide element and the second guide element are designed to engage with each other to guide the first interface device and the second interface device into a connecting position, and wherein the first locking element and the second locking element are designed to releasably lock each other to arrest the first interface device and the second interface device in the connecting position.

IPC Classes  ?

• B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for
• B64D 11/04 - Galleys

Abstract

A time-delay latch (100, 101) for securing a structure in a specified position includes a housing (110), a fluid chamber (140) contained within the housing (110) for holding fluid (160), a pin (120) that extends through the fluid chamber and is axially movable within and through the fluid chamber, and a release frame (180) movably secured within the housing. When the pin is in a latched position, the release frame engages with the pin to prevent axial movement of the pin. When the pin is in an unlatched position, the release frame disengages from the pin to allow axial movement of the pin. The axial movement of the pin between the latched position and the unlatched position requires a prescribed duration of time to elapse. During operation, the axial movement of the pin between the unlatched position and the latched position can occur faster than the prescribed duration of time.

IPC Classes  ?

• E05B 51/02 - Operating or controlling locks or other fastening devices by other non-mechanical means by pneumatic or hydraulic means
• E05B 83/42 - Locks for passenger or like doors for large commercial vehicles, e.g. trucks, construction vehicles or vehicles for mass transport
• B64C 1/14 - Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens

Abstract

In order to reduce maintenance work and to improve long-time reliability, the invention provides a health monitoring method for checking a functionality of a flight control surface driving apparatus (104) using at least one load sensor (110) for sensing a load imposed on a control surface drive device (106), the method comprising at least one of the steps: a) comparing at least one load sensor output signal (62-1) of the at least one load sensor (110) with at least one first threshold (T1-L, T1-U) while operating the control surface drive device (106) to move the at least one control surface (102) to a predetermined extended position, b) comparing at least one load sensor output signal (62-1, 62-2) of the at least one load sensor (110) with at least one second threshold (T2-L, T2-U) while operating the control surface drive device (106) to move the at least one control surface (102) from an extended position to a retracted position. Further, a flight control surface drive apparatus (104), a flight control system (100) and an aircraft (10) comprising a control device (112) configured to automatically conduct such health monitoring method are described.

IPC Classes  ?

• B64C 13/40 - Transmitting means with power amplification using fluid pressure
• B64C 13/50 - Transmitting means with power amplification using electrical energy
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• B64F 5/60 - Testing or inspecting aircraft components or systems

Abstract

In order to reduce maintenance work and to improve long-time reliability, the invention provides a health monitoring method for checking a functionality of a flight control surface driving apparatus (104) using at least one load sensor (110) for sensing a load imposed on a control surface drive device (106), the method comprising at least one of the steps: a) blocking movement of the transmission device (108) by means of a brake device (118), b) commanding the control surface drive device (106) to apply a load on the blocked transmission device (108), and c) determining whether at least one load sensor output signal (62) of the at least one load sensor (110) is within a predetermined range. Further, a flight control surface drive apparatus (104), a flight control system (100) and an aircraft (10) comprising a control device (112) configured to automatic command conduct of such health monitoring method are described.

IPC Classes  ?

• B64C 13/50 - Transmitting means with power amplification using electrical energy
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• B64F 5/60 - Testing or inspecting aircraft components or systems
• B64C 13/40 - Transmitting means with power amplification using fluid pressure

Abstract

The invention relates to an aircraft cabin portion (10) having a cabin device module (20) which has an upper face, a fluid-guiding element (30) located on the upper face of the cabin device module (20), and a fluid collector (100) located at a lower end of the fluid-guiding element (30). The fluid collector (100) consists substantially of a flexible material which forms a lumen for draining a fluid, wherein the lumen has an entry opening (105) located at the lower end of the fluid-guiding element (30) so that the fluid flows from the at least one fluid-guiding element (30) into the lumen. The invention also relates to an aircraft having an aircraft cabin portion (10).

IPC Classes  ?

• B64C 1/06 - Frames; Stringers; Longerons
• B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for

Abstract

The invention relates to a tank system for storing a cooled medium, having an inner sleeve which is made of a first fiber-reinforced material and which defines a receiving area for receiving the medium, an outer sleeve which is made of a second fiber-reinforced material and which surrounds the inner sleeve, and multiple spacers which are arranged between the inner sleeve and the outer sleeve in the shape of rods and which are designed to keep the inner sleeve and the outer sleeve at a distance to each other such that at least one thermally insulating intermediate space is produced between the inner sleeve and the outer sleeve, wherein at least the inner sleeve prevents the medium to be stored from leaking.

IPC Classes  ?

• B32B 3/06 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by features of form at particular places, e.g. in edge regions for attaching the product to another member, e.g. to a support
• B32B 1/00 - Layered products essentially having a general shape other than plane
• B32B 3/26 - 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 layer with cavities or internal voids
• B32B 5/18 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by features of a layer containing foamed or specifically porous material
• B32B 27/06 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance
• B32B 27/08 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance of synthetic resin of a different kind
• B64D 37/02 - Tanks

Abstract

The invention relates to a method for pretreating a polymer-coated surface (11) that comprises particles and/or pigments, wherein laser light is emitted by a laser source (110), in particular a pulsed infrared laser beam (111) in the near-infrared range with a pulse fluence of 0.01 to 50 J/cm2 is generated. The method also comprises orienting the laser light by a deflection unit (115) as a laser beam (111) towards the surface (11) and moving the laser light over the surface (11) along a path (40). The emission of the pulsed laser light comprises setting the pulse fluence so that first particles and/or pigments of the surface (11) which face the laser beam (111) absorb the pulsed infrared laser light (111), and part of the surface detaches, the layer thickness of the polymer after detachment being greater than or equal to 50%, preferably greater than or equal to 75%, particularly preferably greater than or equal to 90% of the original layer thickness of the polymer.

IPC Classes  ?

• B23K 26/0622 - Shaping the laser beam, e.g. by masks or multi-focusing by direct control of the laser beam by shaping pulses
• B23K 26/082 - Scanning systems, i.e. devices involving movement of the laser beam relative to the laser head
• B23K 26/16 - Removal of by-products, e.g. particles or vapours produced during treatment of a workpiece
• B23K 26/352 - Working by laser beam, e.g. welding, cutting or boring for surface treatment
• B23K 103/00 - Materials to be soldered, welded or cut

Abstract

The invention relates to a method for maintaining an aircraft air-conditioning system (10), wherein a maintenance control apparatus (100) is connected to a control system (12) of the aircraft air-conditioning system (10). A decontamination activation signal output by the maintenance control apparatus (100) for activating a decontamination process is transmitted to the control system (12) of the aircraft air-conditioning system (10). In response to receiving the decontamination activation signal, the control system (12) of the aircraft air-conditioning system (10) controls the operation of the aircraft air-conditioning system (10) such that at least one section to be decontaminated of an air-distribution system (20, 34, 48) of an aircraft fitted with the aircraft air-conditioning system (10) is heated to a decontamination temperature that is higher than an operating temperature of the section of the air-distribution system (20, 34, 48) in normal operation of the aircraft air-conditioning system (10).

IPC Classes  ?

• A61L 9/16 - Disinfection, sterilisation or deodorisation of air using physical phenomena
• B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
• B08B 7/00 - Cleaning by methods not provided for in a single other subclass or a single group in this subclass
• B64F 5/30 - Cleaning aircraft
• B64F 5/40 - Maintaining or repairing aircraft

Abstract

A holding system for a wheelchair in an aircraft is proposed, comprising a plate-shaped base unit having first fastening elements at an underside adapted to be connected to complementarily shaped second fastening elements in the form of seat rails on a floor or surrounding structure in the aircraft for fastening the base unit, a front holding unit and a rear holding unit arranged on an upper side of the base unit at a distance from each other and defining therebetween a placement area for a wheelchair, wherein the front holding unit and the rear holding unit are adapted to form a releasable form-fit connection with the wheelchair disposed on the placement area so that the wheelchair is braced between the front holding unit and the rear holding unit, and wherein the holding system is adapted to fix the wheelchair stationarily to the floor during operation of the aircraft.

IPC Classes  ?

• B64D 11/06 - Arrangements or adaptations of seats

Abstract

The invention relates to a freight container intended to be received in the cargo hold (3) of an aircraft (1), comprising a floor element (9), wherein a first and a second side wall (21, 23) extend away from first and second edges (17, 19) of the base surface (13) of the floor element (9) which lie opposite each other, the first and second side walls being parallel to each other; wherein a top wall (27) is provided between edges (25) of the first and second side walls (21, 23), which edges are remote from the first and second edges (17, 19), the top wall extending parallel to a resting surface (11) of the floor element (9); wherein a front wall (29) extends between the first and second side walls (21, 23) from a third edge (31) of the base surface (13) to a front edge (33) of the top wall (27); wherein the front wall (29) has a first front wall portion (35), which extends, between the first and second side walls (21, 23), from the third edge (31) of the base surface (13) at a first angle (W1) of at least 90° to the resting surface (11); and wherein the front wall (29) has a second front wall portion (37), which extends from the front edge (31) of the top wall (27) at a second angle (W2) of less than 180° and more than 90° to the top wall (27). This makes it possible to convey the freight container (7), in an inclined position, deeper into the cargo hold (3) of an aircraft (1) than if the top wall (27) simply extended to the frontmost end of the freight container (7). Thus, in turn, the height of the freight container (7) in the region of the top wall (27) can be increased.

IPC Classes  ?

• B65D 88/14 - Large containers rigid specially adapted for transport by air

Abstract

The invention relates to a freight carrier (7) intended to be received in the cargo hold (3) of an aircraft (1), to a system made up of one or more freight carriers (7) and a receiving platform (103), and to a receiving platform (103). The freight carrier (7) comprises a floor element (9) which has a resting surface (11) that is designed to lie on a floor surface of a cargo hold (3) of an aircraft (1). The freight carrier (7) is designed such that its resting surface (11) can be moved over a floor surface extending in a floor plane. The floor element (9) has a base element (12) having a base surface (13). The base surface (13) is situated on the base element (12) such that the base surface (13) faces away from the resting surface (11). The resting surface (11) is provided with means designed to allow the freight carrier (7) to be slid over the floor surface. The floor element (9) has a cavity (85) which extends toward the base surface (13) between the front portion (81) and the rear portion (83).

IPC Classes  ?

• B65D 88/14 - Large containers rigid specially adapted for transport by air
• B64D 9/00 - Equipment for handling freight; Equipment for facilitating passenger embarkation or the like

Abstract

The invention relates to a vehicle region comprising a roof section of a primary structure and two luggage compartments. One of the luggage compartments comprises a releasable luggage compartment hatch and a luggage compartment cover which delimits the top of a luggage area. A releasable securing device can rotatably secure the luggage compartment hatch to the luggage compartment, wherein in an intermediate space above one luggage compartment, the front edge of the luggage compartment cover is arranged at a distance to an end point on which one side of the cover panel is movable, said distance being greater than or equal to the width of the cover panel. Furthermore, a method is provided for assembling and disassembling a cover panel above two luggage compartments, said cover panel being guided at least partly through a luggage area of such a luggage compartment for which the luggage compartment hatch has been removed.

IPC Classes  ?

