Abstract: An improved cruciform-type parachute is provided for aerial delivery of cargo, with a center panel shaped as a square or other regular polygon, and first lens-shaped panels conjoined to each edge of the center panel. The first lens-shaped panels are formed of two circular section sub-panels conjoined along their respective arc segments. Side panels, shaped as rectangles or other quadrilaterals, have one edge conjoined with each first lens-shaped panel at the other edge opposite from the center panel. The adjacent side edges of each pair of adjacent side panels are conjoined to either convex edge of a second lens-shaped panel. The second lens-shaped panels are defined by three edges; two of which are defined by symmetrically opposed convex arcs joined at one end, and the third edge defined by a straight line intersecting the other ends of the arcs. One end of each of a plurality of upper rigging members are disposed along an edge opposite from the first lens-shaped panel on each side panel.

Abstract: A rotatable leading edge for the fuselage and wings of an aircraft is disclosed. The leading edge may be rotated from an undeflected or retracted position adjacent to the fuselage and wings to a deflected or extended position. In the extended position, the leading edge increases lift of the aircraft at low speeds. In the retracted position, gaps associated with the leading edge are avoided.

Abstract: Controllable refueling drogues and associated systems and methods are disclosed. A system in accordance with one embodiment includes a fuel delivery device having a deployable portion configured to be deployed overboard an aircraft during aerial refueling. The deployable portion can include at least a portion of a flexible fuel line, a drogue coupled to the flexible fuel line, and an actuatable device operatively coupled to at least one of the drogue and the fuel line. The deployable portion can further include a guidance system that is operatively coupled to the actuatable device and that includes instructions to direct the operation of the actuatable device and move the drogue during flight.

Abstract: A UAV capture system is disclosed. In the illustrative embodiment, the UAV capture system is coupled to the deck of a sea-faring vessel. The UAV capture system includes a single arresting line that is supported by a stanchion. In the illustrative embodiment, the stanchion is disposed on a rotatable boom.

Abstract: An extendable leading edge for the fuselage and wings of an aircraft is disclosed. The leading edge may be extended from a retracted position adjacent to the fuselage and wings to an extended position. In the extended position, the leading edge increases lift of the aircraft at low speeds. In the retracted position, gaps associated with the leading edge are avoided.

Abstract: Valves for annular conduits and associated systems and methods are disclosed. A fluid transmission system in accordance with one embodiment of the invention includes a first conduit having a first wall aligned with a flow direction in the first conduit and a second conduit disposed annularly around the first conduit with a second wall aligned with the flow direction. An access channel can be positioned to have an aperture in fluid communication with the first conduit and can be isolated from fluid communication with the second conduit. A valve element can be positioned in fluid communication with the access channel and can be movable between a first position and a second position, with the valve element being positioned to allow a first amount of flow through the access channel when in the first position and being positioned to allow no flow or a second amount of flow less than the first amount of flow through the access channel when in the second position.

Abstract: An articulated leading edge for the fuselage and wings of an aircraft is disclosed. The leading edge may be moved from an undeflected or retracted position adjacent to the fuselage and wings to a deflected or extended position. The leading edge includes fuselage and wing portions which are articulated with respect to each other. The fuselage portion of the leading edge may be rotated around an axis near the nose of the aircraft. When the fuselage portion is rotated, the region between the fuselage portion and wing portion of the leading edge bends and the wing portion is elevated with respect to the wing. In such an extended position, the leading edge increases lift of the aircraft at low speeds. In the retracted position, gaps associated with the leading edge are avoided.

Abstract: A fin control assembly includes a housing, an arm configured to couple to a fin and to steer the fin relative to the housing, and a locking member disposed within the housing. The locking member is configured to (i) lock the arm in a substantially fixed state to inhibit movement of the arm relative to the housing when the locking member is in an engaged position, and (ii) unlock the arm from the substantially fixed state to allow the arm to steer the fin relative to the housing when the locking member moves from the engaged position to a disengaged position. The locking member has a cylindrical body portion and a cylindrical end portion, which is eccentric with the cylindrical body portion, to enable the locking member to lock the arm in the substantially fixed state while the arm holds the fin in a neutral location.

