Abstract: The present invention provides a fireproof bulkhead, having a highly porous structure with an intumescent coating, the highly porous structure being formed as a reticulated foam or as a highly porous pimple or nub structure.

Abstract: An air vehicle comprises a vehicle body and a propulsion assembly. The vehicle body has the shape of a wing airfoil to generate lift when air flows over the vehicle body. The vehicle body has a body longitudinal axis and substantially planar port and starboard sides of composite material, and includes first and second hulls that are secured together side-by-side, the hulls having longitudinal axes that are substantially parallel to the body longitudinal axis and two substantially planar side walls at least one of which is of composite material. Each hull defines a separate fluid chamber that is filled with a fluid that is at least partially buoyant. The propulsion assembly is secured to the vehicle body port and starboard sides. The propulsion assembly includes port front and rear engines and starboard front and rear engines, wherein at least two of the engines have independently controlled thrust vectors.

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 method and apparatus for draining fluid from a structure on an aircraft. The apparatus comprises a drainage tube, a housing, a number of inlet holes in the housing, and a number of outlet holes in the housing. The drainage tube has first end that connects to a structure on an aircraft and a second end opposite the first end. The housing connects to the structure. The drainage tube is located within the housing. Air flows into the housing during flight of the aircraft through the number of inlet holes in the housing. The air flows out of the housing during flight of the aircraft through the number of outlet holes. The air flowing into the housing through the number of inlet holes and out the housing through the number of outlet holes directs fluid out of the drainage tube and away from the structure during flight of the aircraft.

Abstract: A helicopter with a fuselage (4), at least one engine, a roll axis, at least one main rotor, and at least one housing (2) mounted to said fuselage (4). An air inlet (8) and an air outlet (7) are provided along at least a part of a circumference of the at least one housing (2), said air inlet (8) and said air outlet (7) being formed by angularly offset and separate gaps between an inside segment (33) and an outside segment (34) essentially extending respectively longitudinally in direction of said roll axis. At least one rotatable compressor (1) with a plurality of airfoil blades (6) is provided radial inside said at least one housing (2) between said air inlet (8) and said air outlet (7), said at least one rotatable compressor (1) being drivable by said at least one engine about a fan axis (5) and each chord of said airfoil blades (6) is essentially radial oriented with regard to said fan axis (5).

Abstract: A self transportable aerostat system comprising: a first motorized mooring truck; a mooring tower removably attached to a base assembly of the first mooring truck, generally vertically arranged in relation to the bed of the first mooring truck; a proximal and distal boom deck removably attached to the base assembly; a flying sheave for redirecting a tether carried by the base assembly and attachable to an aerostat; a second motorized mooring truck attachable to the outer edge of the distal boom; and, an aerostat truck having an electrical connection for connecting to the first mooring truck and having an aerostat storage compartment for storing the aerostat is a retracted configuration.

Abstract: An assembly having an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis, and a blocking device. The blocking device comprises a nut screwed onto an extension of the second sleeve and comprising an inner shoulder acting as a stop for a second end of the articulation spindle, at least two locking washers engaging with the nut, a tab washer comprising an element immobilizing it in rotation with respect to the second arm of the clevis, and for each locking washer, a blocking element limiting the rotational movement of the locking washer with respect to the tab washer.

Abstract: A flying electric generator for obtaining power from wind currents which includes a fuselage having fore and aft portions and an intermediate portion, a rotor assembly including at least two forward rotors mounted on a pair of forward extending support arms extending from the fuselage and at least two rear rotors mounted to a pair of rearward extending support arms extending from the fuselage and at least one first forward wing mounted to a forward portion of the fuselage and extending outwardly on opposite sides of the fuselage and at least one second rear wing mounted to a rear portion of the fuselage and extending outwardly on opposite side of the fuselage.

Abstract: A sealing member for forming a seal in an aircraft, the sealing member comprising: a sealing material; and a stiffening element which provides structural support to the sealing material and comprises a material with a glass transition temperature below +50° C. The stiffening element is relatively flexible when the aircraft is at low altitude (high temperature) but becomes relatively stiff (increasing resistance to seal flutter) when the aircraft is at cruise altitude (low temperature).

Abstract: A mission pod system for an aircraft set to perform a mission includes a fixed portion that is fixedly secured to an exterior surface of the aircraft. The mission pod system also includes a modular portion that is removably secured to the fixed portion and spaced away from the exterior surface of the aircraft via the fixed portion. The modular portion includes an entirety of mission-specific components.

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: A propulsion system for the orbital control of a satellite with terrestrial orbit travelling with a speed of displacement along an axis V tangential to the orbit comprises two propulsion assemblies, fixed to the satellite facing one another with respect to the plane of the orbit, each of the propulsion assemblies comprising two propulsion modules; each of the propulsion modules successively comprising: a motorized link for rotation about an axis parallel to the axis V, an offset arm, and a platen supporting a propulsion unit able to deliver a thrust oriented along an axis perpendicular to the axis V; the two propulsion modules of each propulsion assembly being linked to the satellite on either side and substantially at equal distances from a plane perpendicular to the axis V passing through a centre of mass of the satellite.

Abstract: One example of a torque transfer system for a rotorcraft includes a first rotational joint connected to a rotorcraft rotary shaft. The first rotational joint receives a portion of a torque generated by rotation of the rotorcraft rotary shaft and transfers the portion of the torque to a rotorcraft rotating component. The torque transfer system also includes a second rotational joint of a different type connected to the rotorcraft rotary shaft. The second rotational joint receives a remainder of the torque generated by the rotation of the rotorcraft rotary shaft and transfers the remainder of the torque to the rotorcraft rotating component.

Abstract: The present invention is an aircraft wing design that creates a bell shaped span load, which results in a negative induced drag (induced thrust) on the outer portion of the wing; such a design obviates the need for rudder control of an aircraft.

Abstract: In the context of the wings of aircraft, the ability to compensate for variations in movement and to absorb assembly tolerances, and flexibility for mounting, are all desired. An object of the disclosure thus relates to a wing portion of an aircraft, having a connecting device between a rigid structure and a flexible structure, the connecting device being attached to a structural element of the wing portion via the intermediary of an attachment support, wherein the attachment support is mounted in translation on the structural element by at least one translation spindle. The disclosure is applicable in the field of aeronautics, in particular for the hydraulic equipment of an aircraft.

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: According to one embodiment, a radial fluid device comprises a cylinder block, first and second pluralities of pistons, a first cam disposed about the first plurality of radially extending cylinders, and a second cam disposed about the second plurality of radially extending cylinders. The direction of rotation of the second cam is independent of the direction of rotation of the first cam.

Abstract: A temporary control fin stop system employs a housing coupled to a vehicle. At least one tang is coupled to the housing and positioned to engage a trailing edge of a fin. The tang is ablatively erodible at a predetermined temperature induced by a flight profile of the vehicle to allow unconstrained motion of the fin.