• B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for
• B60R 5/00 - Compartments within vehicle body primarily intended or sufficiently spacious for trunks, suit-cases, or the like
• B61D 37/00 - Other furniture or furnishings
• B64C 1/06 - Frames; Stringers; Longerons
• B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for

Abstract

The invention relates to an energy recovery assembly (1), to a fuel cell system, and to a vehicle, comprising an electrolyzer (10) which is designed to provide fuel and an oxidizing agent, a fuel cell (20) which is designed to convert the fuel and an oxidizing agent into electric energy, a tank (30) which is designed to store fuel or the oxidizing agent, and a line path (111, 112) which connects the tank (30) to the electrolyzer (10) and the fuel cell (20). The energy recovery assembly (1) additionally comprises an expansion machine (100), which is arranged in the line path (111, 112) and is designed to expand a fluid flowing through the expansion machine (100) and recover mechanical energy, and a valve assembly (12, 22, 40) which is designed to set the line path (111, 112) to a first line mode, in which the fuel or the oxidizing agent is conducted to the tank (30), or a second line mode, in which the fuel or the oxidizing agent is conducted to the fuel cell (20), wherein the fuel or the oxidizing agent flows through the expansion machine (100) in the first line mode and the second line mode.

IPC Classes  ?

• H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
• H01M 8/0656 - Combination of fuel cells with means for production of reactants or for treatment of residues with means for production of gaseous reactants by electrochemical means
• H01M 8/04119 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyte; Humidifying or dehumidifying

Abstract

The invention relates to a storage compartment assembly for a cabin of a vehicle, comprising a storage compartment having a housing, a closeable storage compartment opening, a lower compartment section formed in the housing and an upper compartment section formed in the housing, wherein the lower compartment section and the upper compartment section are arranged directly on top of one another, wherein the storage compartment opening extends over the construction heights of both compartment sections, wherein a lower horizontal pivot edge is formed on a lower boundary of the lower compartment section, on which items of luggage can be placed and slid into the lower compartment section, wherein an upper horizontal pivot edge is formed adjacent to a notional horizontal separating plane between the compartment sections, on which items of luggage can be placed and slid into the upper compartment section, and wherein the storage compartment opening has an upper opening edge facing towards an upper side of the upper compartment section, on which a supporting surface is connected, extending over the upper compartment section and at an angle in the region of 10° to 50° in relation to the separating plane, and enclosing an increasing distance from the separating plane with an increasing distance from the upper boundary.

IPC Classes  ?

• B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for

Abstract

The invention relates to a storage compartment assembly for a cabin of a vehicle, comprising at least one storage compartment having a housing, a lower compartment formed in the housing and having a lower compartment opening, and an upper compartment formed in the housing and having an upper compartment opening, wherein the lower compartment and the upper compartment are arranged directly on top of one another and separated from one another by an intermediate base, wherein the lower compartment opening can be closed by a lower storage compartment flap and the upper compartment opening can be closed by an upper storage compartment flap, wherein a lower horizontal pivot edge is formed on a lower boundary of the lower compartment, on which items of luggage can be placed and slid into the lower compartment, wherein an upper horizontal pivot edge is formed adjacent to a lower boundary of the upper compartment, on which items of luggage can be placed and slid into the upper compartment, and wherein the upper compartment has an upper opening edge on which a supporting surface is connected, extending over the upper compartment and at an angle in the region of 10° to 50° in relation to the intermediate base, and enclosing an increasing distance from the intermediate base with an increasing distance from the upper boundary.

IPC Classes  ?

• B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for

Abstract

Disclosed is a leading edge structure (11) for a flow control system of an aircraft (1), comprising a leading edge panel (13) surrounding a plenum (17) and having a first side portion (21), a second side portion (27), an inner surface (33) facing the plenum (17) and an outer surface (37) in contact with an ambient flow (39), wherein the leading edge panel (13) comprises a plurality of micro pores (45), wherein a first port device (49) is arranged in the first side portion (21) fluidly connected to the plenum (17) via a duct (53) defined by a duct structure (105), and wherein the first port device (49) comprises a first door (55) pivotable by a first hinge (57) about a first hinge axis (59). The object, to provide a more efficient leading edge structure enabling powerful door actuation and requiring minimum space, is achieved in that the leading edge structure (11) comprises a first actuation mechanism (111) for actuating the first door (55), while the first actuation mechanism (111) extends through the duct structure (105), so that a part of the first actuation mechanism (111) is arranged inside the duct (53) and another part of the first actuation mechanism (111) is arranged outside the duct (53).

IPC Classes  ?

• B64C 21/02 - Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
• B64C 21/04 - Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
• B64C 21/06 - Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for sucking
• B64C 21/08 - Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like adjustable

Abstract

Disclosed is a leading edge structure (11) for a flow control system of an aircraft (1), comprising a leading edge panel (13) that surrounds a plenum (17), wherein the leading edge panel (13) has a first side portion (21), a second side portion (27), an inner surface (33) and an outer surface (37), wherein the leading edge panel (13) comprises a plurality of micro pores (45) forming a fluid connection between the plenum (17) and the ambient flow (39), wherein a first air inlet/outlet device (49) is arranged in the first side portion (21) and a second air inlet outlet/device (51) is arranged in the second side portion (27), fluidly connected to the plenum (17), and wherein the first air inlet/outlet device (49) comprises a pivotable first door (55) and the second air inlet outlet/device (51) comprises a pivotable second door (61). The object, to provide a more efficient leading edge structure allowing a simplified air inlet/outlet design and actuation, is achieved in that both the first door (55) and the second door (61) are pivotable between an outlet position (67), a closed position (69), and an inlet position (71).

IPC Classes  ?

• B64C 21/04 - Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
• B64C 21/06 - Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for sucking
• B64C 21/08 - Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like adjustable

Abstract

The invention relates to a storage compartment assembly for a cabin of a vehicle, comprising at least one storage compartment having a housing, a storage compartment opening, a lower compartment formed in the housing, and an upper compartment formed in the housing, wherein the lower compartment and the upper compartment are arranged directly on top of one another and separated from one another by an intermediate base that can be pivoted at least in sections into the upper compartment, wherein a lower horizontal pivot edge is formed on a lower boundary of the lower compartment, on which items of luggage can be placed and slid into the lower compartment, wherein an upper horizontal pivot edge is formed adjacent to a lower boundary of the upper compartment, when the intermediate base is not pivoted, on which pivot edge items of luggage can be placed and slid into the upper compartment, and wherein the upper compartment has an upper opening edge on which a supporting surface is connected, extending over the upper compartment and at an angle in the region of 10° to 50° in relation to the intermediate base, and enclosing an increasing distance from the intermediate base with an increasing distance from the upper boundary.

IPC Classes  ?

• B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for

Abstract

The invention relates to a method for evaluating the usability of a new base element in a plurality of limited spaces. For each limited space, a set of requirements is defined, which comprises placement surface requirements, element requirements and position requirements. A plurality of existing base elements and the new base element are stored in an element database. Each set of requirements for a limited space is converted into logical rules. For each limited space, a new arrangement of structural elements is automatically determined in that structural elements are arranged from the base elements stored in the element database by an interpreter executed on a data-processing device, in such a way that the set of requirements for the limited space in question, which set has been converted into logical rules, is satisfied. The invention further relates to a system for carrying out the method.

IPC Classes  ?

• G06F 30/15 - Vehicle, aircraft or watercraft design
• G06F 30/17 - Mechanical parametric or variational design
• G06F 119/20 - Design reuse, reusability analysis or reusability optimisation
• G06F 111/04 - Constraint-based CAD
• G06F 111/20 - Configuration CAD, e.g. designing by assembling or positioning modules selected from libraries of predesigned modules

Abstract

The invention relates to a multi-part seat track assembly (1) for securing a seat assembly (40) in a vehicle (100). The seat track assembly (1) comprises a base profile (10) having a first material and a seat track upper part (20) having a second material. The base profile (10) and the seat track upper part (20) are connected by means of an adhesive connection (30), wherein the base part (10) has a first adhesive surface (11) and the seat upper part (20) has a second adhesive surface (21) opposite the first adhesive surface (11). The adhesive connection (30) between the base profile (10) and the seat track upper part (20) occurs via the first adhesive surface (11) and the second adhesive surface (21). The first adhesive surface (11) comprises a first surface profile (12) and the second adhesive surface (21) comprises a second surface profile (22), which corresponds to the first surface profile (12) of the first adhesive surface (11).

IPC Classes  ?

• B64D 11/06 - Arrangements or adaptations of seats

Abstract

The invention relates to a component system for interior furnishing of an aircraft, having at least one furnishing component, a plurality of component rails, a plurality of guide elements that can be brought into engagement with the component rails and are movable relative to the component rails, a plurality of retaining elements that are connected to the guide elements and are designed to be coupled to a hull structure of the aircraft or the at least one furnishing component, and a plurality of locking units that are arranged on the component rails and/or on the guide elements and are designed to lock the guide elements to a particular component rail, wherein at least two of the component rails are arranged on the at least one furnishing component or the hull structure at a distance and parallel to each other such that the furnishing component is retractable by means of the component rails on guide elements or component rails that are spatially fixed in the aircraft and can be locked at a retracted position by the locking units.

IPC Classes  ?

• B64C 1/06 - Frames; Stringers; Longerons
• B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for

Abstract

A lightweight structure for a vehicle, more particularly an aircraft, comprises a longitudinal member with a base bridge, which has a first collective conductor on a contact surface, and a transversal member with a central bridge and a transversal bridge extending transverse to the central bridge, the transversal bridge having a first connection conductor, which extends in the region of a first end section of the transversal member on a first surface of the transversal bridge and on a second surface of the transversal bridge oriented opposite the first surface, and a second connection conductor, which extends separately from the first connection conductor at least on the first surface of the transversal bridge. The transversal member extends transverse to the longitudinal member and the transversal member is connected to the base bridge at the first end section in such a manner that the first connection conductor is in contact with the first collective conductor of the base bridge. The lightweight structure further comprises a carbon fibre structural battery connected face-to-face with the central bridge of the transversal member, wherein a first collector of the carbon fibre structural battery is electrically connected to the first or the second connection conductor and a second collector of the carbon fibre structural battery is electrically connected to the other connection conductor.

IPC Classes  ?

• B64C 3/18 - Spars; Ribs; Stringers
• B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
• B64C 39/02 - Aircraft not otherwise provided for characterised by special use

Abstract

The invention relates to a seat rail assembly (10) for fastening a seat assembly in a vehicle (100). The seat rail assembly (10) comprises a seat rail (20) for fastening the seat assembly, the seat rail (20) comprising a metal material. A fastening profile element (30) of the seat rail assembly (10) is designed to receive the seat rail (20), the fastening profile element (30) comprising a plastic. The fastening profile element (30) forms a receiving region (31), which is designed to receive the seat rail (20), and the seat rail (20) comprises a seat rail crown (21), which is arranged in the receiving region (31) of the fastening profile element (30) such that a wall portion (32) of the fastening profile element (30) at least partly extends around the seat rail crown (21). The invention further relates to the use of a seat rail assembly (10) of this type and to a method for producing a seat rail assembly (10).

IPC Classes  ?

• B64D 11/06 - Arrangements or adaptations of seats

Abstract

Described and claimed is a wing (5) for an aircraft (1) comprising a fixed wing (7), a high-lift device (15) and a hold-down arrangement (27) arranged between two supports (23, 25) of the high lift device (15) comprising a first hold-down element (29) attached to the high- lift device (15) and a second hold-down element (31) attached to the fixed wing (7). The first hold-down element (29) contacts the second hold-down element (31) when the high-lift device (15) is in a retracted position in which it prevents a trailing edge (22) of the high-lift device (15) from detaching from an upper surface (19) of the fixed wing (7) when the fixed wing (7) deforms in the spanwise direction. One of the hold-down elements (29, 31) is a load-limited hold-down element (32) which is destroyed when loads transmitted through the holddown elements (29, 31) exceed a threshold. Once destroyed, the trailing edge (22) of the high-lift device (15) is not prevented from detaching from the upper surface (19) anymore. Further, a holddown arrangement (27) and an aircraft (1) comprising a wing (5) are claimed and described.

