Abstract: A ground propulsion assembly for an aircraft includes an axle, a wheel rotatably connected to the axle, and a transmission. The transmission includes a housing mounted proximate the axle and a drive element disposed at least partially outside of the housing and operatively connected to a power input. A mounting bar extends between the axle and the transmission and a mounting bar first end is rigidly connected to the axle, and the transmission is pivotally connected to a mounting bar second end. A spring is disposed between the transmission and the axle and the spring is configured to urge the drive element out of engagement with the wheel. An actuator is operatively connected between the transmission and the axle, and is configured to selectively generate a force in opposition to the disengagement spring such that the drive element moves relative the wheel and operatively engages the wheel.

Abstract: An electro hydrostatic actuator system for retracting/extending a landing gear includes a plurality of hydraulic actuators, a plurality of hydraulic supply sources each including a single hydraulic pump and a single electric motor, provided in parallel to each other and joined at the downstream ends, a plurality of switching valves provided in parallel on a supply path that connects the hydraulic actuators to a junction of the hydraulic supply sources, and a controller configured to sequentially operate the hydraulic actuators. The hydraulic supply sources each include a check valve which prevents operation oil from flowing toward the hydraulic pump. In a normal state, the hydraulic supply sources together supply operation oil sequentially to the hydraulic actuators. When any of the hydraulic supply sources is failed, the other hydraulic supply source(s) other than the failed hydraulic supply source supplies operation oil sequentially to the hydraulic actuators.

Abstract: A window body constituting a window of an aircraft includes an electromagnetic shield film, and a conductive paint is applied to an outer perimeter edge face of the window body. A fixing member secures the window body to an airframe with a gasket seal and a window frame interposed therebetween. The fixing member has a first bonding surface on which a conductive film is formed. The first bonding surface is in direct contact with the gasket seal. An electrical path is formed through the electromagnetic shield film, the conductive paint, the gasket seal, the fixing member, and the window frame.

Abstract: In some embodiments, an actuation system includes a plurality of threaded member portions, a plurality of roller nuts, a driving member configured to receive mechanical energy from a power source, a plurality of driven members, and a magnetorheological (MR) fluid disposed between the plurality of driven members and at least one braking surface. An output member may be coupled between the rotor system and either the plurality of threaded member portions or the plurality of roller nuts and configured to translate linearly in response to the threaded member portions advancing or receding within the roller nuts.

Abstract: An aeroplane includes a fuselage having a pair of hydrofoils providing hydrodynamic lift and stabilization arranged in the form of an inverted V. The junction between each hydrofoil and fuselage is situated forward the center of gravity of the aeroplane. The distance separating the junction between each hydrofoil and the fuselage, with respect to the center of gravity of the aeroplane is comprised between 0 and 170% of the mean aerodynamic chord of the main wing of the aeroplane, preferably between 20% and 135%. Each hydrofoil is inclined downwards, from its leading edge in the direction of its trailing edge. The straight line connecting these two edges form, a nominal pitch angle comprised between 2 and 12°, preferably between 6 and 8°. A part of the hydrofoil is located beneath a horizontal tangential plane of the aeroplane; each hydrofoil has a flexible intermediate section allowing the hydrofoil to flex upwards.

Abstract: The present invention concerns a device for use in an aircraft fuel pressure sensor line. More particularly, but not exclusively, this invention concerns a fuel pressure sensor line connecting an aircraft fuel pump to a pressure sensor. The invention also concerns a fuel pressure sensor line reservoir for use with a sensor line connecting an aircraft fuel pump to a pressure sensor. An aircraft fuel pump system comprises an aircraft fuel pump and a pressure sensor connected the aircraft fuel pump via a sensor line. The sensor line includes a reservoir located between the aircraft fuel pump and the pressure sensor. The reservoir acts to prevent liquid contacting the pressure switch when the fuel pump is not active.

Abstract: Methods and Apparatus to point a payload at a target are disclosed herein. An example method includes estimating a first orientation of a base of a payload to point the payload at a target. The base is coupled to a satellite via a pivot joint and a linear actuator. The linear actuator is to enable adjustment of an azimuth angle and an elevation angle of the base. The example method further includes communicating a command to actuate the actuator to move the base to the first orientation and determining a base orientation error. The base orientation error is a difference between the first orientation and a second orientation of the base to which the actuator moves the base in response to the command. The example method also includes determining a stroke position error of the actuator based on the base orientation error.

Abstract: An electrical and electronics bay of an aircraft has at least two rows of systems elements, each row being separated by a single corridor extending an entire longitudinal length of the electrical and electronics bay and being devoid of the systems elements. Each row has at least one set of systems elements and at least one electrical power center, wherein the systems elements are arranged in cabinets. At least one of the cabinets includes at least one removable mobile shelf for allowing access from a front to the back of the cabinets. Bottom edges of back faces of the cabinet are arranged against the fuselage to remove an additional corridor at the back of the cabinet, and front faces of the cabinet are directly accessible from the single corridor.

Abstract: A protection device (20) for protecting a fuselage (2) of a rotorcraft (1) against a pyramid-shaped structure (10) for carrying a load, which pyramid-shape structure has a frame having a quadrilateral shape together with a first pair (13) of two arms (12) and a second pair (15) of two arms (14), each arm extending in elevation from the frame up towards an apex (16). The protection device includes a protective plate (21), a blade (30) secured to the protective plate (21) for exerting a force on the two arms of the first pair, and a chevron (40) provided with two branches connected to the protective plate (21) in order to tend to move the arms of the second pair transversely apart from each other.

