Abstract: A thin membrane structure for stabilizing a spacecraft is provided. The spacecraft has a first end and a second end. The spacecraft has a center of pressure and a center of gravity. The thin membrane structure comprises a module secured to the spacecraft and a structure having a polygonal base and a plurality of triangular side panels meeting in a point opposite the base with the point secured to the module. Prior to deployment, the structure is entirely contained within the module. Subsequent to deployment, the structure expands to a pyramidal shape with the distance between the center of pressure and the center of gravity increasing to a length greater than approximately one-half the length of the spacecraft.

Abstract: An air vehicle, as well as a method for folding an air vehicle for storage, may include a fuselage and a wing connected to the fuselage. The wing may include two ends positioned opposite from each other, and the wing may be substantially perpendicular to the fuselage. At least one of the ends may define a space therebetween the fuselage and the wing. The space may be sized to receive a potion of the wing when the wing is wrapped around the fuselage.

Abstract: A crew bunk system may include a bunk frame assembly and at least two vertically spaced crew berths. Each one of the crew berths may have a lengthwise hinge line dividing the crew berth into a stationary panel and a foldable panel. The stationary panel may be fixedly coupled to the bunk frame assembly. The foldable panel may be hingedly coupled to the stationary panel along the hinge line. The crew bunk system may include at least one connecting member interconnecting the foldable panels such that the foldable panels pivot in unison between a deployed position and a stowed position. The crew bunk system may include a latching mechanism configured to lock the foldable panels in the stowed position.

Abstract: An aircraft fuel system including a fuel line for carrying liquid fuel, and a microwave energy transmitter for energizing water carried in the fuel line. Also, a method of suppressing ice formation in an aircraft fuel system, the fuel system including a fuel line carrying liquid fuel, and a microwave energy transmitter, the method comprising transmitting microwaves along the fuel line to energize water carried with the fuel in the fuel line.

Abstract: A composite material elongate structural member, such as a spar, for use in an aerospace structure, comprises a web disposed between upper and lower flanges. The web may include a clockwise twist about an axis parallel to the length L at a first portion towards the wing-root-end of the spar and a counter-twist in the anticlockwise direction at a second portion towards the wing-tip-end of the spar. The geometry of the spar may vary non-linearly along its length (L) so that the developed width of the spar as measured from a distal edge of the upper flange via the web to a distal edge of the lower flange varies linearly with increasing distance along the length (L). The risk of causing, during fabrication of the spar, undesirable creasing, stressing or stretching of composite material layers in a region in which the geometry of the member varies non-linearly may be reduced by means of such an arrangement.

Abstract: A composite material elongate structural member, such as a spar or stringer, for use in an aerospace structure, comprises a web having an angled portion, for example in the form of a chamfer, curved surface or the like, which joins a foot of the member to the rest of the web. A first surface on the foot is shaped to abut a structure to be stiffened. The foot also has a second surface opposite the first surface. The web has a third surface and a fourth surface at the same layer in the composite material as the first and third surfaces, respectively. On/in the interposed portion there is a fifth surface which joins the first and third surfaces. The geometry of the member may vary along its length (L) so that with increasing distance, the first surface is displaced towards the second surface as the width of the fifth surface decreases.

Abstract: A multi layer composite L-shaped stringer for use in an aerospace structure comprises a foot and a web extending from an edge of the foot. A first surface on the foot is shaped to abut a structure to be stiffened. The foot also has a second surface opposite the first surface. The web has a third surface and a fourth surface at the same layer in the composite material as the first and third surfaces, respectively. The geometry of the stringer may vary along its length (L) so that as the first surface is displaced towards the second surface, the fourth surface is displaced towards the third surface. The developed width (DW) from the distal edge of the foot to the distal edge of the web of the stringer may be substantially constant for all cross-sections along a length of the stringer.

Abstract: A fuselage segment of an aircraft fuselage is provided with an outer skin and an inner skin that are spaced apart from one another by a core, wherein conduits for system installations are integrated into the core, as well as a method for manufacturing such a fuselage segment.

Abstract: An aircraft (1) having a fuselage (2), a power plant (10), a rotary wing (15) having at least one main rotor (16), and a fixed wing (20) comprising two half-wings (21, 22) extending on either side of the fuselage (2). The aircraft (1) also has at least two propulsive propellers (30) on either side of the fuselage (2). Each is positioned on respective ones of the half-wings (21, 22), and an anti-torque and yaw-control tail rotor (35). A transmission system (40) connects the power plant (10) to each main rotor (16) and the tail rotor (35). The transmission system (40) connects the power plant (10) to each propeller (30) via a respective differential mechanism (50) that is controllable on request so that each propeller (30) can be driven in cruising flight and need not be driven in rotation by the power plant (10) on the ground or while hovering.