IPC Classes  ?

• B64C 3/50 - Varying camber by leading or trailing edge flaps
• B64C 9/22 - Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing

Abstract

Described and claimed is a wing (5) for an aircraft (1) comprising a fixed wing (7), a high-lift device (15) and a hold-down arrangement arranged (27) between two supports (23, 25) of the high lift device (15) comprising a first hold-down element (29) attached to the high-lift device (15) and a second hold-down element (31) attached to the fixed wing (7). The first hold-down element (29) contacts the second hold-down element (31) when the high-lift device (15) is in a retracted position in which it prevents a trailing edge (22) of the high-lift device (15) from detaching from an upper surface (19) of the fixed wing (7) when the fixed wing (7) deforms in the spanwise direction. One of the hold-down elements (29, 31) is a load-limited hold-down element (32) which transition from a first stable state to a second state when the load acting on the hold-down arrangement (27) exceeds an operational threshold. Further, a hold-down arrangement (27) and an aircraft (1) comprising a wing (5) are claimed and described.

IPC Classes  ?

• B64C 9/22 - Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing

Abstract

Described and claimed is a wing for an aircraft comprising a fixed wing, a high-lift device and a hold-down arrangement arranged between two supports of the high lift device comprising a first hold-down element attached to the high-lift device and a second hold-down element attached to the fixed wing. The first hold-down element contacts the second hold-down element when the high-lift device is in a retracted position in which it prevents a trailing edge of the high-lift device from detaching from an upper surface of the fixed wing when the fixed wing bends in the spanwise direction. One of the hold-down elements is a load-limited hold-down element which comprises a biasing means. When the load transmitted through the hold-down arrangement exceeds an operational threshold, elastic deformation of the biasing means results in the hold-down arrangement no longer preventing the trailing edge high-lift device from detaching from the upper surface of the fixed wing. Further, a hold- down arrangement and an aircraft comprising a wing are claimed and described.

IPC Classes  ?

• B64C 9/02 - Mounting or supporting thereof
• B64C 9/24 - Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing by single flap

Abstract

Described and claimed is a wing for an aircraft comprising a fixed wing, a high-lift device and a hold-down arrangement arranged between two supports of the high lift device comprising a first hold-down element attached to the high-lift device and a second hold-down element attached to the fixed wing. The first hold-down element contacts the second hold-down element when the high-lift device is in a retracted position in which it prevents a trailing edge of the high-lift device from detaching from an upper surface of the fixed wing when the fixed wing deforms in the spanwise direction. One of the hold-down elements is a load- limited hold-down element which comprises a hydraulic element that is configured to allow the high-lift device to move away from the fixed wing when a load acting through the hold- down arrangement exceeds an operational threshold. Further, a hold-down arrangement and an aircraft comprising a wing are claimed and described.

IPC Classes  ?

• B64C 9/02 - Mounting or supporting thereof
• B64C 9/24 - Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing by single flap

Abstract

The invention relates to an avionics network comprising a plurality of avionics components and a configuration monitoring device, which is connected by wire or wirelessly to the plurality of avionics components. The configuration monitoring device here has at least one configuration data interface which is designed to receive a plurality of configuration parameters characterizing the operating status of the avionics components. The configuration monitoring device further comprises a parameter filtering device which is connected to the at least one configuration data interface and which is designed to filter a subset of the configuration parameters received. The configuration monitoring device additionally comprises reference parameter storage, which is designed to store sets of reference values for configuration parameters, and a parameter comparison device, which is coupled to the reference parameter storage and the parameter filtering device, and which is designed to compare the subset of configuration parameters received and filtered by the parameter filtering device with a set of reference values for the configuration parameters stored in the reference parameter storage.

IPC Classes  ?

• H05B 47/18 - Controlling the light source by remote control via data-bus transmission
• H05B 47/19 - Controlling the light source by remote control via wireless transmission
• G05B 1/03 - Comparing elements, i.e. elements for effecting comparison directly or indirectly between a desired value and existing or anticipated values electric for comparing digital signals
• B64F 5/60 - Testing or inspecting aircraft components or systems
• H04L 12/403 - Bus networks with centralised control, e.g. polling
• H04L 29/08 - Transmission control procedure, e.g. data link level control procedure

Abstract

The invention relates to a vehicle seat which has at least one seat shell, the seat shell comprising a frame having two frame units, which are spaced apart from one another, and a shell surface assembly extending from one of the frame units to the other frame unit, the shell surface assembly having a mesh-like structure made of a first fiber-reinforced plastic, and the seat shell having at least one retaining element which is connected to a corresponding receiving element for securing the seat shell.

IPC Classes  ?

• B64D 11/06 - Arrangements or adaptations of seats
• B60N 2/70 - Upholstery springs

Abstract

A slat arrangement (2) for a wing of an aircraft (58) is proposed, the arrangement (2) having a movable leading-edge slat (4) and a connection section (6), wherein the leading-edge slat (4) comprises a slat leading edge (5) having and a slat trailing edge (10), wherein the connection section (6) comprises a receiving opening (16) for receiving the slat trailing edge (10), wherein the connection section (6) comprises an overhang (12) having a free end (13), wherein the slat trailing edge (10) is designed to be translated under the overhang (12), and wherein a trailing region (18) of the slat (4) is configured to be elastically deformed by the overhang (12) when the slat trailing edge (10) is moved into the receiving opening (16).

IPC Classes  ?

• B64C 3/50 - Varying camber by leading or trailing edge flaps
• B64C 9/22 - Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing

Abstract

A flow body for an aircraft comprises a skin having a first flow surface, which comprises a flow influencing section comprising at least one first layer comprising a first fiber composite material, at least one separator layer, at least one third layer comprising a third fiber composite material, and at least one base layer comprising a base fiber composite material, wherein the first layer comprises lithiated carbon fibers embedded into a matrix to form a negative electrode, wherein the third layer comprises carbon fibers with an electrode active material coating to form a positive electrode, wherein the separator layer comprises a non-conductive material for electrically isolating the first layer and the third layer from each other, and wherein the flow influencing section is configured for selectively raising a region of the arrangement of first layer, separator layer and third layer from the base layer upon application of a voltage between the first and third layers to form a bump on the flow body.

IPC Classes  ?

• B64C 23/04 - Influencing air flow over aircraft surfaces, not otherwise provided for by generating shock waves
• B64C 3/20 - Integral or sandwich constructions
• F03G 7/00 - Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for

Abstract

In order to improve sealing at the transition between high-lift devices and fairings, the inventions suggest a shutter assembly (54) which may be installed in a high-lift system (16), thereby forming the shutter arrangement (24). The shutter assembly (54) comprises the shutter panel (30) and possibly the driving member (32). The shutter assembly (54) can be installed in the high-lift system (16), so as to form any embodiment of the shutter arrangement (24). The shutter arrangement (24) covers the trunnion opening (22) and is moveable in correspondence with the movement of the high-lift device (18) in a continuous and strictly monotone manner.

IPC Classes  ?

• B64C 1/26 - Attaching the wing or tail units or stabilising surfaces
• B64C 9/02 - Mounting or supporting thereof

Abstract

The invention relates to a system (16, 35) for outputting air from an air source in a passenger cabin (46) of a vehicle (42), comprising at least one valve (2, 34) and at least one voltage source (11) that can be connected to the valve (2, 34), wherein the valve (2, 34) is arranged in a valve seat (6) that can be fluidically connected to the air source, wherein the valve (2, 34) has a valve body (8), which in turn has an electro-active polymer that can be deformed with the application of an electrical voltage, wherein the valve body (8) has a basic shape which completely covers the valve seat (6) in order to close same when there is no voltage applied, and wherein the valve body (8) is designed to at least partially open the valve seat (6) with the application of a voltage of the voltage source (11) by deforming the electro-active polymer, such that air can flow from the air source through the valve (2, 34).

IPC Classes  ?

• B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space

Abstract

The present invention relates to a load carrier (7) for accommodation in the cargo hold (3) of an aircraft (1), to a system comprising a load carrier (7) and a fan unit (59), and to a method for loading the cargo hold (3) of an aircraft (1). In particular, the invention relates to a load carrier (7) for accommodation in the cargo hold (3) of an aircraft (1), the load carrier comprising a bottom element (9), which has a support surface (11), the load carrier (7) being designed to be moved over a floor surface extending in a floor plane while the support surface (11) faces the floor surface, the bottom element (9) having a base surface (13), the support surface (11) being provided with a plurality of rolling elements (69, 81), each of the rolling elements (69, 81) being rotatable about an axis of rotation (71), the axis of rotation being oriented such that a parallel to the axis of rotation (71) runs parallel to the floor plane, and the rolling elements (69, 81) being retained on the bottom element (9) such that the axis of rotation (71) of each of the rolling elements (69, 81) can be rotated about a vertical axis (73) running perpendicularly to the floor plane. Furthermore, the invention relates to a load carrier (7) comprising a bottom element (9), the support surface (11) of which is provided with outlet openings (23), through which air can exit from the support surface (11) in order to form an air cushion under the support surface (11). The invention also relates to a load carrier (7) comprising a bottom element (9) the support surface of which is provided with slider elements.

IPC Classes  ?

• B64F 1/32 - Ground or aircraft-carrier-deck installations for handling freight
• B64D 9/00 - Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
• B65D 88/12 - Large containers rigid specially adapted for transport
• B65D 90/18 - Castors, rolls, or the like, e.g. detachable
• B65D 88/14 - Large containers rigid specially adapted for transport by air
• B65G 7/02 - Devices adapted to be interposed between loads and the ground or floor, e.g. crowbars with means for assisting conveyance of loads
• B60P 1/64 - Vehicles predominantly for transporting loads and modified to facilitate loading, consolidating the load, or unloading the load supporting or containing element being readily removable
• B65G 7/04 - Rollers
• B65G 7/06 - Devices adapted to be interposed between loads and the ground or floor, e.g. crowbars with means for assisting conveyance of loads using fluid at high pressure supplied from an independent source to provide a cushion between load and ground

Abstract

The invention proposes a component (2) made of a fibre-reinforced plastic, having a first surface portion (4), a second surface portion (6) and a transition portion (8), which is enclosed by the first surface portion and the second surface portion, wherein surface tangents (16a, 16b, 16c) to the first surface portion and the second surface portion are not parallel, at least in regions adjacent to the transition portion, wherein the transition portion has a curvature which adjoins the adjacent surface portions in a tangentially constant manner, wherein an arrangement of at least two layers made of a fibre-reinforced plastic extends from the first surface portion, over the transition portion, onto the second surface portion, and wherein fibres (14) at least of one of the layers run with an unchanging orientation on the first surface portion and the second surface portion and, on the transition portion, run in a laterally offset, inflected or curved manner along the running direction.

IPC Classes  ?

• B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
• B29C 53/00 - Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor

Abstract

A tolerance-compensating actuating mechanism (13) for actuating an output device (8) from an input device (11) is illustrated and described, wherein the output device (8) is movable relative to the input device (11) within a tolerance range, wherein the actuating mechanism (13) has actuating kinematics (14) comprising an input lever (15) mounted on the input device (11) and an output lever (17) mounted on the output device (8) and a pivot (21) which is movable relative to the input device (11) and the output device (8), wherein the actuating kinematics (14) are designed in such a manner that a movement of the input lever (15) between an open position and a closed position causes a movement of the output lever (17) between an open position and a closed position. The problem of providing an actuating mechanism which permits as effective tolerance compensation as possible and prevents constraining forces between the input device and the output device is solved in that the actuating mechanism (13) in addition to the actuating kinematics (14) has reference kinematics (39) connecting the output device (8) and the input device (11) to the pivot (21), and in that the reference kinematics (39) are designed in such a manner that they adapt the position of the pivot (21) during a movement of the output device (8) relative to the input device (11).

