Abstract: In a wing with wing shells with good shear strength made of fibrous composite materials, particularly fiber-reinforced plastics, for aircraft, members taking up tensile and compressive forces are attached to the inside of the wing shells. These members have unidirectional fibers extending longitudinally of the wing. Stringers spaced longitudinally of the wing are provided on the inside of the wing shells, their fiber component being formed by a fiber ply joined to the fiber ply of the wing shell. Unidirectional fibre bundles are arranged between spaced stringers, the bundles being embedded with good shear strength in the synthetic resin matrix of the wing shells, extending longitudinally of the wing and having a substantially rectangular cross-section.

Abstract: A remote indication system for a cargo door which indicates the following conditions: Opened, Closed, Latched, Unlocked and Locked. The entire system, including sensors, is independent of the standard flight deck warning system. This provides the required redundancy for the system so that direct observation is not required. An independent system from the standard flight deck warning system and/or the indication for each step of the process rather than just "open/closed" is utilized in the present cargo door control and indicating system.

Abstract: A nose landing gear assembly for an airplane which can be launched with catapult assistance. The landing gear assembly includes a nose strut, upper drag link, lower drag link, launch bar and launch bar actuator. When the nose shut is in the extended position, the upper drag link, lower drag link and launch bar form a direct load path between the catapult shuttle and the airplane thereby avoiding subjecting the nose strut to loads reacted from the shuttle. The nose strut, launch bar, launch bar actuator and airplane fuselage form a first four bar linkage. Furthermore, the nose strut, upper drag link, lower drag link and airplane fuselage form a second four bar linkage such that during retraction of the nose strut, the launch bar, launch bar linkage, upper drag link and lower drag link are caused to move up and into the airplane wheel well.

Abstract: A body configuration for improving the fluid-dynamic performance efficiency of aircraft and watercraft comprises a generally conical upper segment (54) and a generally conical lower segment (56) that are joined at a common base plane (53), achieved by inverting the conical lower segment (56). The slopes of the conical surfaces are determined by the prescribed planform of the craft or vehicle and by the height of the conical segments wherein the height of the conical upper segment (h.sub.u) is less than and typically two-thirds that of the conical lower segment (h.sub.L). Although not limited to elliptical planforms, a generally circular planform (52) is preferred for a vertical takeoff and landing aircraft operating in the subsonic flight regime and an elliptical planform (68), with a large aspect ratio for takeoff and low-speed flight, then rotating to a low-aspect-ratio orientation for supersonic flight operation, is preferred for supersonic transport and single-stage-to-orbit type aircraft.

Abstract: Multiple satellites are densely packed in modern multi-satellite launch vehicles. Stocking of a subsequent satellite (20) in the presence of adjacent satellites (12) subjects both satellites to damage due to mishandling and human error during craning operations. An alignment mechanism (30) attaches to subsequent satellite (20) and operates in conjunction with a craning tether (26) to stock a launch vehicle dispenser (10) with subsequent satellite (20). An alignment mechanism (30) restricts lateral motion of subsequent satellite (20) during stocking while keeping subsequent satellite (20) centrally located in a vacant position on a launch vehicle dispenser (10).

Abstract: A spacecraft telescope door (10) adapted for use with remote sensing devices requiring optical and infrared calibration. The door (10) includes a first calibration surface (24) disposed on a first panel (14) for providing a radiant temperature reference for infrared calibrations. A second calibration surface (26) is disposed on a second panel (12) for providing an absolute radiance reference for optical calibrations. A panel hinge (16) controls the relative position of the panels (12,14) with respect to each other, and an aperture hinge (20) controls the relative position of the panels with respect to the aperture (28). In a specific embodiment, the first surface (24) is painted with chemglaze Z306, a highly emissive paint with a low reflectance for facilitating infrared calibration. The second surface (26) is painted with YB71, a diffuse reflective paint for facilitating optical calibration.

Abstract: An airplane steering system which permits 180 degree turns with minimum tire scrub. The system involves steering of both the nose landing gear and the front and rear wheels of both main landing gear each consisting of three inline wheels; thus, the center of turn is placed between the main gears and allows the airplane to make 180 "pirouette" turns.

Abstract: An aircraft (10) including a stowable, wingtip mounted, vortex turbine (30) for dissipating or extracting energy from a lift induced vortex (28) emanating from the aircraft (10) is provided. The vortex turbine (30) includes a first and a second array (38, (40) of blades (32a,b) (34a,b) extending respectively from a first and a second hub section (32), (34). Hub sections (32), (34) may be independently pivoted about a common axis of rotation (36) to a stowed position for landing, take-off, or ground operation, whereat none of the blades (32a,b) (34a,b) extend below a minimum ground clearance of the aircraft, or beyond a maximum horizontal extension of the wing (16). In flight, the hub sections (32), (34) may be deployed and the pitch of the blades adjusted to maximize dissipation of the lift induced vortex (28), thereby minimizing drag and providing improved safety for other aircraft flying through the wake of the aircraft (10) producing the vortex (28).