Abstract: An aircraft structural assembly includes an area element which has a core and an outer layer. A first surface of the area element is convexly curved, at least in certain sections, relative to an imaginary central area of the area element extending through the core of the area element. By contrast, a second surface of the area element located opposite the first surface is oriented, at least in certain sections, parallel to the imaginary central area of the area element extending through the core of the area element. The area element is configured in the form of a floor panel of a floor system. The first or the second surface of the area element is designed to form a walkable floor surface of the floor system in the state of the aircraft structural assembly when mounted in an aircraft.

Abstract: A cabin attendant seat including a carrier element which comprises a backrest section and a base section that carries the backrest section and a seat element fastened to a front side of the carrier element. At least one first stowage compartment is integrated into the carrier element. An inclined section of a rear wall of the carrier element is inclined, at least along a section of the first stowage compartment integrated into the carrier element, in such a way that a cross-sectional area of the carrier element increases in the direction of the base section of the carrier element.

Abstract: The invention relates to a compound helicopter comprising a fuselage, at least one engine and a main rotor driven by said at least one engine. At least one pair of fixed wings are mounted in an essentially horizontal plane on a left hand and a right hand side of the fuselage and horizontally oriented propulsion devices are mounted to each of the fixed wings, the fixed wings encompassing each a drive shaft from the at least one engine. Each fixed wing comprises a lower main wing and an upper secondary wing being connected to each other within an interconnection region. The propulsion devices include pusher propellers arranged at the interconnection region and the upper secondary wing houses the drive shaft from the at least one engine.

Abstract: A front landing gear system for an aircraft including a swing arm rotatively coupled to a wheel, a forward link arm rotatively coupled to the swing arm, a oleopneumatic cylinder rotatively coupled to the swing arm, second extension arm and a bulkhead, a plate rotatively coupled to the bulkhead, an actuation device rotatively coupled to the bulkhead and to the plate, where refraction of the linear actuation device causes the plate and extension arms to move upward towards the bulkhead.

Abstract: A main landing gear system for an aircraft including a truss element, a first support unit and second support unit affixed to the truss on opposing sides of the truss, a first actuator and a second actuator rotatively affixed to respective first support unit and second support unit and to a respective first wheel and second wheel, a first trailing link and second trailing link each coupled to the respective first wheel and second wheel, a first extension plate and second extension plate each rotatively coupled to the respective first trailing link and second trailing link and to a side of the truss, a first plate locking unit and second plate locking unit rotatively affixed to an end of the respective first extension plate or second extension plate and to a side of the truss.

Abstract: An apparatus and method for attachment of a payload or store to the external surface of an aerial vehicle includes a single point release feature. The apparatus includes an elongated base having a first distal end and a second distal end. A retention receptacle including a hollow tube is disposed adjacent the first distal end and is configured to removably receive and retain the store or payload. In addition, a release receptacle housing a release mechanism assembly is disposed adjacent said second distal end. When the release mechanism assembly is in the closed and locked position, the store or payload is retained to the vehicle via a spring loaded lock pin advanced into the retention receptacle. When the release mechanism assembly is in the open and unlocked position, the store or payload may be disengaged from the vehicle.

Abstract: According to one embodiment, an apparatus includes an optical sensor having one or more thermally sensitive components. The sensor is gimbal mounted on a space or air-borne vehicle and includes a heat sink component thermally coupled to the one or more thermally sensitive components via at least one heat strap and configured to at least passively receive and store thermal energy from the one or more thermally sensitive components without use of a motorized thermal energy transfer device. The apparatus also includes a radiator configured to receive thermal energy from the heat sink component and to dissipate thermal energy to an ambient environment. The radiator is disposed on a first side of an optical path of the sensor opposite a second side of the optical path on which the heat sink component is disposed. The heat sink component is configured to at least partially balance a center-of-gravity of the sensor.

Abstract: Embodiments include an aerial vehicle. Two winged surfaces are provided in communication with a fuselage. The surfaces are in communication at a front edge via a cuff, at a midsection via a first resilient member, and at a trailing edge via a second resilient member. As the aerial vehicle is in flight, it is subject to loads. The connections of the surfaces provides flexibility and resiliency to maintain the surfaces in communication with the fuselage and to allow regulated separation of the winged surfaces at their rear edges in a first direction in a first flexed state and at their front edges in a second direction, different from the first direction, in a second flexed state.

Abstract: An emergency pod configured for use with a rotary wing aircraft is provided including a rigid, generally hollow shell. An inflatable raft is arranged within an interior portion of the hollow shell. The life raft is coupled to an inflation mechanism. A first activation device and a second activation device are operably coupled to the inflation mechanism, the second activation device being disposed within the shell and fastened to a movable portion of the shell, wherein the first activation device and the second activation device operable independently of one another. Inflation of the inflatable raft is initiated when a force is applied to one of the first activation device and the second activation device.

Abstract: A moveable control surface mounting rib assembly (110) comprises a rib (144) which is attached to one side of a spar member (112) and a stiffener (160) attached to another side of the spar member. The stiffener abuts the upper and lower flanges of the spar member in order to react the loads. The invention is applicable to the mounting of any movable control surface.

Abstract: A mounting apparatus includes a fixed mounting structure that includes a first fixed fitting including a plurality of first flanges and a second fixed fitting. A rotatable mounting structure has a swivel fitting configured to engage and swivel with respect to the first fixed fitting. The swivel fitting includes a plurality of second flanges, one of which is configured to rest on one of the plurality of first flanges when the swivel fitting and first fixed fitting are engaged. The rotatable mounting structure also has a slide fitting configured to slide with respect to the second fixed fitting based on the swivel fitting being engaged with the first fixed fitting. An adjustment assembly is arranged at an interface between the second fixed fitting and the slide fitting. The adjustment assembly is configured to adjust an angular position of the slide fitting relative to the swivel fitting.