IPC Classes  ?

• F16H 21/04 - Guiding mechanisms, e.g. for straight-line guidance
• B64D 11/02 - Toilet fittings
• B23Q 1/44 - Movable or adjustable work or tool supports using particular mechanisms

Abstract

An avionics network comprises at least one data bus system, a multiplicity of network subscribers connected to one or more of the data bus systems via network interfaces, a central configuration server designed to configure each of the multiplicity of network subscribers individually according to a predefined functionality, and a synchronization node designed to stipulate a work cycle for the multiplicity of network subscribers via the at least one data bus system according to a stipulated synchronization protocol.

IPC Classes  ?

• H04L 12/403 - Bus networks with centralised control, e.g. polling

Abstract

Processes for producing an OLED screen with a reduced, minimized, or eliminated bezel section surrounding the display area. The control circuity (206) of the display screen is moved to beneath the OLED (212) and transistor layers (210). The screens with the reduced sized may be installed in an aircraft, and, two or more of the OLED screens with reduced sized may be positioned adjacent to each other so as to form an array.

IPC Classes  ?

• H01L 27/32 - Devices consisting of a plurality of semiconductor or other solid-state components formed in or on a common substrate including components using organic materials as the active part, or using a combination of organic materials with other materials as the active part with components specially adapted for light emission, e.g. flat-panel displays using organic light-emitting diodes

Abstract

Device (1) for producing a T-shaped semifinished product from a multiply non-crimp fabric (3) comprising reinforcing fibres for a composite material. The T-shaped semifinished product has a web (5) and a flange (7). The device (1) comprises a web forming tool (9), with which a web portion (15) of the non-crimp fabric (3) is clamped in place, a forming tool (21), with which plies of a flange portion (19) of the non-crimp fabric (3) are split into two parts and are formed into the flange (7), a depositing device (29), with which a tube body (31) is deposited on the flange portion (19) formed into the flange (7), a holding tool (41), with which a clearance (39) between the holding tool and the flange (7) is formed, and a filling device (37), with which the tube body (31) is filled with a gas such that the tube body (31) fills the clearance (39) and firmly holds the flange portion (19) formed into the flange (7), and alternatively, rather than the tube body (31), a magnetic force can be generated between a sheet (31) and the web forming tool (9), said magnetic force attracting the flexible sheet (31) towards the web forming tool (9) such that the flexible sheet (31) firmly holds the flange portion (19) formed into the flange (7). Furthermore, a corresponding method is illustrated and claimed.

IPC Classes  ?

• B29C 43/48 - Endless belts
• 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 70/50 - Shaping or impregnating by compression for producing articles of indefinite length, e.g. prepregs, sheet moulding compounds [SMC] or cross moulding compounds [XMC]

Abstract

In order to improve space allocation, reduce weight and increase aerodynamic performance in high-lift devices (20), an actuator arrangement (24) for a fixed leading edge member (26) is proposed. The fixed leading edge member (26) has an inner cavity (48) defined by the outer skin (44) and ribs (46). The actuator arrangement (24) comprises at least one geared rotary actuator (42) which moves relative to the other parts along a circular arc section (52) during extending and retracting of the high-lift device (20) between a fully retracted position and a fully extended position. In the fully retracted position, the actuator (40) is predominantly accommodated within the inner cavity (48) and in the extended position the actuator (40) is predominantly positioned outside the inner cavity (48), preferably protruding through a D-nose cut-out (50).

IPC Classes  ?

• B64C 9/22 - Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing
• B64C 13/28 - Transmitting means without power amplification or where power amplification is irrelevant mechanical

Abstract

A table arrangement (10) comprises a mounting element (12), which can be fastened to a fastening structure element (102) and defines a mounting plane (E). The table arrangement (10) further comprises a first table element (20) connected to the mounting element (12), wherein the first table element (20) is pivotable relative to the mounting element (12) about a first pivot axis (S1) between a stowage position, in which the first table element (20) extends substantially parallel to the mounting plane (E) defined by the mounting element (12), and a position of use, in which the first table element (20) extends substantially perpendicular to the mounting plane (E) defined by the mounting element (12). Finally, the table arrangement (10) comprises a second table element (22) connected to the first table element (20), wherein the second table element (22) is arranged substantially parallel to the first table element (20) and is rotatable relative to the first table element (20) about a rotation axis (D) arranged parallel to the mounting plane (E) in the position of use.

IPC Classes  ?

• B64D 11/06 - Arrangements or adaptations of seats
• B60N 3/00 - Arrangements or adaptations of other passenger fittings, not otherwise provided for

Abstract

The invention relates to an oxygen mask for supplying oxygen to a person, which can be modified for use on differently sized faces. The oxygen mask has a holding frame, which has a first cross-brace and a second cross-brace, a substantially gas-impermeable material arranged on the holding frame and which can be stretched between the first cross-brace and the second cross-brace, a headband connected to the holding frame, an exhalation valve arranged on the material and penetrating the material, and an oxygen supply line for providing oxygen to an inside of the oxygen mask, wherein the first cross-brace and the second cross-brace are arranged in two lateral holders, which are opposite each other, wherein at least the first cross-brace is flexible and wherein the distance of the lateral holders to each other is adjustable at least between a first and a second distance.

IPC Classes  ?

• A61M 16/06 - Respiratory or anaesthetic masks
• A62B 18/08 - Component parts for gas-masks or gas-helmets, e.g. windows, straps, speech transmitters, signal-devices
• A41D 13/11 - Protective face masks, e.g. for surgical use, or for use in foul atmospheres
• A62B 18/02 - Masks
• A62B 9/02 - Valves

Abstract

The invention relates to a leading edge assembly (9) for a wing (3). The leading edge assembly comprises a housing (11) which is configured to be connectable to a fixed wing section (59) of the wing (3) and in which a first opening (19) connecting an exterior (45) of the housing (11) with an interior (47) of the housing (11) is formed, an actuating element (13) which is movably connected to the housing (11) such that the actuating element (13) is movable between a first position and at least one second position, wherein the actuating element (13) extends through the first opening (19) and comprises a first section (49) which is arranged in the interior (47) of the housing (11) and a second section (51) which is arranged in the exterior (45) of the housing (11) and which is configured to be connectable to a high lift device.

IPC Classes  ?

• B64C 9/24 - Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing by single flap

Abstract

The invention relates to a seat assembly for a cabin of a means of transportation, having an aisle which is arranged in the longitudinal direction of the cabin, two mutually spaced cabin walls which are oriented parallel to the aisle at least in some regions and laterally delimit the cabin, two outer passenger seat regions which are separated from one another by the aisle and each of which adjoins one of the two cabin walls, wherein the outer passenger seat regions have at least one row of seats with a respective inner first seat module which faces the aisle, a central second seat module adjoining the first module, and an outer third seat module adjoining the respective cabin wall. Each of the seat modules has a seat and an ottoman paired with the seat or a foot rest at a distance from the respective seat, and the third seat module is offset to the second seat module in the longitudinal direction such that the seat of the third seat module adjoins the ottoman or the foot rest of the second seat module in the transverse direction.

IPC Classes  ?

• B64D 11/06 - Arrangements or adaptations of seats

Abstract

The invention relates to a method for producing a torsion box for a structure of an aeroplane. Said method comprises the following steps: providing a first component made of a fibre composite material, which first component has a first planar base having a first inner side and a first outer side, a plurality of first stiffening elements being arranged on the first inner side and forming a composite with the first base; providing a second component made of a fibre composite material, which second component has a second planar base having a second inner side and a second outer side, a plurality of second stiffening elements being arranged on the second inner side and forming a composite with the second base; superimposing the first component and the second component in such a way that the first stiffening elements lie, at least in some areas, on the second inner side and the second stiffening elements lie, at least in some areas, on the first inner side; and connecting the first stiffening elements to the second base and connecting the second stiffening elements to the first base.

IPC Classes  ?

• B64C 1/12 - Construction or attachment of skin panels
• B64C 1/06 - Frames; Stringers; Longerons
• B64C 3/18 - Spars; Ribs; Stringers
• B64C 3/20 - Integral or sandwich constructions
• B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
• B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor

Abstract

The present invention relates to an indicator apparatus (10) for guiding occupants in an interior accommodated by an aircraft fuselage, having a mounting device (12), which can be fastened to a wall portion of the interior and is provided with at least one indicator means (14), which conveys at least one item of visual information to the occupants of the interior when in operation, wherein the at least one indicator means (14) can be or is operated electrically, and wherein the at least one indicator means (14) can be or is connected to a power supply (30) for its operation. In order to create an indicator apparatus (10) which helps improve the orientation of passengers in the cabin of an aircraft, can be produced easily and is easy to install and service, and which can be operated in a fail-safe manner in an emergency situation of the aircraft, according to the invention the at least one indicator means (14) is provided with an at least one-piece layer (16), on which the circuitry necessary for its operation is provided in an integrated fashion, and the power supply (30) is formed by at least one composite structure battery (40) which is built up layer by layer and can be or is connected to the layer (16). The present invention also relates to a method for producing an indicator apparatus (10) of this kind.

IPC Classes  ?

• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• G09F 9/00 - Indicating arrangements for variable information in which the information is built-up on a support by selection or combination of individual elements
• H01L 51/00 - Solid state devices using organic materials as the active part, or using a combination of organic materials with other materials as the active part; Processes or apparatus specially adapted for the manufacture or treatment of such devices, or of parts thereof

Abstract

The invention relates to a handling system (30) for a receptacle space (10) in a vehicle for storage for containers (20). A linear guide (32) is provided on an inner wall of the receptacle space (10). The linear guide (32) guides at least one carrier element (37) in the movement direction of the container (20), wherein the storage position of the container (20) is provided having the rear wall thereof in the region of the rear wall of the receptacle space (10). The removal position is provided in the region of an insertion opening (13), arranged opposite the rear wall. The at least one carrier element (37) is operatively connected to at least one spindle nut (42) of a spindle drive (40). The container (20) is thus moved linearly from a stowage and storage position to a removal position and vice versa.

IPC Classes  ?

• B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for
• B64D 11/04 - Galleys

Abstract

A flow body for an aircraft with an integrated de-icing system is proposed. The flow body comprises a front skin, at least one internal structural component arranged inside the front skin, at least one lever having a first end, a second end and an attachment point between the first end and the second end, and at least one actuator for applying an impulsive force. The actuator is arranged inside the front skin at a distance thereto, wherein the lever extends from the actuator to an inner surface of the front skin, such that the first end is coupled with the front skin and such that the second end is coupled with the actuator, wherein the attachment point is swivably supported on the internal structural component, wherein a distance between the second end and the attachment joint is greater than the distance between the first end and the attachment joint, and wherein the lever and the actuator are designed for applying an impulsive force in a transverse direction to the lever, such that the lever rotates around the attachment point and such the first end urges the front skin to locally elastically deform for removing ice accretion from an outer side of the front skin.

IPC Classes  ?

