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WO/2014/113426A1 |
A main landing gear system for an aircraft including a truss element including a front portion joined to a rear portion, a first support unit and second support unit affixed to the truss at the junction of the first portion and the secon...
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WO/2014/108503A1 |
The invention concerns a tubular fusible member (21) extending along a longitudinal axis (AL), intended to engage in a double yoke (14) and in a single yoke (12) to form a hinge (11). According to the invention, the fusible member (21) i...
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WO/2014/106425A1 |
An aircraft turning over-travel detection device (100) comprises: an over-travel push rod (20) and a detection assembly, the detection assembly comprising a target (40), a proximity sensor (30), a sleeve (60), an energy storage spring (5...
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WO/2014/102437A1 |
The invention relates to an improvement to the control system for landing a VTOL unmanned aircraft on a moving platform, comprising the addition of: a sensor-based control system, said sensors measuring the tension of the cable that conn...
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WO/2014/105894A2 |
An electric connector assembly is provided that is designed to provide a simple and reliable electric connection between a source of electric power on an aircraft and a plurality of electrical connections, such as those from stator windi...
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WO/2014/090334A1 |
Wheel drive unit for attachment to an aircraft running gear, said wheel drive unit including a drive motor (22) or a drive motor (22) with subsequent transmission (24) and comprising the following features: a mounting component (10) adap...
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WO/2013/062312A9 |
The present invention relates to a flying submarine probe, comprising: airplane-type wings arranged at the left and right sides of an enclosed hull, such that the wings are adjustable in the horizontal and vertical directions by up to 18...
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WO/2014/086670A1 |
Wheel motorizing system, notably for allowing an aircraft to run along the ground, comprising an electric motor (5), a drive member (6) secured to the hub (7) of the wheel (2), and a clutch device (10) connecting the output shaft (5a) of...
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WO/2014/083317A1 |
A landing gear assembly comprising a first part (12b) movable relative to a second part (14b), and a spring (26) coupled to the first and second parts via first and second anchor points. A lost motion assembly (30, 31) is provided to ena...
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WO/2014/083170A1 |
The invention relates to an aircraft landing gear comprising: a strut (12) intended to be articulated to a structure of the aircraft in order to be able to move between a deployed position and a retracted position, a brace strut (15); a ...
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WO/2014/076485A1 |
An aircraft landing gear longitudinal force control system (20) for an aircraft having landing gears with braking and/or driving wheel(s). The system includes an error- based force controller (21) having feedback for minimising any error...
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WO/2014/076486A1 |
The present invention provides a landing gear force and moment distributor system (20) for an aircraft having a landing gear including a pair of bogies arranged symmetrically about the longitudinal axis, each bogie having an actuator arr...
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WO/2014/062276A2 |
In specific embodiments, a vehicle propellable through fluids comprises a main work section and a plurality of propulsion units. The main work section includes a payload support hub, a payload support structure rotatable in 360 about the...
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WO/2014/062275A2 |
In specific embodiments, a vehicle propellable through fluids or along surfaces, comprises a main work section and a plurality of propulsion units for propelling the main work section. The main work section supports one or more payloads....
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WO/2014/057046A2 |
The invention is aimed at an aerial vehicle (10) of mini‑drone or micro‑drone type, of the remote‑operated, fixed‑wing type, comprising propulsion means, the aerial vehicle (10) comprising means (20) of attachment to a support (2...
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WO/2014/053726A1 |
The invention concerns a device (10) for receiving an aircraft, and in particular a helicopter when it lands. The invention is characterised by the fact that the device comprises at least one main inflatable pouch (12, 18) comprising a m...
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WO/2014/055269A1 |
A system for configuring landing supports of a load to land on uneven terrain includes a terrain sensor configured to detect a terrain characteristic of the uneven terrain. The system further includes landing supports configured to suppo...
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WO/2014/049328A1 |
An airflow modification patch (14) for reducing aeroacoustic noise generated by an aircraft assembly. The patch has a substrate (14a) and a plurality of airflow disruption elements (14b).
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WO/2014/046564A1 |
In the proposed method, each landing gear wheel is rotated with the aid of one of the radial- or axial-type air turbines which are mounted on said wheel, rotate in opposite directions and to which compressed air from the main engines ...
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WO/2014/041342A1 |
A landing gear assembly (10) having first and second parts (12b, 14b) movably mounted with respect to one another. The landing gear assembly includes a critical space (32). A spring assembly (26) is arranged to bias the first and second ...
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WO/2014/029962A1 |
A brake assembly for a vehicle comprising a wheel (2) comprising a hollow section (4) and a rim (6), the rim (6) comprising a first portion (9) comprising an electrically conductive material (8) and a second portion (10) adjacent to the ...
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WO/2014/023941A1 |
The present invention provides drive systems for rotating one or more wheels (16) of an aircraft landing gear (10) for the purposes of ground taxiing and/or spin-up prior to landing. The drive system includes a motor (52) operable to rot...
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WO/2014/023939A1 |
The present invention provides drive systems for rotating one or more wheels (16) of an aircraft landing gear (10) for the purposes of ground taxiing and/or spin-up prior to landing. A first aspect provides a drive system for rotating a ...
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WO/2014/018196A1 |
A landing gear tire traction control system and methods are presented. An outer tire (306) of an aircraft wheel is depressurized to a depressurized state in response to a non- optimal aircraft landing condition. An inner rotor (314) of t...
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WO/2014/014136A1 |
The aircraft capable of takeoff/landing via the fuselage thereof and the takeoff/landing system of the aircraft according to the present invention are configured such that multiple takeoff/landing rollers are arranged in a sliding direct...
