Abstract: A T-38 trainer aircraft that is modified to have the wings of an F-5 fighter aircraft. The F-5 wings have leading edge flaps which increase aircraft maneuverability and allow the plane to be landed at a lower speed. The F-5 wing is coupled to existing wing joints of the fuselage by fittings which increase the angle of incidence of the aircraft approximately 2.degree.. The increased angle of incidence provides the pilot with a greater over the cone field of view. The modified T-38 also has a pair of forward strakes located on the leading edge of the aircraft nacelles. The forward strakes further increase the performance of the plane. Attached to the tail of the aircraft are a pair of aft strakes which counteract the pitch created by the forward strakes.

Abstract: A lifting body moves relative to a fluid, thereby creating a vortex field in the fluid downstream of the lifting body. The lifting body has a predetermined lift distribution along the length thereof which enhances the velocity component of the fluid flow directed outwardly from the centroid of the vortex field to reduce the strength of trailing vortices. In a preferred embodiment, the lifting body is a wing with a perturbation proximate to the tip end of the wing planform trailing edge.

Abstract: A kite framing-member connector for forming a connection between at least two elongated kite framing-members. The kite framing-member connector comprises: a first framing-member connection fitting attached to a second framing-member connecting mechanism. The first framing-member connection fitting is adapted to receive and hold the end of a framing-member such as a spreader. The second framing-member connecting mechanism includes a flap portion having a flexible, flap-end portion that is securable to a kite framing-member, such as a leading edge spar, by surrounding and gripping a section of the kite framing-member. It is preferred to include an attachment structure carried on the flap-end portion that is connectable with a harness line in a manner such that tensional force on the harness line causes the second framing-member connecting mechanism to increase the gripping force applied to the section of the second kite framing-member about which the flap portion is secured.

Abstract: An aircraft maintenance robot (20) for maintaining aircraft surfaces is described, that includes a maintenance tool (228), for example a nozzle (78), conduits and a pump, which supply fluid to the maintenance tool, which sprays the fluid on aircraft surfaces; movable arm with rotatable hinges and wrists such that a manifold to which the maintenance tools are coupled may be positioned in response to control signals; and a processor which, after accounting for the position of the aircraft, the weather conditions, and the physical dimensions of the aircraft, generates the control signals used to position the maintenance tool such that, after positioning the aircraft, the maintenance operation may be performed without human intervention. The preferred embodiment of the present invention discloses the use of the maintenance robot (20) for deicing aircraft. A wide variety of interchangeable end effectors, however, may be used for a wide variety of applications.

Abstract: Boundary layer control apparatus is provided (22). The boundary layer control apparatus (22) is for use with an aircraft propulsion nacelle (12) positioned such that the air inlet (14) of the propulsion nacelle is located proximate an aircraft surface (10), wherein a boundary layer is established on the surface when the aircraft is propelled through an atmosphere, causing air to flow over the surface. The boundary layer control apparatus (22) includes a duct having an entrance (24) positioned between the aircraft surface (10) and the inlet (14) of the propulsion nacelle (12) for capturing the boundary layer air passing over the aircraft surface and diverting the boundary layer air away from the inlet.

Abstract: The thermal protection device is made up of a plurality of juxtaposed unit modules each comprising a fairing element provided with fixing tabs and thermal insulation integrated in the fairing element. The gap between neighboring fairing elements is limited to the minimum width necessary for accommodating thermal expansion thereof. The connection means which releasably connect the fixing tab to a primary structure to be protected comprise a ball fixed to the fixing tab in adjustable manner and capable of being locked in a corresponding socket of a retaining part fixed to the primary structure. The ball is locked in its socket by means of a bolt capable of being released by action exerted against a resilient return force.