• B64D 15/16 - De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface

Abstract

The invention relates to a primary structural assembly (100) for an aircraft outside-skin heat exchanger (50), the assembly comprising: an outer-skin portion (5) which defines an outer shape of the aircraft (1) and forms a portion of a hull of the aircraft (1), wherein the outer-skin portion (5) comprises at least one recess (10); a thermal-transfer fluid connection (20) which is designed to convey a thermal-transfer fluid into the recess (10); a component (50) which closes the recess (10); and at least one retaining means (30) which is arranged in or on the recess (10) and is designed to hold the component (50) closing the recess (10) in the recess (10). The invention further relates to an aircraft (10) comprising such a primary structural assembly (100) and to a method for attaching an aircraft outside-skin heat exchanger.

IPC Classes  ?

• B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
• B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled

Abstract

The invention relates to a method of repairing a defect in a fibre composite component formed from at least one fibre ply of a fibrous material of a fibre composite and a matrix material of the fibre composite embedding the fibrous material. The method comprises the following steps: removing the defect from the fibre composite component and forming a repair cavity in the fibre composite component, inserting at least one repair fibre layer of a fibrous material into the formed repair cavity of the fibre composite component, and curing the matrix material embedding the fibrous material of the repair fibre ply after introducing the repair fibre ply into the repair cavity of the fibre composite component. At least one repair fibre ply is introduced into the repair cavity, the ply thickness of which is smaller than the ply thickness of the fibre plies of the remaining fibre composite component.

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 73/04 - 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

Abstract

The invention relates an infrared light transmission welding method in which a simple polychromatic incoherent infrared light (32) is generated by a simple infrared light source (24) and is transmitted through a first workpiece part (12) to a welding point (16) for joining to a second workpiece part (14), in order to provide universal welding of thermoplastic workpiece parts (12, 14) in a simple manner. In particular, the infrared light is guided through a transparent clamping element (26).

IPC Classes  ?

• B29C 65/14 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure using wave energy or particle radiation
• B29C 65/48 - Joining of preformed parts; Apparatus therefor using adhesives
• B29C 65/50 - Joining of preformed parts; Apparatus therefor using adhesives using adhesive tape
• B29C 65/00 - Joining of preformed parts; Apparatus therefor
• B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof

Abstract

The invention relates to a method for producing a composite component, which comprises a bottom layer, a cover layer and a honeycomb structure, the method comprising the following steps: applying the honeycomb structure to the bottom layer such that a plurality of honeycomb chambers is formed; filling honeycomb chambers in a reinforcement region with a granular material and removing granular material from other honeycomb chambers such that each honeycomb chamber in the reinforcement region is filled up to a granular-material filling height and honeycomb chambers outside the reinforcement region are free of granular material; applying the cover layer to the honeycomb structure such that the plurality of honeycomb chambers is closed, and heating the composite component to a process temperature at which the granular material introduced into the honeycomb chambers expands in order to fill up the honeycomb chambers filled with granular material and the cover layer, the bottom layer, the honeycomb structure and the expanded granular material harden, the density of the expanded granular material in the honeycomb chambers filled with granular material being dependent on the granular-material filling height. The invention further relates to a composite component produced by means of the method.

IPC Classes  ?

• B32B 37/24 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with at least one layer not being coherent before laminating, e.g. made up from granular material sprinkled onto a substrate
• B29C 44/18 - Filling preformed cavities
• B29C 44/44 - Feeding the material to be shaped into a closed space, i.e. to make articles of definite length in the form of expandable particles or beads
• B32B 3/12 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
• B32B 27/06 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance
• C08J 9/04 - Working-up of macromolecular substances to porous or cellular articles or materials; After-treatment thereof using blowing gases generated by a previously added blowing agent
• C08J 9/232 - Forming foamed products by sintering expandable particles

Abstract

The invention relates to a method for manufacturing a component from a fibre-reinforced plastic, in which method at least one layer of a semi-finished fibre product having a peripheral contour is applied to the moulding tool at a first temperature so that the contour lies within the peripheral edge. A compensating body having a thermal expansion coefficient greater than a thermal expansion coefficient of the moulding tool is positioned along the peripheral edge so that the compensating body extends from the edge in the direction of the peripheral contour. After sealing the assembly, resin is introduced and the assembly is heated. As a result, the compensating body expands more than the moulding tool and encloses the semi-finished fibre product in a flush manner so that the shape of the component can correspond to a designated final shape and does not need to be reworked.

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
• B29C 70/54 - Component parts, details or accessories; Auxiliary operations
• B29C 33/30 - Mounting, exchanging or centering
• B29C 33/40 - Plastics, e.g. foam or rubber
• B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
• B29C 45/00 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor

Abstract

The invention relates to a method for manufacturing a component (16, 18) for an aircraft. This relates in particular to components for the structure, such as frames (18) and stringers (16). In order to reduce weight, aircraft are increasingly being constructed from polymer fibre-reinforced composite materials. Originally, these were fibre-reinforced composite materials made of thermosetting polymer and carbon fibres. With the development of high-performance thermoplastics, thermoplastic fibre-reinforced composite materials have increasingly become the focus of research and development. One example of such a high-performance plastic is poly(etheretherketone). However, the manufacture of components (16, 18) from thermoplastic fibre-reinforced composite materials is a complex process. The disclosure indicates an improved method for manufacturing such components (16, 18). The method comprises the following steps: manufacturing a planar article (28) from a thermoplastic fibre-reinforced composite material comprising a thermoplastic polymer material and reinforcing fibres embedded therein; reshaping the planar article (28) into a semi-finished product; and solidifying the semi-finished product in order to obtain the component (16, 18). The invention also relates to the components (16, 18) which can be obtained using said method.

IPC Classes  ?

• B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• 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 70/50 - Shaping or impregnating by compression for producing articles of indefinite length, e.g. prepregs, sheet moulding compounds [SMC] or cross moulding compounds [XMC]
• B29C 70/42 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles

Abstract

The invention relates to a method for connecting two components. In this method, a first component and a second component, which are each formed from a thermoplastic material, are first provided. The first component has a first peel-off ply on a first surface of the first component. The first peel-off ply is removed from the first component. Once the first peel-off ply has been removed, the first surface of the first component is brought into contact with a second surface of the second component. The first component and the second component are then welded to one another at the first and second surface by ultrasonic welding.

IPC Classes  ?

• B29C 65/08 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure using ultrasonic vibrations
• B29K 101/12 - Thermoplastic materials
• B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof

Abstract

The present invention relates to a storage system (1), comprising a first pouch (10) for receiving an electronic device (30) and a second pouch (20) for receiving the first pouch (10). The first pouch (10) is at least partially enclosed by the second pouch (20) when the first pouch (10) is received in the second pouch (20). The first pouch (10) has a first woven fabric layer (11). Furthermore, the first pouch (10) has an insulating layer (13), which adjoins the first woven fabric layer (11) and is designed to bind material produced in the event of combustion. The second pouch (20) can be closed in such a way that, when the second pouch (20) is closed, an opening (25) for removing thermal energy remains.

IPC Classes  ?

• A45C 3/00 - Flexible luggage; Hand bags
• A45C 7/00 - Collapsible or extensible luggage, bags or the like
• B65D 30/08 - Sacks, bags or like containers characterised by the material used with laminated or multiple walls in spaced face-to-face relationship, e.g. double walls
• A45C 11/00 - Receptacles for purposes not provided for in groups

Abstract

A fastening system (10) comprises a structure holding element (12) which can be fastened to a structural component (104). The fastening system (10) further comprises a component holding element (20) which can be fastened to a component (102) that is to be fastened and which is movable relative to the structure holding element (12) between a first operating position and a second operating position. A first lever element (24) of the fastening system (10) is connected to the structure holding element (12) so as to be rotatable about a first rotation axis (A1) and is connected to the component holding element (20) so as to be rotatable about a second rotation axis (A2). Lastly, the fastening system (10) comprises a connection element (38), which is connected to the component holding element (20) so as to be rotatable about a third rotation axis (A3) and which is connected to the structure holding element (12) so as to be displaceable in translation relative to the structure holding element (12), in such a way that the second rotation axis (A2), when the component holding element (20) is transferred from its first operating position into its second operating position, is displaced in a plane (E) extending perpendicularly to the second rotation axis (A2).

IPC Classes  ?

• B64C 1/06 - Frames; Stringers; Longerons
• B64C 1/14 - Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens
• B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for
• E05D 3/18 - Hinges with pins with two or more pins with sliding pins or guides

Abstract

The invention relates to a wing (3) for an aircraft (1), comprising a main wing (5), a slat (7), and a connecting assembly (9) movably connecting the slat (7) to the main wing (5), such that the slat (7) is movable between a retracted position and at least one extended position, wherein the connecting assembly (9) comprises a slat track (11) and a roller bearing (13), wherein a front section (17) of the slat track (11) is mounted to the slat (7), wherein a rear section (19) and an intermediate section (21) of the slat track (11) are mounted to the main wing (5) via the roller bearing (13), wherein the roller bearing (13) comprises a guide rail (23) mounted to the main wing (5) and a first roller (27), wherein the first roller (27) is rotatably mounted to the rear section (19) of the slat track (11), wherein the first roller (27) engages a first engagement surface (33) formed by the guide rail (23), wherein the roller bearing (13) comprises a second roller (31), wherein the second roller (31) is rotatably mounted to the main wing (5), wherein the second roller (31) engages a second engagement surface (35) formed by the intermediate section (21) of the slat track (11), wherein the first engagement surface (33) comprises a first section (45), which is straight or is curved with a first radius of curvature (51) and a first center of curvature (53), and the second engagement surface (35) comprises a second section (49), which is straight or is curved with a second radius of curvature (55) and a second center of curvature, wherein, when both the first section (45) and the second section (49) are curved, the first center of curvature (53) and the second center of curvature are spaced from each other.

IPC Classes  ?

• B64C 9/22 - Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing

Abstract

Processes for producing an OLED screen with a reduced size, in particular for an aircraft. The processes utilize laser cutting to reduce the size of OLED screens from a production line. After the cutting, a plasma coating process seals the cut edges. The portion of the production OLED screen that is cut may be a portion of the display screen. The screens with the reduced sized may be installed in an aircraft, and, two or more of the OLED screens with reduced sized may be positioned adjacent to each other so as to form an array.

IPC Classes  ?

• H01L 27/32 - Devices consisting of a plurality of semiconductor or other solid-state components formed in or on a common substrate including components using organic materials as the active part, or using a combination of organic materials with other materials as the active part with components specially adapted for light emission, e.g. flat-panel displays using organic light-emitting diodes
• H01L 51/52 - Solid state devices using organic materials as the active part, or using a combination of organic materials with other materials as the active part; Processes or apparatus specially adapted for the manufacture or treatment of such devices, or of parts thereof specially adapted for light emission, e.g. organic light emitting diodes (OLED) or polymer light emitting devices (PLED) - Details of devices
• H01L 51/56 - Processes or apparatus specially adapted for the manufacture or treatment of such devices or of parts thereof

Abstract

A mounting system (10) comprises a holding element (12) in which a receiving opening (20) is formed, and a nut element (14) received in the receiving opening of the holding element. A fastening arrangement (16) of the mounting system is designed, in a first operating state, to fasten the nut element to the holding element in a movable manner relative to the holding element in a plane perpendicular to a longitudinal axis (LI) of the receiving opening. In a second operating state, the fastening arrangement is designed to fix the nut element in its position relative to the holding element. Finally, the mounting system comprises a fastening pin (18) that is introducible into the nut element along a longitudinal axis (L2) of the nut element and, in a desired end position, is rotatable about the longitudinal axis (L2) of the nut element relative to the nut element in order to fix the fastening pin in its position relative to the nut element and to transfer the fastening arrangement from its first operating state into its second operating state.