Abstract: A fairing (1) for a structural element of a rotorcraft, the fairing including a rear portion (2) that is substantially orthogonal to the longitudinal direction (L) of the aircraft, extending between two spaced-apart trailing edges (3, 4) and thus presenting a determined width, said rear portion (2) closing at least part of the internal volume defined by the fairing (1) and generating aerodynamic drag in forward flight. According to the invention, the rear portion presents, at least at the trailing edges (3, 4), a shape that is perturbed on the streamlines (5) of the air-flow.

Abstract: A device for mounting an aircraft engine, including a rigid structure, an engine attachment including a connecting plate superposed to an associated connecting plate of said rigid structure, and means for mutually tightening said plates comprising at least one wedge-effect tightening block and corresponding bearing surfaces of said plates which are conformed so that, when each tightening block is applied against said bearing surfaces along a direction parallel to the plane of the contact surface between both of these plates, this block exerts by a wedge-effect a force for tightening these plates against each other along a direction perpendicular to said plane.

Abstract: A high capacity broadband service is provided from an Earth orbiting satellite having a payload that includes multiple large antennas, the satellite having an inverted configuration when deployed on orbit. The satellite has an aft surface proximate to a launch vehicle structural interface, a forward surface opposite to said aft surface, and a structure disposed therebetween. In a launch configuration, two or more deployable antennas are disposed, undeployed, on or proximate to and forward of the forward surface; on-orbit, the payload is operable when the satellite is disposed with the aft surface substantially Earth facing while the forward surface is substantially facing in an anti-Earth direction. Each deployable antenna is disposed, so as to be Earth facing, when deployed, in a position substantially forward and outboard of the forward surface.

Abstract: An engine mounting structure for aircraft including an engine mounting system including a device for transmission of the thrust efforts fitted with two lateral connecting rods and with a spreader beam mounted in connected fashion on a support element, through a principal connecting device defining a principal spreader beam hinge line positioned in a plane. The spreader beam is also mounted in connected fashion with some play on the element, using a secondary connecting device located at some distance, as seen from above, from the device, and defining a secondary spreader beam hinge line, which is also positioned in a plane. The rotation of the spreader beam is stopped by device coming into contact with the spreader beam.

Abstract: The present invention consists of an aerial device, comprising a structure and a rotating element equipped with at least one blade, suitable for effecting a rotation relative to the structure around a rotation axis, wherein the device is equipped with means making it possible to cause the rotating element to rotate relative to the structure and wherein these means include a gas generator and a pipe that makes it possible to guide the gas towards an orifice at a distance from this rotation axis in order to cause the rotating elements to rotate by means of the gas ejected through the orifice, characterized in that the generator outlet and the pipe are part of the rotating elements and are suitable for rotating around the rotation axis relative to the structures.

Abstract: An aircraft structural element situated at an interface between a wing and the fuselage, and including a web and profiled elements flanking the web. At least one the profiled element includes a flat part positioned without overlap in the continuation of a flat part of the web and connected thereto by a welded butt joint using friction stir welding.

Abstract: A single slotted trailing edge flap arrangement for an aircraft wing, comprising a main flap element and an auxiliary flap element sealed to and supported by the main flap element for movement between a retracted and an extended position relative to the main flap element so as to vary the planform area of the flap. The auxiliary flap element remains sealed to the main flap element when in its extended position, and movement of the auxiliary flap element relative to the main flap element is solely translational. The auxiliary flap element may be translationally deployed from the main flap element by sliding the auxiliary flap element out from the underside of the main flap element. Also, a method of operating the flap arrangement.

Abstract: A parachute can be opened automatically without requiring manual operation. In addition, the parachute is capable of staying balanced during the course of landing. The parachute comprises: a spherical canopy, an air guide member and four assistant canopies. The air guide member is a rotation symmetrical structure with respect to the central axis, each of the cylindrical members is also a rotation symmetrical structure with respect to the assistant central axis, and the assistant canopies are also symmetrically arranged with respect to the central axis, so as to maintain the parachute in a stable and balanced state when the parachute is falling.

Abstract: A multilayer construction for aerodynamic riblets includes a first layer composed of a material with protuberances, the first layer material exhibiting a first characteristic having long-term durability and a second layer composed of a material, exhibiting a second characteristic with capability for adherence to a surface.

Abstract: An array of aerodynamic riblets is created by a plurality of high stiffness tips with a layer supporting the tips in predetermined spaced relation and adhering the tips to a vehicle surface.

Abstract: A multilayer construction for an array of aerodynamic riblets incorporates a first layer composed of a material with protuberances, the first layer material having shape memory and a second layer composed of a material exhibiting a second characteristic with capability for adherence to a surface.