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WO/2014/009616A1 |
The invention relates to a device for opening and closing a hatch of an aircraft gear casing (1) comprising at least one hatch (4) and a plurality of hinges (6a, 6b, 6c) linking the hatch (4) to the structure (8) of the aircraft and capa...
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WO/2014/007705A1 |
The present invention relates to a landing arresting system for vertical take-off and landing (VTOL) aerial vehicles(1) comprising a landing and take-off platform(6) and at least one VTOL locking member (4) having a projecting portion (3...
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WO/2014/001757A1 |
An aircraft landing gear comprises a wheel rotatable about an axle, a motor, and a bi-directional overrunning clutch (30), operable to either connect or disconnect the wheel from the motor. The bi-directional clutch comprises a ring-shap...
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WO/2013/190087A1 |
The invention relates to an electric circuit suitable for cutting off an electric power supply of an electrical device, said electric circuit receiving as input at least two discrete electrical signals, the values of which condition the ...
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WO/2013/184656A1 |
An actuator assembly includes an actuation member, a release member, and a source of pressurized gas, wherein during a normal mode of operation, the actuation member and the release member are engaged to move in unison, and wherein durin...
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WO/2013/179025A1 |
An aircraft landing gear arrangement is provided comprising: a first landing gear portion (2) comprising one or more wheels, a second landing gear portion (3), the first landing gear portion being rotatable with respect to the second lan...
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WO/2013/178999A1 |
A system for indicating the pressure in an aircraft landing gear shock absorber is provided, the system comprising a source of collimated light and a target, the source of collimated light being attached to the aircraft, and being operab...
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WO/2013/179710A1 |
A control device (20) of an aircraft steering apparatus, for controlling an aircraft steering apparatus (1) comprising: an operation part having a rudder pedal (4) provided in a cockpit of an aircraft, a main pilot steering wheel (2), an...
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WO/2013/179026A1 |
An aircraft landing gear arrangement is provided comprising: • a first landing gear portion (2) comprising one or more wheels, • a second landing gear portion (3), the first landing gear portion being rotatable with respect to the se...
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WO/2013/175167A1 |
An aircraft brake assembly comprising a support leg (3), a main wheel (4) rotatably mounted on the support leg (3), a brake (2) comprising a first sub-assembly fixed to the main wheel (4) and a second subassembly (6) moveably mounted on ...
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WO/2013/144589A1 |
An aircraft landing gear (10) which includes a noise-inducing region (12) and a cover (14). The cover comprises a cover portion (14a) arranged to enclose the noise-inducing region to inhibit an airflow negotiating the noise-inducing regi...
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WO/2013/144479A1 |
Device (210) for supplying electrical power to an aircraft on the ground, comprising two electric generator (216, 218) driven by an auxiliary power unit (220), characterized in that the first generator is connected by connection/disconne...
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WO/2013/133839A1 |
A landing gear for an aircraft. The landing gear may have a wheel/truck assembly (404), an oleo strut/support frame (402) for supporting the wheel/truck assembly, and a retraction assembly (410) attached to the oleo strut/support frame, ...
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WO/2013/132114A1 |
The invention relates to an automatic system of fastening a mobile surface for vertical take-off and landing aerial vehicles (1), and methods of taking off and landing. The system comprises: a landing carriage (2) having suction means (3...
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WO/2013/123993A1 |
A drive unit (40) for an aircraft ground wheel (Ί 2) associated with a brake unit (30) for braking the ground wheel (12) is disclosed, the drive unit (40) comprising a driving motor (42) being drivingly coupleable to the ground wheel (1...
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WO/2013/124636A1 |
A landing gear (10) for an aircraft having a main fitting (12) arranged to be coupled to the aircraft and arranged to move between a stowed condition and a deployed condition and a trailing arm (14) movably coupled to the main fitting (1...
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WO/2013/117607A1 |
The invention relates to a steering actuator piston with a rack (6) for an aircraft landing gear (1). The piston comprises a body (18) made of light alloy having an externally threaded main section (11) ending at one end in a shoulder (1...
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WO/2013/117902A1 |
An aircraft landing gear including wheels and a fairing arranged to be moveable between a first and a second configuration, wherein in the first configuration the fairing is arranged to shield an element of the landing gear from incident...
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WO/2013/112206A1 |
The present invention's side-arm recovery system enables large Unmanned Aircraft Systems (UASs) to operate from small vessels or from ground sites with a minimal footprint. The side-arm recovery system allows arresting an UAS independent...
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WO/2013/107650A1 |
The invention relates to a component consisting of or having at least one fiber composite material. The component is an aircraft landing gear or a part of an aircraft landing gear, in particular of an airplane. According to the invention...
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WO/2013/107651A1 |
The invention relates to a drag brace (1) for a landing gear. According to the invention, the node elements (12, 14) consist of a metal material, and the connecting elements (16) which connect the node elements consist of a fiber composi...
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WO/2013/106010A1 |
A system for use in monitoring, measuring, recording, computing and transmitting the oxygen levels and identification of oxygen contamination within an aircraft telescopic landing gear strut (7). An oxygen sensor (21) is mounted in relat...
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WO/2013/083732A1 |
Aircraft landing gear strut (1) comprising a tubular part (3) to accept a shock absorber and an axle bearer part (2) situated at the end of the tubular part (3) and designed to accept a landing gear wheel support mechanism. The tubular p...
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WO/2013/084011A1 |
This system consists of a motion-generating mechanism (i.e. a mechanism setting the aircrafts' wheels to rotate), consisting of a hydraulic motor (chosen from compatible hydraulic motor types shown in Fig. 1, 2, 3 and 4) as well as of an...
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WO/2013/075210A1 |
A metering pin assembly, for use in an aircraft landing gear shock absorber, that is operable to move within the shock absorber, independently of the shock absorber, to respond to movement of the landing gear under subjected load.
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