IPC Classes  ?

• F16B 37/04 - Devices for fastening nuts to surfaces, e.g. sheets, plates
• F16B 37/08 - Quickly-detachable nuts, e.g. consisting of two or more parts; Nuts movable along the bolt after tilting the nut

Abstract

A movable flow body device for an aircraft is proposed, comprising an elongated flow body having a main extension axis, a first mechanical interface in a first position along the main extension axis, a second mechanical interface in a second position and a third mechanical interface in a third position. The first mechanical interface may be a master interface arranged in a central region, while the second and third mechanical interfaces are slave interfaces. Preferably in the outboard position a link plate between a support lever and a support rib of the flow body is inverted compared to the further inboard mechanical interface, which allows for supporting slimmer and longer flow bodies in the outboard region and providing a rigging hinge line through the whole flow body.

IPC Classes  ?

• B64C 9/02 - Mounting or supporting thereof
• B64C 9/22 - Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing
• B64C 9/16 - Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing

Abstract

The invention relates to an electronic arrangement for an aircraft (1), an aircraft having a structure and such an electronic arrangement (3) and a method for providing such an electronic arrangement (3). The electronic arrangement has a structural portion (5) of a structure of an aircraft (1) and one or more structural elements (15), each having a frame (16) and one or more electronic components (20a-c, 26, 27), which are fixed to the frame (16). The structural portion (5) has a reinforcement arrangement (8) of elongate longitudinal and transverse reinforcement elements (6, 7) connected to each other, an outer skin (9), which is arranged on one side of the reinforcement arrangement (8) and is fixed to the longitudinal and transverse reinforcement elements (6, 7), wherein a surface of the outer skin (9) facing away therefrom forms an outer surface (11) of the structural portion (5), and has one or more skin panels (12), each of which is a section of the outer skin (9), which is defined between two directly adjacent longitudinal reinforcement elements (6) of the longitudinal reinforcement elements (6) and two directly adjacent transverse reinforcement elements (7) of the transverse reinforcement elements (7). In at least one of the skin panels (12), an opening (13), completely arranged in the skin panel (12), is formed in the outer skin (9), and for each of the skin panels (12) with one of the openings (13) an associated structural element (15) is separately provided, which is designed and detachably fastened by the frame (16) thereof to the outer skin (9) in the corresponding skin panel (12) on the side of the outer skin (9) opposite the outer surface (11), such that it seals the corresponding opening (13) such that the skin panel (12) has at least the same pressure-tightness and at least the same strength relative to tension, pressure and shear forces which act in the skin panel (12) in the extension direction of the outer skin (9) as the same skin panel (12) without the corresponding opening (13).

IPC Classes  ?

• B64C 1/36 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like adapted to receive antennas or radomes
• H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons
• H01Q 1/12 - Supports; Mounting means

Abstract

The invention relates to an elongate antenna assembly (1) for an aircraft. The antenna assembly (1) comprises a structural section (3) and an antenna element (5), wherein the structural section (3) comprises an elongate leading edge section (7) extending in a longitudinal direction (13) of the antenna assembly, a first lateral section (9), and a second lateral section (11), wherein the leading edge section (7) is curved such that the leading edge section (7) comprises a convex outer surface (15) extending in the longitudinal direction (13) of the antenna assembly (1) on a convex side (19) of the antenna assembly, wherein the first lateral section (9) extends away from the leading edge section (7) on a first side (23) of the leading edge section (7) in a first direction (39) transverse to the longitudinal direction (13) of the antenna assembly, wherein the second lateral section (11) extends away from the leading edge section (7) on a second side (25) of the leading edge section (7) opposite the first side (23) of the leading edge section (7) in a second direction (41) transverse to the longitudinal direction (13) of the antenna assembly, wherein an elongate first recess is formed in the leading edge section (7) on the convex side (19) of the antenna assembly, wherein the first recess extends in the longitudinal direction (13) of the antenna assembly, wherein an elongate first section (27) of the antenna element (5) extends in the longitudinal direction (13) of the antenna assembly (1) and is arranged in the first recess, such that an outer surface (43) of the elongate first section (27) of the antenna element (5) and the convex outer surface (15) of the leading edge section (7) form a first surface of the antenna assembly (1) on the convex side (19) of the antenna assembly.

IPC Classes  ?

• H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons

Abstract

Disclosed is a wing (3) for an aircraft (1), comprising a fixed wing (5), a foldable wing tip portion (9) and a flight latch device (17) for latching the foldable wing tip portion (9) in the extended position, wherein the flight latch device (17) comprises a housing (19), a latch bolt (21), and a motor (23) for driving the latch bolt (21) between the latched and unlatched positions. The object, to provide a wing having a flight latch device with a simple and efficient offset compensation, is achieved in that the flight latch device (17) comprises a threaded shaft (29) rotationally driven by the motor (23), a nut (37) engaging the shaft (29), so that the nut (37) can rotate relative to the shaft (29), wherein the nut (37) is connected to the housing (19) via a linear guide (41) and is connected to the latch bolt (21) for common linear movement with the latch bolt (21), and wherein the flight latch device (17) comprises an offset compensation, providing that the shaft (29) is supported pivotable relative to the housing (19) and the latch bolt (21) is coupled to the nut (37) via a compensational bearing (49) allowing angular play between the nut (37) and the latch bolt (21).

IPC Classes  ?

• B64C 3/56 - Folding or collapsing to reduce overall dimensions of aircraft
• F16H 25/20 - Screw mechanisms

Abstract

Disclosed is a wing (3) for an aircraft (1), comprising a fixed wing (5), a foldable wing tip portion (9), and a flight latch device (17) for latching the foldable wing tip portion (9) in the extended position, wherein the flight latch device (17) comprises a housing (19), a latch bolt (21) linearly movable relative to the housing (19), and a motor (23) for driving the latch bolt. The object, to provide a wing having a flight latch device with reduced space requirements, is achieved in that the flight latch device (17) comprises a threaded shaft (29) having an external thread (33) and being mounted to the housing (19) in a torque proof manner, the flight latch device (17) comprises a nut (37) having an internal thread (39) engaging the external thread (33) of the shaft (29), so that the nut (37) can rotate about the shaft (29) along the external thread (33), the motor (23) is arranged coaxially around the nut (37), wherein a rotor part (45) is mounted to the nut (37) in a torque proof manner, and wherein a stator part (47) is rotatably connected to the rotor part (45) and is connected to the housing (19) by a first linear guide (51) allowing linear movement and inhibiting rotation of the stator part (47), and the nut (37) is connected to the latch bolt (21) for common linear movement with the latch bolt (21).

IPC Classes  ?

• B64C 3/56 - Folding or collapsing to reduce overall dimensions of aircraft

Abstract

The invention relates to an actuation device (26a-26f) for a public transport vehicle (2). The aim of the invention is to be able to avoid the transmission of bacteria from one person to another person during the actuation of the actuation device (26a-26f). This aim is achieved, according to the invention, in that the actuation device (26a-26f) can be actuated by means of a predefined contactless actuation gesture, the actuation device (26a-26f) having a sensor unit (28) that measures without contact and an evaluation unit (30), which is connected to the sensor unit (28). The sensor unit (28) is designed to generate a sensor signal and to transmit the sensor signal to the evaluation unit (30) when an object, in particular a finger or a hand of a person, performs, within a detection space of the sensor unit (28), a movement at a distance from the actuation device (26a-26f), the signal being dependent on the movement sequence of the movement. The evaluation unit (30) is designed to check, using the sensor signal, whether the movement performed by the object is a predefined contactless actuation gesture, by means of which the actuation device (26a-26f) can be actuated, and, if the movement performed by the object is such an actuation gesture, to generate a control signal for a device (10, 14, 20, 24, 32, 34) of the vehicle (2), which device is to be controlled.

IPC Classes  ?

• B60K 37/06 - Arrangement of fittings on dashboard of controls, e.g. control knobs
• E05B 81/00 - Power-actuated vehicle locks
• H03K 17/18 - Modifications for indicating state of switch

Abstract

A leading-edge arrangement for an aircraft is proposed, comprising a plurality of movable flow bodies, a supply duct, an air transfer duct, and at least one perforated tube, wherein the movable flow bodies are arranged in a consecutive arrangement to form a row with a first end and a second end, wherein the supply duct reaches into an interior of one of the flow bodies at the first end, wherein the air transfer duct connects to the supply duct and extends at least through the interior of the respective flow body in the direction towards the second end, wherein the at least one perforated tube is arranged inside at least one of the flow bodies that directly follows on, wherein the at least one perforated tube is in fluid communication with the transfer duct, and wherein the transfer duct is configured to transfer air from the supply duct into the at least one perforated tube.

IPC Classes  ?

• B64D 15/04 - Hot gas application
• B64C 3/50 - Varying camber by leading or trailing edge flaps
• B64C 9/08 - Adjustable control surfaces or members, e.g. rudders bodily displaceable
• B64C 9/26 - Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing by multiple flaps
• B64C 3/28 - Leading or trailing edges attached to primary structures, e.g. forming fixed slots

Abstract

Disclosed and described is an aircraft galley (1) having a plurality of galley inserts (GAINs) (3) and a master aircraft galley control unit (MGCU) (5), wherein the galley inserts (3) are connected to the MGCU (5) via an aircraft galley data bus (galley data bus) (7), and at least one panel (17), wherein the galley inserts (3) each have a status selected from the following group: initialization, standby ON, ON, waiting, interrupted, ended, maintenance, fault, standby OFF or stopped/ended, wherein the aircraft galley (1) also comprises a data collector (15), the data collector (15) is connected to the aircraft galley data bus (7), such that the data collector (15) collects the respective statuses of the galley inserts (3), and wherein the data collector (15) stores information which can be displayed on the panel (17) in accordance with the respective statuses.

IPC Classes  ?

• H04L 12/40 - Bus networks
• B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for

Abstract

The invention relates to a method for removing a two-part connector (2) in a workpiece arrangement (4), comprising the following steps: - providing a workpiece arrangement (4) having a first surface (6) and an opposing second surface (8) and having a hole (10), which connects the first surface (6) to the second surface (8), wherein: a connector (2) is fastened in the hole (10), which connector has a bolt (14) extending along a central axis (16) and a sleeve (12) fastened on the bolt (14); the bolt (14) has a head portion (36) and a shank portion (38) with retaining grooves (42); the sleeve (12) is fastened to the bolt (14) on the side of the second surface (8) in such a manner that the inner surface (74) thereof engages with the retaining grooves (42) and prevents a relative movement of bolt (14) and sleeve (12) parallel to the central axis (16); and the sleeve (12) has an outside diameter which is greater than the diameter of the hole (10) in the workpiece arrangement (4), - cutting the sleeve (12) and/or the bolt (14), and - removing the connector (2) from the hole (10).

IPC Classes  ?

• F16B 19/06 - Solid rivets made in one piece
• B21J 15/02 - Riveting procedures
• B21J 15/50 - Removing or cutting devices for rivets

Abstract

Disclosed is an actuation unit (15) for actuating a foldable wing tip portion (9) of a wing (3) for an aircraft (1), the actuation unit (15) comprising a motor (17) configured to be mounted to a fixed wing (5) for an aircraft (1), a drive pinion (19) driven rotationally by the motor (17), a first rack (21) configured to be mounted to the fixed wing (5), a second rack (23) configured to be mounted to the foldable wing tip portion (9), a third rack (25) configured to be mounted to the fixed wing (5) movably along a defined first movement path (31) and drivingly engaged by the drive pinion (19), and a transfer pinion (27) mounted to the third rack (25) rotatably about an axis of rotation (33) extending perpendicular to the first movement path (31), wherein the first rack (21) engages the transfer pinion (27) at a first side (37) and the second rack (23) engages the transfer pinion (27) at an opposite second side (39) of the transfer pinion (27), such that, when the drive pinion (19) drives the third rack (25) along the first movement path (31), the transfer pinion (27) drives the second rack (23) along a second movement path (41).

