Abstract: An aircraft wing includes a rear spar, a first skin, a second skin overhanging and converging to an opening of width (A), a support structure including a bracket engaging the spar and skins and a rib engaging the bracket via a rib attachment portion with a dimension (C) less than dimension (A).

Abstract: A spacecraft (P) has a propulsion system making it possible to exert a force of variable magnitude and orientation on the spacecraft, a control system designed to control the propulsion system in terms of magnitude and orientation so as to make the spacecraft approach a target around a planet, with the aid of a force having at least one component (fx, fy, fz), in the rotating reference frame tied to the target, which depends substantially linearly on the corresponding coordinate (x, y, z) of the craft in this reference frame.

Abstract: A propulsion unit for an airship comprises a driveshaft, having a gimbal mount to a mounting frame attachable to a fuselage, the gimbal being mounted in the mounting frame and comprising an inner ring and an outer ring having orthogonal rotational axes, the inner ring including a propeller unit having a conical housing pivotable on trunnions with the gimbal and a propeller affixed to a propeller shaft coaxial with the axis of the conical housing. The outer ring includes a toroidal Orientation of the conical housing and propeller shaft is accomplished by actuators, a first actuator controlling the angle of the outer ring relative to the framework and a second actuator controlling the angle of the conical housing relative to the outer ring.

Abstract: Sleeper seats, wherein each comprises a head rest, a back rest, a seat pan or seat cushion, a leg rest, an ottoman and a divider between the individual seats with the their column. The four seats are arranged in a staggered chevron formation and two columns. All the seats in each column are parallel with each other and set at a “herringbone” angle ? to the column direction, in other words their central axes make the angle ? with a longitudinal axis of the array. Each seat extends from its column side of the longitudinal axis across the axis to a small extent. Along the axis, first a seat from one column crosses the axis and then a seat from the other column crosses the axis and so on.

Abstract: Systems and methods to provide distributed flow control actuation to manage the behavior of a global flow field, are provided. An example of a system can include an aerodynamic structure having an outer surface, and an array of a plurality of effectors connected to the outer surface of the aerodynamic structure to be in fluid contact with a flowing fluid when operationally flowing, to induce controlled, globally distributed disturbances at a viscous wall sublayer of a turbulent boundary layer of the flowing fluid when operationally flowing and to manipulate fluid behavior of the flowing fluid to thereby substantially reduce pressure loss associated with incipient separation of the fluid flow from portions of the aerodynamic structure.

Abstract: A mat for reducing the disturbance of particulate matter by wind, has a first layer of coarse mesh material, and a second layer of coarse mesh material. The first layer is held in a substantially fixed position relative to the second layer. The mat is particularly suitable for use as a helicopter landing mat, in conditions where dust, sand, snow, water or other particles or liquids might otherwise cause a disturbance resulting in loss of visibility, damage or wear to parts of the helicopter, and injury or damage to nearby people or equipment.

Abstract: A vehicle control method (and concomitant control structure) comprising deploying an electrolaminate affixed to a substrate and using the combination to control motion of the vehicle.

Abstract: A speed brake apparatus reduces the airspeed of an aircraft by increasing aerodynamic drag. First and second brake panels are located on opposite sides of a portion of the aircraft, such as the fuselage, and are adapted to swing outward about a downstream hinge axis into deployed positions extending into the air stream. The panels are controlled by an operating device that includes a linear actuator. The actuator moves an operating head connected to a pair of toggle assemblies to convert linear movement of the operating head to the deployment and retraction movement of the brake panels.

Abstract: The present invention relates to a device for the installation of commercial components in an aircraft that features at least one equipment carrier for accommodating the components, wherein the at least one equipment carrier is arranged between a luggage rack and the skin of the aircraft and held on the aircraft structure such that it can be pivoted between a maintenance position and an installation position. In order to accommodate the commercial components in a space-saving fashion and to simplify the installation and maintenance work, the equipment carrier can be at least partially pivoted into the luggage rack and is accessible in order to perform installation and maintenance work from the luggage rack in the maintenance position.