Abstract: Aerospace vehicle yaw generating systems and associated methods are disclosed herein. One aspect of the invention is directed toward a yaw generating system that can include an aerospace vehicle having a fuselage with a first portion and a second portion. The system can further include a movable control surface coupled to the fuselage and extending generally in a horizontal plane. The control surface can be movable to a deflected position in which the control surface can be positioned to create a flow pattern proximate to the fuselage when the aerospace vehicle is located in a flow field. The flow pattern can be positioned to create a pressure differential between the first portion of the fuselage and the second portion of the fuselage. The first and second portions can be located so that the pressure differential produces a yawing moment on the aerospace vehicle.

Abstract: An apparatus for controlling movement of a flying device, such as a kite. In controlling such movement, the apparatus comprises a series of force transmitting members associated with a control bar to be grasped by an operator. Such association minimizes interference of the force transmitting members with the control bar surface so as to heighten the level of control that the operator may exert over the kite. Such association also permits the operator to achieve, through movement of the control bar, selective adjustments in both the velocity and acceleration at which the kite and the operator are able to move in a single direction.

Abstract: Servocontrolled aerodynamic control surfaces, such as the direction rudder (1) of an airplane, are equipped with servoactuators (5). The bearing supports (3) of the rotation axis (2) or hinged axis give rise to the formation of free play for the manufacturing tolerances, that will be more pronounced with the wear of the bearings or joint elements. The mechanism (8) in question includes an elastic element (10) fixed to the structure (4) wherein the control surface (1) is jointed, connected rigidly to an articulated connecting rod (12) having a following roller (13) of a cam (9) integral to the control surface (1). The cam (9) profile produces a continuous nonlinear, angular deformation, of the elastic element in order to determine a force torque on the control surface (1) that is maximum in the neutral position of the control surface and manages to be eliminated in the extreme side deviations.

Abstract: A toy helicopter landing skid structure includes an upper support stand, a propping member and a bottom stand. The upper support stands are connected to the bottom of a helicopter airframe, and the propping member is connected to the bottom of each upper support stand, two insert slots extended in opposite directions at each connecting position of the upper support stand, the propping member and the bottom stand, a hollow portion disposed in each insert slot for clamping an elastic member, a plurality of fixing holes disposed at the bottom of each propping member, a plurality of bottom stands disposed at each propping member for passing a binder through the two fixing holes for binding the propping member with the bottom stand, so as to absorb external forces and impact by the slanting connected upper support stand with the insert slot and the installed elastic member.

Abstract: An aircraft barrel lay-up assembly is provided comprising a barrel mandrel assembly having a contiguous outer barrel lay-up surface. A minor barrel outer surface element is movable between a minor barrel engaged position and a minor barrel disengaged position and forms a minority portion of the contiguous outer barrel lay-up surface when in the engaged position. A major barrel outer surface element is movable between a major barrel engaged position and a major barrel disengaged position. The major barrel outer surface has a first major barrel surface end and a second major barrel surface end moving together to reduce an effective major barrel outer surface circumference when in the major barrel disengaged position. A composite ply assembly is formed around the barrel mandrel circumference and cured while coincident to form a composite barrel element.

Abstract: A long-haul airplane has a private cabin for the pilots within a storage compartment disposed on a floor below the flight deck. The private cabin is in communication with the flight deck through an opening in the floor.

Abstract: A landing arrangement for an aircraft comprises an aircraft support assembly (22) to support the aircraft (10) when the aircraft is on the ground. The aircraft support assembly (2) is movable between a first ground engaging condition (22b) in which the aircraft nose (24) is spaced above the ground by a first distance (X) and a second ground engaging condition (22C) in which the aircraft nose (24) is spaced above the ground by a second distance (Y). The second distance (Y) is less than the first distance (X).

Abstract: A helicopter having a torque-correcting thruster device. The helicopter has an aerodynamic body which has opposite side portions, a top portion and a bottom portion. The aerodynamic body has a cockpit and a pilot seat in the cockpit. The helicopter includes landing gear attached to the bottom portion of the aerodynamic body. The helicopter includes a rotor that is supported by the aerodynamic body and a rotor blade attached to the rotor, and a thruster device operative on one of the side portions of the aerodynamic body to produce an aft-directed thrust that counteracts the torque produced by rotation of the rotor blade so as to control the yaw of the helicopter. The aft-directed thrust simultaneously supplements the forward thrust of the helicopter.