IPC Classes  ?

• B64C 3/56 - Folding or collapsing to reduce overall dimensions of aircraft
• B64C 9/00 - Adjustable control surfaces or members, e.g. rudders
• B64C 23/06 - Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
• B64C 13/34 - Transmitting means without power amplification or where power amplification is irrelevant mechanical using toothed gearing
• F16H 19/04 - Gearings comprising essentially only toothed gears or friction members and not capable of conveying indefinitely-continuing rotary motion for interconverting rotary motion and reciprocating motion comprising a rack

Abstract

The invention relates to a method for producing a load-bearing element for a means of transportation, comprising the steps of: - providing a flat base flange, which is made of a first material and has a first surface and a second surface; - applying at least one layer made of at least one second material to the first surface using an application or welding method based on friction; and - machining the at least one layer made of the second material in order to produce a desired profile cross-section of the load-bearing element, the first material and the second material being metal materials that differ from one another.

IPC Classes  ?

• B23K 20/12 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
• B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
• B23K 103/18 - Dissimilar materials
• B23K 101/28 - Beams

Abstract

A flow body for an aircraft, in particular for a wing leading edge device, is proposed, the flow body having a curved front skin having a leading edge and at least one trailing-edge component coupled with at least one spanwise edge of the front skin, wherein the trailing-edge component comprises a constant cross-sectional profile that tapers in a chordwise direction to form two spanwise flow surfaces that end in a trailing edge, and wherein the trailing-edge component is designed for providing a flush transition between the front skin and at least one of the two spanwise flow surfaces.

IPC Classes  ?

• B64C 3/28 - Leading or trailing edges attached to primary structures, e.g. forming fixed slots
• B64D 15/04 - Hot gas application
• B64C 9/24 - Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing by single flap
• B64C 3/14 - Aerofoil profile

Abstract

In order to reduce vibration of movable airfoil structures (38), such as rudders (22), elevators (24), and ailerons (20), a spring device (48), a leaf spring (50) for example, is mounted to an airfoil mounting structure (28), such as a vertical tail plane (16), horizontal tail plane (18) or the wings (14), such that the spring device (48) exerts a force on a cam device (80), which transforms the spring force (F) into an airfoil torque (M). The airfoil torque (M) is applied to the airfoil structure (38) and thus reduces a risk of vibration or flutter. The cam device (80) is configured to redirect the spring force (F) such that when the airfoil structure (38) is moved in a first direction (108), torque decreases and when moved in the opposite second direction (110) the torque is zero.

IPC Classes  ?

• B64C 9/00 - Adjustable control surfaces or members, e.g. rudders
• B64C 9/30 - Balancing hinged surfaces, e.g. dynamically
• B64C 13/38 - Transmitting means with power amplification
• F16F 1/26 - Attachments or mountings
• F16F 1/368 - Leaf springs
• F16F 3/02 - Spring units consisting of several springs, e.g. for obtaining a desired spring characteristic with springs made of steel or of other material having low internal friction

Abstract

A device (1) for manufacturing a composite component comprises a tool (5) with first and second sections (9,11) forming first and second confinement surfaces (29, 31) respectively. The first and second sections are movable relative to each other into and out of a fastening configuration. A closing mechanism (7) with a closing section (15) forms a third confinement surface (25), the closing mechanism being directly or indirectly connected to the tool. When the first and second sections are arranged in the fastening configuration, the first and second confinement surfaces face one another, and the first section, the second section and the closing mechanism are arranged such that a cavity (13) is formed therebetween. The closing section is transferable from an open configuration into a closed configuration. When the closing section is in the open configuration, the volume of the cavity is larger than when the closing section is in the closed configuration. When the closing section is in the closed configuration, the third confinement surface extends along a plane (19) which is arranged perpendicular to each of the first and second confinement surfaces. When the closing mechanism is heated from a first temperature to a second temperature, the closing section transfers from the open configuration into the closed configuration at a predefined temperature.

IPC Classes  ?

• B29C 70/54 - Component parts, details or accessories; Auxiliary operations
• B29D 99/00 - Subject matter not provided for in other groups of this subclass

Abstract

A leading-edge component for an aircraft is proposed, the component comprising at least a part of a flow body having a front skin, a hollow space at least partially delimited by the front skin and at least one separate retention device, wherein the at least one retention device comprises a flexible structure with a mesh, a web, a fabric or a plurality of strings, wherein the retention device is arranged behind the front skin in a distance thereto and extends along a main extension direction of at least a section of the front skin, and wherein the retention device is designed for retaining a front skin that deforms to move into the hollow space upon an impact of a foreign object.

IPC Classes  ?

• B64C 3/28 - Leading or trailing edges attached to primary structures, e.g. forming fixed slots
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for

Abstract

The invention relates to a system (2) and a method for welding two thermoplastic workpieces. The system (2) has an ultrasonic tool (8), a support (10) and a cooling unit (12). The ultrasonic tool (8) is designed to generate mechanical vibrations. The system (2) is designed to clamp together the workpieces in the receiving region (16) by means of the ultrasonic tool (8) and the support (10) if at least one fastening portion (18) of the workpieces (4, 6) opposite one another is arranged in the receiving region (16). The ultrasonic tool (8) is designed to introduce the mechanical vibrations into the fastening portion (18) of the workpieces (4, 6) in order to weld the workpieces (4, 6) in a joining zone (20). The cooling unit (12) is designed to cool, with cooling fluid (22), at least a part of the fastening portion (18) of the workpieces (4, 6) and/or a cooling portion (24) of the workpieces (4, 6) directly adjacent to the fastening portion (18).

IPC Classes  ?

• B29C 65/08 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure using ultrasonic vibrations
• B29C 65/50 - Joining of preformed parts; Apparatus therefor using adhesives using adhesive tape
• B29C 65/00 - Joining of preformed parts; Apparatus therefor

Abstract

The invention relates to a system for automatically adapting operating parameters of an on-board kitchen facility (4) according to provided supply items (5) for on-board catering in a vehicle, in particular an aircraft (100), comprising an on-board kitchen facility (4) having an identification device (8) which is designed to identify a supply item (5); and a control device (3) for controlling the on-board kitchen facility (4), the control device (3) being designed to provide operating parameters for the identified supply item (5) and to operate the on-board kitchen facility (4) according to the operating parameters.

IPC Classes  ?

• B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for
• H05B 1/02 - Automatic switching arrangements specially adapted to heating apparatus
• G06Q 10/08 - Logistics, e.g. warehousing, loading or distribution; Inventory or stock management

Abstract

The invention relates to a layer composite for an aircraft or spacecraft, containing coated first carbon fibers, the coating having an electrically insulating effect.

IPC Classes  ?

• B32B 7/025 - Electric or magnetic properties
• B32B 15/14 - Layered products essentially comprising metal next to a fibrous or filamentary layer
• B32B 15/08 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance of synthetic resin
• B32B 15/20 - Layered products essentially comprising metal comprising aluminium or copper
• B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
• C08J 5/06 - Reinforcing macromolecular compounds with loose or coherent fibrous material using pretreated fibrous materials
• D06M 10/10 - Macromolecular compounds

Abstract

The invention relates to a method for removing a blind rivet (2) in a workpiece arrangement (4), comprising the following steps: - providing a workpiece arrangement (4) having a first surface (6) and an opposite second surface (8) and having a hole (10), which connects the first surface (6) to the second surface (8), a blind rivet (2) being fixed in the hole (10), which blind rivet has a shell (12) and a screw (14) extending through the shell (12), the shell (12) and the screw (14) arranged therein extending coaxially along a common center axis (16), the shell (12) having a shell head portion (22), a straight portion (26), a deformation portion (30) and a threaded portion (32) having an internal thread (34), the straight portion (26) being located in the hole (10) and the deformation portion (30) and the threaded portion (32) protruding out of the hole (10) on the side of the second surface (8), the screw (14) having a screw head portion (36) and a pin portion (38) having an external thread (42), the screw (14) being arranged in the shell (12) such that the internal thread (34) of the shell (12) engages in the external thread (42) of the screw (14) and the deformation portion (30) of the shell (12) is deformed so that the outside diameter of the deformed deformation portion (30) is larger than the diameter of the hole (10), - cutting the shell (12) in the region of the thread portion (32) and/or the deformation portion (30), and - removing the blind rivet (2) from the hole (10).

IPC Classes  ?

• B21J 15/50 - Removing or cutting devices for rivets

Abstract

An aircraft panel assembly with: a panel; and a plurality of stiffeners on the panel. Each stiffener has an attachment part attached to the panel and a structural part spaced apart from the panel. A rib foot beam crosses the stiffeners at a series of intersections. At each intersection the rib foot beam is located between the panel and the structural part of a respective one of the stiffeners.

IPC Classes  ?

• 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
• B29C 43/10 - Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies
• B29C 43/36 - Moulds for making articles of definite length, i.e. discrete articles
• 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 70/84 - Moulding material on preformed parts to be joined
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B64C 3/18 - Spars; Ribs; Stringers
• B64C 3/20 - Integral or sandwich constructions
• B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
• B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
• B64C 1/06 - Frames; Stringers; Longerons
• B64C 1/12 - Construction or attachment of skin panels

Abstract

A leading-edge component (2, 31, 37) for an aircraft (44) is shown, comprising at least a part of a flow body (4) having a front skin (6) and a rib (8), wherein front skin comprises a top section (10), a bottom section (12) and a leading edge (14) arranged therebetween, wherein the rib extends from the bottom section to the top section, wherein the rib comprises a flange (16, 32, 38) that at least partially surrounds the rib, wherein the flange is attached to an inner side of the front skin, and wherein the at least one peripheral surface (24, 40) extends from the contact surface (20) inwardly into the flow body and away from the inner side (18) of the front skin or encloses a weakened connection region (42) with the contact surface for bending inwardly into the flow body upon an impact onto the front skin on or adjacent to the at least one peripheral surface.

IPC Classes  ?

• B64C 3/18 - Spars; Ribs; Stringers
• B64C 3/28 - Leading or trailing edges attached to primary structures, e.g. forming fixed slots

Abstract

An embodiment of the present invention provides an aerostructure assembly of an aircraft comprising a first aerostructure portion (201) extending in a direction between a first position (bl) and a second position (b2) and comprising structurally of at least one rib or spar portion at least partially enclosed by a cover portion; a corresponding second aerostructure portion (203) connected to the first aerostructure portion (201) and extending continuously in the direction from the first aerostructure portion between the second position (b2) and a third position (b3) and comprising structurally of at least one further rib or further spar portion at least partially enclosed by a further cover portion; wherein the first aerostructure portion has a first aerodynamic planform area (SI) and the corresponding second aerostructure portion has a corresponding second aerodynamic planform area (S2); wherein a total aerodynamic planform area of the first aerostructure portion and corresponding second aerostructure portion is equal to the sum of the first aerodynamic planform area (51) and the corresponding second aerodynamic planform area (52); wherein the total aerodynamic planform area and structural component characteristics of the first aerostructure portion (201) and the corresponding second aerostructure portion (203) are defined such that the aerostructure assembly is sized for use on the aircraft; and, wherein the aerodynamic planform area and the structural component characteristics of the first aerostructure portion (201) are in addition sized for use on a second aircraft.