Abstract: A hinge rib for pivotally connecting an aerodynamic control element such as a spoiler or aileron to an aircraft structure. The hinge rib includes a first hinge rib arm having a grain oriented in a first direction and a second hinge rib arm having a grain oriented in a second direction which is not parallel with the first grain direction. The arms may be formed together from a single piece of material, or more typically they are formed separately before being attached together such that the grain of the first arm is not parallel with the grain of the second arm.

Abstract: An assembly for stowing away and removing a survival kit in a passenger cabin of an aircraft, includes a first stowage compartment configured to be put in place in a floor of the passenger cabin. The first stowage compartment is equipped for completely accommodating the survival kit and for leading out a hook that is connected to the survival kit by way of a strap. The hook is used for hooking the survival kit to an attachment device of a rescue device with the first stowage compartment remaining closed.

Abstract: An aircraft wing assembly comprising: a main wing element; an inboard rib and an outboard rib, each mounted to the main wing element; a bridging structure attaching the inboard rib to the outboard rib; an inboard flap and an outboard flap; and an inboard bearing and an outboard bearing, each mounted to the bridging structure and each engaging a respective one of the flaps. The bridging structure ensures that an accurate distance is maintained between the ribs during installation, and maximises the stiffness of the assembly. Also, the bridging structure can act as a shear plate supporting both the inboard and outboard bearings, thus removing any twisting moment on the ribs.

Abstract: An aircraft structure including stiffened panels assembled at the junction, without continuity of the stiffeners. Multiple panels are used to form the fuselage, tail units and wings of an aircraft. These panels include stiffeners which are interrupted at each panel junction. However, the stresses experienced by the stiffeners must be transmitted despite these interruptions. Known solutions require the use of at least one additional part per stiffener and per interruption. In order to solve this problem, the disclosed embodiments include a doubler necessitating at most one additional part per panel junction area for all of the interrupted stiffeners in this area.

Abstract: The invention relates to a steering unit for a wind propulsion system, the steering unit comprising a first fixed attachment means for securing a first end of a tractive cable the second end of which is secured to a device or a vehicle to which a tractive force shall be transferred, a second attachment means for attaching a number of tractive lines, the second end of which being secured to an aerodynamic wing element, a mechanical support frame connecting the first attachment means to the second attachment means for transferring a tractive force. The invention aims at providing such a steering unit with improved design for better maneuverability and stability.

Abstract: Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension.

Abstract: Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension.

Abstract: A method and device of dynamically reducing the buffeting of an airplane. The method is carried out by detecting a risk of buffeting of the airplane in flight by a monitor. At least one control surface is turned by an actuator arranged at a trailing edge of each wing of the airplane. The control surface is turned, at a predetermined respective rate of turn, into a predetermined respective position to modify lift profile of the wing along a wingspan length to reduce lift in at least one buffeting-generating region of each wing.

Abstract: A wing of an aircraft has a mainplane, which has an upper face, a lower face and an aerodynamically shaped area. The wing has an additional airfoil which is articulated on the mainplane and can be extended from a retracted state with a slot area being opened between the mainplane and the additional airfoil. The wing also has a variable-position slot-varying apparatus which is arranged on the lower face, forms a part of the aerodynamic profile of the additional airfoil or mainplane when the additional airfoil is extended, and at least partially covers the slot area between the mainplane and the additional airfoil on the lower face when the additional airfoil is in the retracted state. The slot-varying apparatus can be varied between a curved configuration, in which it forms a part of an aerodynamic profile, and an extended configuration, in which it at least partially covers the slot area.

Abstract: An aircraft having a lambda-box wing configuration includes, a fuselage, a propulsion system, a first pair of swept-back airfoils, connected to the top forward portion of the fuselage, a second pair of swept-forward airfoils, connected to the lower rear portion of the fuselage at a point of the said fuselage aft of the connection of the swept-back airfoils, and a third pair of substantially vertical airfoils, the tips of the swept-forward airfoils being connected to the lower side of the swept-back airfoils at an intermediate point of the span of the said swept-back airfoils, by the substantially vertical airfoils, the swept-back airfoils having a higher aspect ratio than that of the swept-forward airfoils, which makes the swept-back airfoils have a reduced induced drag without penalizing their weight.

Abstract: A leading edge structure is disclosed for an aircraft wing in which a droop nose is articulated by a double hinge.