Abstract: The difficulty and expense of fabricating a support strut for a ram air driven turbine are reduced by providing an axially opening channel in a central portion of the strut. Blockage of a portion of the airstream flowing through the ram air turbine and past the strut is reduced by extending the axially opening channel through the entire axial length of the strut. Apparatus for converting or transferring power generated by the ram air turbine to a point of use, such as an aircraft, is routed through the axially opening channel, thereby allowing convenient access to such apparatus. A strut design is provided which may be readily manufactured as a single unitary structure from a variety of metallic and non-metallic materials including fiber reinforced composites.

Abstract: A system for removing and/or preventing ice build-up on an aircraft includes at least one heat exchanger mounted within an aperture in the tailpipe of a gas turbine engine. The heat exchanger includes an inner plate having a surface which faces inwardly into the tailpipe and which is in direct contact with the heated exhaust gas in the tailpipe, and an outer plate with a surface facing outwardly from the tailpipe and in direct contact with a cooler air stream passing around the turbine engine core. A series of heat exchange fins are formed on the inner plate to direct exhaust gas across the inner plate, and a series of heat exchange fins are formed on the outer plate to direct the cooler air across the outer plate. Heat transfer fluid flows between the inner plate and the outer plate and absorbs heat energy from the exhaust gas. The heat transfer fluid flows through a filter, accumulator and pump system to heat transfer structure integral with the exposed portions of the aircraft.

Abstract: A safety system for reducing the risk of injury during a survivable crash of a high-speed passenger vehicle. The safety system includes at least one bulkhead support base mounted to a vehicle within a passenger compartment and a bulkhead panel mounted to a portion of the bulkhead support base. In addition, the device includes energy-absorbing means associated with the bulkhead panel for absorbing the energy of a passenger impacting on the bulkhead panel. In this manner, the system minimizes injury to a passenger striking upon a bulkhead wall or class-divider wall within the vehicle. A triggering system is also provided for electronically activating the safety system when necessary.

Abstract: A system for preventing the automatic or inadvertent opening of an aircraft door or access hatch that has not been closed and locked properly provides an increase in the overall flight safety of aircraft. The system includes a door monitoring system (1), which is connected to at least one of a cabin pressure control arrangement (4), a cabin temperature control arrangement (5), and an air tap system control arrangement (36). The door monitoring system (1) provides a signal indicating if at least one door or access hatch is not properly closed and locked. The controllers (4, 5, 36) receive the door monitor signal at respective inputs and also receive information necessary for determining the current flight configuration of the aircraft from various other aircraft systems, such as a landing gear control arrangement or an engine monitor arrangement.

Abstract: The leading edge (12) of an aircraft wing is equipped with a kruger nose which includes a rigid flap (18) and a mechanism (26,28,30,40) ensuring the deployment of the flap in an intermediate landing position (P3) and in a take-off position (P2). The disposition of this mechanism is such that, in the landing position (P3), a slot exists between the flap (18) and the leading edge, whereas this slot disappears in the take-off position (P2). The mechanism preferably includes two connection rods (28,30) connecting a control reversing lever (26) and an intermediate reversing lever (40).

Abstract: A method is provided for controlling a carrier which is used to carry a flight vehicle, the method including (a) providing a carrier and a control system mounted on a lower side thereof; (b) sending a signal to a flight vehicle to decrease a velocity thereof for landing; (c) sensing a flight direction of the flight vehicle and instantaneous velocities thereof; and (d) accelerating the carrier to catch up with the flight vehicle at a location therebeneath and adjusting the velocity of the carrier to match with that of the flight vehicle such that the flight vehicle is able to smoothly land so as to be supported on a top surface of the carrier.

Abstract: In a window structure equipped on the side walls of a cabin in the body of an airplane, a transparent board is mounted on the outer portion for sealing the pressure inside the cabin. A dust cover is mounted in the inner side of the transparent board sealing the pressure, and a shade 80 which is able to take an up and down movement is mounted on the cabin side of the dust cover for blocking outer incident light. The dust cover comprises of a transparent resin board and a non-elastic film stuck on the surface of the transparent resin board facing the shade. The acrylic resin used as the material of the transparent resin board expands by absorbing the water in the air, but by the operation of the non-elastic film, the dust cover bends toward the outer direction F of the body, and will not interfere with the locus L.sub.1 of the up and down movement of the shade.