IPC Classes  ?

• B64C 3/18 - Spars; Ribs; Stringers
• B64C 5/02 - Tailplanes
• B64C 5/06 - Fins
• B64C 5/10 - Stabilising surfaces adjustable
• B64C 9/00 - Adjustable control surfaces or members, e.g. rudders
• B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor

Abstract

According to the present invention, a system and a method for evaluating performance of a porous skin of an aircraft is presented. The aircraft comprises at least the porous skin, and a boundary layer control system. The performance evaluation system is characterized by a first sensor providing data related to the performance of the porous skin. The performance evaluation system is further configured to clean the porous skin based on the performance of the porous skin determined using the data received from the first sensor in order to ensure that the porous skin operates at its maximum capability.

IPC Classes  ?

• B64C 21/02 - Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
• B64C 21/04 - Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
• B64C 21/06 - Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for sucking
• B64C 21/08 - Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like adjustable

Abstract

An unmanned ground-based transport vehicle, UGV, includes a housing, having a base plate and at least one housing side wall that is substantially perpendicular to the base plate. Arranged in the housing is at least one wheel drive, which is coupled to at least one wheel. The wheel is arranged in a recess in the base plate. The UGV further includes a plurality of sensors for sensing the environment of the UGV, and a controller for autonomous location and navigation of the UGV on the basis of sensing parameters of the plurality of sensors. The UGV includes at least one load-receiving element that is coupled to the housing side wall and extends outwards from the housing side wall, wherein the load-receiving element comprises a load support surface for supporting an item with respect to a vertical direction which extends transverse to the base plate. The UGV is adapted to exchange data with other UGVs for transporting, in a cooperative manner, a common payload.

IPC Classes  ?

• G05D 1/02 - Control of position or course in two dimensions
• G05D 1/08 - Control of attitude, i.e. control of roll, pitch, or yaw
• B66F 9/06 - Devices for lifting or lowering bulky or heavy goods for loading or unloading purposes movable, with their loads, on wheels or the like, e.g. fork-lift trucks

Abstract

A wing leading-edge device (2, 42) is proposed, which comprises a slat body (4, 42) having a front side (6) with a forward skin (8) and a back side (10) with a rearward skin (12), and at least a drive arrangement (14) having at least one lug (18, 20) and a slat track (16), wherein the back side (10) extends between an upper spanwise edge (26) of the forward skin (8) and a lower spanwise edge (28) of the forward skin (8), wherein the back side (10) is defined by a continuously curved profile contour for receiving a fixed leading edge (32), wherein the at least one lug (18, 20) is at least partially arranged between the back side (10) and the front side (6), and wherein the slat track (16) is coupled with the at least one lug (18, 20). The connection points to the slat body (4, 42) are shifted far forward to improve the load introduction and reduce moments acting on the drive mechanism.

IPC Classes  ?

• B64C 3/50 - Varying camber by leading or trailing edge flaps
• B64C 9/22 - Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing
• B64C 9/14 - Adjustable control surfaces or members, e.g. rudders forming slots

Abstract

In an aircraft, latches, keyed mounting plates, and bi-stable power drive units (PDUs) are used to move and secure cargo within the cargo hold of the aircraft. The latches have a latch head that secures the cargo in the vertical (Z) and lateral (Y) directions and, optionally, a roller to allow movement of the cargo in the longitudinal (X) direction of the cargo hold. One or more of the PDUs are vertically actuatable to selectively engage against and move cargo along a designated path within the cargo hold. The keyed mounting plates ensure that the cargo hold of the aircraft is configured properly and that proper orientation of components installed for moving cargo within the cargo hold are not inadvertently installed in a misconfigured position or orientation.

IPC Classes  ?

• B64D 9/00 - Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
• B64C 1/20 - Floors specially adapted for freight

Abstract

The invention relates to connected components made of thermoplastic fibre-composite materials, said components being connected by pins that are introduced under pressure and rotation into the resultantly pliable matrix material of the components, and also relates to a method for connecting components of this type.

IPC Classes  ?

• B29C 65/02 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure
• B29C 65/56 - Joining of preformed parts; Apparatus therefor using mechanical means
• B29C 65/72 - Joining of preformed parts; Apparatus therefor by combined operations, e.g. welding and stitching
• B29C 65/00 - Joining of preformed parts; Apparatus therefor
• B29C 65/06 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure using friction, e.g. spin welding
• B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof

Abstract

The present invention provides a method for welding thermoplastic components, in particular thermoplastic fiber composite structural components for an aircraft or spacecraft, comprising the following steps: - arranging an insert, which has a conductor structure having a plurality of parallel electrical conductor elements, in a joining zone between a first thermoplastic component and a second thermoplastic component such that at least some portions of the parallel electrical conductor elements are located in the joining zone; - locally melting the components in the region of the joining zone by supplying current to the conductor structure; - disconnecting the conductor elements; and - removing the insert from the joining zone by pulling out the disconnected conductor elements. The present invention also provides an insert for the resistance welding of thermoplastic components, in particular by means of a method of this type.

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"
• B29C 65/20 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure using heated tool with direct contact, e.g. using "mirror"
• B29C 65/30 - Electrical means
• B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
• B29C 65/00 - Joining of preformed parts; Apparatus therefor

Abstract

Disclosed is a leading edge structure (n) for a flow control system of an aircraft (1), comprising a leading edge panel (13) that surrounds a plenum (17), wherein the leading edge panel (13) has a first side portion (21), a second side portion (27) opposite the first side portion (21), an inner surface (33) facing the plenum (17) and an outer surface (37) in contact with an ambient flow (39), and wherein the leading edge panel (13) comprises a plurality of micro pores (45) forming a fluid connection between the plenum (17) and the ambient flow (39), wherein the plenum (17) is connected to an air outlet arrangement (49) configured for causing an underpressure in the plenum (17), so that air from the ambient flow (39) is drawn through the micro pores (45) into the plenum (17) and from there discharged through the air outlet arrangement (49) into the ambient flow (39). The object to provide a simpler leading edge structure with a reduced weight, is achieved in that the air outlet arrangement (49) is configured to operate in a flow control mode where a first mass flow rate of air from the ambient flow (39) is drawn through the micro pores (45) into the plenum (17), and in a cleaning mode where a second mass flow rate of air from the ambient flow (39) is drawn through the micro pores (45) into the plenum (17), wherein the second mass flow rate is greater than the first mass flow rate.

IPC Classes  ?

• B64C 21/08 - Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like adjustable
• B64C 21/02 - Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
• B64C 3/28 - Leading or trailing edges attached to primary structures, e.g. forming fixed slots

Abstract

The invention relates to an aircraft cabin pedestal (10) which is designed for use as a step during a check, installation, maintenance, repair or the like in an aircraft cabin (12). The aircraft cabin pedestal (10) comprises a first step section (14) which has a first step height (16). Furthermore, the aircraft cabin pedestal comprises a second step section (18) which is arranged next to the first step section (14) and has a second step height (20) which is smaller than the first step height (16). In addition, the aircraft cabin pedestal (10) comprises a third step section (22) which is arranged next to the first step section (14) on a side opposite the second step section (18) and has a third step height (24) which is smaller than the first step height (16). Furthermore, the aircraft cabin pedestal comprises a foam core (26) which forms at least one inner structure of the first step section (14), of the second step section (18) and of the third step section (22).

IPC Classes  ?

• B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for
• A47C 12/00 - Step-stools

Abstract

The invention relates to a device (2), comprising: a frame (4), a transfer roller (6) with a circumferential lateral wall (8), a drive unit (10), a slit nozzle (12) with a muzzle end (14) for dispensing lacquer, and a deformation unit (16), wherein the slit nozzle (12) and the deformation unit (16) are each connected to the frame (4), wherein an outside contact surface of the lateral wall (8) comprises several depressions (20), wherein the transfer roller (6) is mounted rotatably about an axis of rotation (22) at the frame (4), wherein the drive unit (10) is configured to drive the transfer roller (6) in a rotation direction of the transfer roller (6), such that the lateral wall (8) continuously passes through a first angular range (26) and the second angular range, each fixed to the frame (4). The deformation unit (16) is arranged to elastically deform the lateral wall (8) resulting in a respective first deformation section (30) of the lateral wall (6) passing through the first angular range (26) and a respective second deformation section (31) of the lateral wall (8) passing through the second angular range (28), wherein the muzzle end (14) of the slit nozzle (12) is arranged in direct contact with or contactless to the outside contact surface (18) at the second deformation section (31) for dispensing lacquer into at least into respective depressions, and wherein the transfer roller (6) is configured to roll on a work surface for transferring the lacquer.

IPC Classes  ?

• B05C 1/02 - Apparatus in which liquid or other fluent material is applied to the surface of the work by contact with a member carrying the liquid or other fluent material, e.g. a porous member loaded with a liquid to be applied as a coating for applying liquid or other fluent material to separate articles
• B05C 1/08 - Apparatus in which liquid or other fluent material is applied to the surface of the work by contact with a member carrying the liquid or other fluent material, e.g. a porous member loaded with a liquid to be applied as a coating for applying liquid or other fluent material to work of indefinite length using a roller

Abstract

The invention relates to a method for the additive manufacturing of flame-retardant workpieces with improved fire behaviour. To this end, polyamide materials are provided which contain a flame retardant, which is selected from one or more of red phosphorus, phosphorus-containing compounds and melamine-based flame retardants. In particular, flame-retardant polyamide materials in powder form which are suitable for selective laser sintering are provided. The workpieces produced by selective laser sintering from these flame-retardant polyamide materials in powder form also have a surprisingly high surface smoothness in addition to the good fire behaviour. A polyamide material consisting of polyamide 6 and red phosphorus is particularly suitable. The workpieces can be used in the interiors of aircraft, in particular in the force-ventilated region.

IPC Classes  ?

• C08J 3/28 - Treatment by wave energy or particle radiation
• C08K 3/32 - Phosphorus-containing compounds
• C08L 77/00 - Compositions of polyamides obtained by reactions forming a carboxylic amide link in the main chain; Compositions of derivatives of such polymers
• B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
• B33Y 70/00 - Materials specially adapted for additive manufacturing

Abstract

Disclosed is flap support (11) for supporting a flap (9) of a wing (5) for an aircraft (1), the flap support (11) comprising a load bearing fairing shell (13) and a reinforcement structure (31) at least partially received in the interior space (27) of the fairing structure (13) and mounted to the first and second side wall portions(21, 23) of the fairing shell (13), wherein the fairing shell (13) comprises a front attachment device (33) configured for attachment to a main wing (7), wherein the reinforcement structure (31) comprises an aft attachment device (63) configured for attachment to the main wing (7), and wherein the flap support (11) further comprises a hinge device (39) configured for forming an articulated connection to the flap (9). The object, to provide a particularly strong and at the same time lightweight flap support, is achieved in that the hinge device (39) forms part of the reinforcement structure (31).

IPC Classes  ?

• B64C 9/02 - Mounting or supporting thereof
• B64C 7/00 - Structures or fairings not otherwise provided for
• B64C 9/16 - Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing

Abstract

The invention relates to a preparation for pre-treating titanium or titanium alloy surfaces comprising 200 to 400 g/l NaOH and 10 to 150 g/l MGDA in water, wherein the preparation has a pH value of at least 12.

IPC Classes  ?

• C23C 22/64 - Treatment of refractory metals or alloys based thereon