Abstract: A winglet (114) is attached to a wing tip (112) by a main beam (132) which extends into the wing tip (112) and is attached to the rear spar (118). A canted spar (134) also extends to be attached proximate the forward spar (116).

Abstract: An aerodynamic structure (1) comprising a series of shock bumps (3a, 3b, 3c) extending from its surface. The shock bumps are distributed along a line (7) with a smaller mean angle of sweep than an unperturbed shock (4) which would form adjacent to the surface during transonic movement of the structure in the absence of the shock bumps. Instead of being distributed along the line of the unperturbed shock, the shock bumps are distributed along a line which is less swept than the mean angle of sweep of the unperturbed shock. When the structure is moved at a transonic speed; a shock forms adjacent to its surface and the shock bumps perturb the shock (9) so as to reduce its angle of sweep.

Abstract: An aircraft for carrying passengers and/or cargo has first, second and third cabins arranged in a split level floor configuration within a fuselage. The cabin floors are connected by stairs, elevators or escalators. Two of the cabins are stacked above a reduced height lower hold which acts as an energy absorbing crush zone in the event of a crash.

Abstract: An oblique wing aircraft designed for reduced surface area to volume ratio. The aircraft has an oblique wing comprising a forward swept wing segment and an aft swept wing segment. A center oblique airfoil section connects the forward and aft swept wing segments. The center oblique airfoil section has a larger chord near its centerline than the chords of either of the forward or aft swept wing segments. The chord of the center oblique airfoil section tapers down more rapidly than the forward or aft wing segments as the center oblique airfoil section extends outboard toward the forward and aft swept wings. Preferably, the aircraft is an all-wing aircraft.

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: An array of aerodynamic riblets incorporates a high elongation elastomeric layer having spaced tips and optionally a protective cladding. The elastomeric layer may be adhered to an aerodynamic surface directly or as an appliqué in combination with one or more of an adhesive layer, one or more supporting polymer layers and a metal foil layer.

Abstract: An aerodynamic structure comprising a series of shock bumps (3) extending from its surface. The shock bumps are distributed across the structure with a non-uniform spacing (d1, d2) between the centers and/or edges of adjacent bumps. The non-uniform spacing between the bumps can be arranged to give maximum wave drag alleviation for the minimum number of bumps as a function of the shock strength across the span, leading to minimum wing weight penalties for a given amount of wave drag alleviation.

Abstract: A momentum altering system comprises a transportation device configured to transport the momentum altering system towards an object moving through water. An engagement device is configured to attach to the object when the momentum altering system is transported sufficiently near the object. At least one decelerating device is connected to the engagement device. At least one decelerating device is deployed by the engagement device after the engagement device attached to the object. At least one decelerating device includes a plurality of parachute sea anchors that produce drag when pulled though water thereby altering momentum of the object.

Abstract: An aircraft according to the invention enables passengers to be received and comprises a first deck for receiving passengers, a second deck for receiving passengers, which is placed over the first deck, as well as at least one access door. The first deck has at least one first zone having a substantially planar floor and situated on the same level as the access door and at least one second zone having a floor offset in height relative to the first zone. The cabin further comprises at least one rectilinear ramp linking the first zone of the first deck to the second zone of the first deck, and at least one rectilinear ramp linking the first zone of the first deck to the second deck.

Abstract: An actuator including: a housing; a piston movably disposed in the housing, the piston being movable between an extended and retracted position; a plurality of gas generation charges generating a gas in fluid communication with the housing; and an exhaust port for exhausting gas from the cylinder generated by the plurality of gas generation charges; wherein activation of each of the plurality of gas generation charges results in an increase in pressure in the housing causing the piston to move in the housing from the refracted to the extended position. The actuator can further include a return spring for biasing the piston in the retracted position and the plurality of gas generation charges can be disposed in the housing.

Abstract: A fin retention system having a plurality of fin retention units and in which each unit is associated with one deployable fin of the projectile. Each retention unit has an alignment device and a pair of span arms extending outwardly from opposite sides of the alignment device. An attachment device attaches the free ends of the span arms of adjacent fin retention units together. In doing so, the alignment device engages and holds each fin in its undeployed position.

Abstract: A nacelle for housing an engine includes a fan cowl sized to cover at least a first axial portion of the engine. The engine includes an inlet end, an exhaust end, and an axis extending through the engine from the inlet end through the exhaust end. The fan cowl is coupled to an engine mounting pylon via a mounting assembly including at least one power drive system. The fan cowl is movable with respect to the engine along the axis toward at least one of the inlet end and the exhaust end.