Abstract: A pylon (14) for supporting a turbo-fan jet engine, in particular, an ultra-high by-pass turbo-fan jet engine (12) is disclosed. The pylon (14) attaches to the forward and aft parts of the engine core (22) and supports the engine (12) from an airplane wing (10) while resisting static and dynamic forces applied by the engine and the nacelle of the engine to the pylon. The pylon (14) includes a pylon bifurcation portion(16), having an upper end (23) and a lower end. The upper end (23) is positioned exterior to the fan duct (8) of the engine and is attached to the wing (10). The lower end is positioned inside of the fan duct (8). The lower end further includes an aft section that is attached by lugs (38) to the aft part of the engine core (22), and a forward section that is attached to the forward part of the engine core.

Abstract: A helicopter external cargo suspension system (12) has load sensors (19,20) at each suspension point for sensing the magnitude of a load (32) at each suspension point. A delay period (FIG. 6) is determined based on the magnitude of the load, and a load is released if one of the following failure modes occurs for a period which exceed the delay period: one of the suspension points is unloaded, the magnitude of the load exceeds a maximum threshold magnitude, or if the distribution of the load, as indicated by the difference in magnitude at each suspension point, exceeds a difference threshold magnitude. If the magnitude of the load is below a minimum threshold magnitude, the load will be carried by one of the suspension points in response to a failure of the other suspension points.

Abstract: This invention relates to a composite aircraft comprising a conventional aircraft (2) and a carrier aircraft (4) connected together during flight as a composite aircraft by way of a connector (6). The carrier aircraft has a vertical takeoff and/or landing capability and the conventional aircraft is provided with a directable propulsion nozzle so that during operations as a composite aircraft lift is shared by components of lift from the propulsion systems of both aircraft. Therefore, by connecting itself to the carrier aircraft, the conventional aircraft may takeoff and/or land vertically as the case may be, but without the requirement for a vertical takeoff and/or landing capability of its own and all the weight penalties associated therewith.

Abstract: Auxiliary control of extension, retraction and pivotal movement of aircraft landing gear when not in use is provided by a method of operation, apparatus for attaching to the landing gear, and an assembly comprising landing gear and apparatus. The apparatus comprises auxiliary jacking means (18, 19) attachable between relatively telescopic parts of an oleo main strut of the landing gear and between relatively pivotal parts of the oleo and of a bogie pivotally attached to a lower end of the oleo. The landing gear may thus be powered up by the auxiliary jacking means (18, 19) with the pivotal movement of the bogie (4) being controlled simultaneously during, e.g. removal, fitting or servicing of the landing gear.

Abstract: Spoilers, mounted on vertical stabilizer tail surfaces of large aircraft release controllable Bernoulli forces to augment rudder and aileron aircraft controls. Data from surface pressure sensors, also mounted on vertical stabilizer tail surface, is computer-interpreted to minimize tail drag and structural flight-stress. The spoilers suitable for this role include parallel lines of controllable height barriers, located on the fore part of each side of symmetrical airfoils of airplane tails.

Abstract: A thrust maneuver system for steerable vehicles comprising a plurality of thrusters of varying impulsive force, some of which provide a base force, and others varying multiples of the base force. The forces may be used additively or subtractively to obtain a desired force for any given maneuver.

Abstract: An air-launchable gliding sonobuoy store includes a canister enclosing an flatable-membranous wing folded in a collapsed state with an electroacoustic system. After launching, the wing inflates and a steering mechanism controls the wing glide path by skewing the trailing edge thereof. Upon reaching the sea, the wing serves as a buoy with the electroacoustic system transducer depending therefrom.