Abstract: A nacelle for housing an engine includes a fan cowl sized to cover at least a first axial portion of the engine. The engine includes an inlet end, an exhaust end, and an axis extending through the engine from the inlet end through the exhaust end. The fan cowl is coupled to an engine mounting pylon via a slider-type mounting system that includes at least one slider track assembly defining at least one slot therein. The at least one slot is configured to receive at least one fan cowl slider fitting.

Abstract: Aircraft mission equipment (e.g., an electrical equipment cabinet) comprising a base plate equipped on a bottom with a plurality of air casters that provide flotation mobility. When the equipment is being loaded in or unloaded from an aircraft, the actuated air casters provide a plurality of air cushions. The total lift force produced by the air cushions is sufficient to float the equipment above and out of contact with the floor, thereby improving ease of handling and reducing point loads on the floor structure. Portions of the air distribution system that provides pressurized air to the air casters on the bottom of the base plate are structurally integrated into the base plate of the mission equipment.

Abstract: The invention relates to a securing plate (1) for removably securing a one-piece propulsion unit (17) to a wing of an aircraft, characterised in that it includes first connection means (4, 5, 8, 13, 14) for securing the plate to the wing, second connection means (24) for securing the one-piece propulsion unit to the plate and third connection means (7) for securing a pair of longitudinal handling members (22) to the plate. The invention also relates to a specific longitudinal member and to an installation including a one-piece propulsion unit secured in the plate.

Abstract: A cabin attendant seat (14) comprises a backrest element (20) and a seat element (22) which is secured to the backrest element (20). The backrest element (20) is rotatable about a rotation axis (24a, 24b) in order to move the cabin attendant seat (14) between a rest position and an operating position. A fastening device (18) for fastening the cabin attendant seat (14) to a side wall (16) of an aircraft monument (12) is constructed and sized in such a manner that it is capable of directing away a predetermined maximum force which can be introduced into the cabin attendant seat (14) during operation of the cabin attendant seat (14) via the side wall (16) of the aircraft monument (12).

Abstract: A vertical take-off and landing aircraft includes a fixed wing airframe having opposed left and right wings extending from left and right sides, respectively, of a fuselage having opposed leading and trailing extremities and an empennage located behind the trailing extremity. Four fixed, open and horizontal, vertical take-off and landing (VTOL) thrust rotors are mounted to the airframe in a quadrotor pattern for providing vertical lift to the aircraft, and a vertical, forward thrust rotor is mounted to the trailing extremity of the fuselage between the trailing extremity of the fuselage and the empennage for providing forward thrust to the aircraft. The four VTOL thrust rotors are coplanar being and operating in a common plane that is parallel relative to, and being level with, top surfaces of the left and right wings in and around a region of each of the four VTOL thrust rotors.

Abstract: A torque link member for aircraft landing gear includes a first end for connecting to a lower portion or an upper portion of the aircraft landing gear and a second end for connecting to another torque link member. A locking pin is disposed on one of the upper portion, the lower portion, the first end or the second end. The locking pin is axially movable between an engaged position wherein the pin protrudes for interengagement with a cooperating aperture on the first end, the second end, the upper portion, the lower portion, or the second end of the other torque link member, and a disengaged position. The locking pin is biased toward the engaged position and movable against the biasing to the disengaged position.

Abstract: An aircraft capable of carrying passengers and cargo includes a fuselage, having a crown section and a keel, a first passenger cabin, having a first floor, located in a forward portion the fuselage, and a first cargo deck, located below at least a portion of the first passenger cabin. A split level cabin is located in an aft portion of the fuselage, the split level cabin including an upper second cabin having a second floor above the level of the first floor, and a lower third cabin beneath the upper second cabin and having a third floor below the level of the first floor. A second cargo deck is located in the aft portion of the fuselage and beneath at least a portion of the lower third cabin. The crown section has a substantially constant cross-sectional shape fore-to-aft above the first passenger cabin and the split level cabin, and the keel below the second cargo deck is lowered compared to the keel below the first cargo deck.

Abstract: A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) (100, 400, 1000, 1500) configured to control pitch, roll, and/or yaw via airfoils (141, 142, 1345, 1346) having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns (621, 622). Embodiments include one or more rudder elements (1045, 1046, 1145, 1146, 1245, 1345, 1346, 1445, 1446, 1545, 1546) which may be rotatably attached and actuated by an effector member (1049, 1149, 1249, 1349) disposed within the fuselage housing (1001) and extendible in part to engage the one or more rudder elements.