Abstract: A method and system of attitude steering and momentum management for a spacecraft suitable over a wide range of orbit altitude and inclination parameters and a similar wide range of mission steering profiles is provided. The system utilizes two active momentum wheels positioned with their spin axes nominally coaligned on the spacecraft pitch axis. Each wheel is pivoted by jackscrew type mechanisms which allow the angular momentum to be tilted (e.g. within the range 0-45.degree. from the nominal alignment with respect to the spacecraft body). The spacecraft control processor generates wheel torque commands for the wheel speed electronics and jackscrew drive commands for the platform assemblies in order to adjust the speed and amount of tilt of the momentum wheels. The invention provides a two-momentum wheel array that allows use of either momentum bias steering or large angle zero-momentum steering and accommodates multiple orbit geometries and varying degrees of attitude steering agility.

Abstract: An air vehicle that includes a body lower portion, a body intermediate portion, body lower portion, a solar panel, elevating apparatus, gimbling apparatus, and inflatable landing gear. The body lower portion has a body lower portion outer surface and contains a body lower portion chamber. The body intermediate portion has a body intermediate portion upper surface and contains a body intermediate portion chamber. The body intermediate portion is connected to the body lower portion. The body upper portion contains a body upper portion chamber and is displaced a distance above the body intermediate portion. The solar panel has a solar panel outer surface and contains a solar panel void. The solar panel connects the body upper portion to the body intermediate portion. The elevating apparatus raises and lowers the air vehicle and is disposed within the body upper portion chamber.

Abstract: Insect debris is removed from or prevented from adhering to insect impingement areas of an aircraft, particularly on an inlet cowl of an engine, by heating the area to 180.degree.-500.degree. C. An apparatus comprising a means to bring hot air from the aircraft engine to a plenum contiguous to the insect impingement area provides for the heating of the insect impingement areas to the required temperatures. The plenum can include at least one tube with a plurality of holes contained in a cavity within the inlet cowl. It can also include an envelope with a plurality of holes on its surface contained in a cavity within the inlet cowl.

Abstract: The present invention comprises a method for injecting a heavier payload into orbit than is possible using a traditional method and the same rocket booster launch vehicle. The method of the present invention does not utilize a parking orbit and does not perform orbital injection at perigee or apogee of the desired orbit. Rather, in the present method the flight path angle is positive at the final lower stage booster burn so as to boost the perigee kick motor and payload into a suborbital trajectory having a low perigee, which may be below the surface of the Earth. In the preferred embodiment, the launch vehicle maintains a negative flight path angle during the PKM burn. The PKM burn does not occur at perigee, but perigee is at the desired location when the PKM burn is complete. Use of this method increases the payload capacity of some launch vehicles by up to fifty percent (50%).

Abstract: A control system for aircraft airfoils, which is an improvement over existing aileron, flap, spoiler and deicing technologies, in providing increased roll control and aerodynamic lifting and braking functions; with greatly reduced drag increased airspeed and precise control performance at all airspeeds, due to clean uninterrupted airfoil surfaces and directional conformance of wing to the intended flight path.This is accomplished by use of a torque tube mounted internally in the aeroelastic airfoil structure, and firmly attached to the airfoil tip structure. In operation the inboard end of the torque tube when rotated differentially on its pivot axis, imposes a helicoidal twist on the aeroelastic airfoil structure, with maximum angle of incidence at the outboard wing tip, providing near perfect lateral roll control or cooperating to provide increased lift and braking or maneuverability, also the foregoing operations provide automatic deicing. The torque tube can be operated by conventional control systems, e.

Abstract: A failure of any one of three swashplate actuators of a helicopter rotor blade is detected. Once such a detection is made, the position of this nonfunctional swashplate is locked and measured. The inputted commanded swashplate collective position, commanded swashplate x-axis rotational position, and commanded swashplate y-axis rotational position are then passed to a failure-mode control matrix. The failure-mode control matrix computes swashplate actuator commanded positions for the two operable swashplate actuators so that aircraft attitude control is maintained. These two swashplate actuator commanded positions instruct positional movement of the rotor blade swashplate to thereby meet the commanded swashplate x-axis rotational position and the commanded swashplate y-axis rotational position which will control attitude. A quasi-swashplate-collective-position corrector computes the quasi-swashplate collective position that will occur because of the successful control of the aircraft's attitude.

Abstract: A load glider has, between the parachute surface and the load, a device in which a reversible transfer of mechanical energy from the main lines to the steering lines takes place, so that essentially only frictional forces are to be overcome during the operation of the steering lines. The device includes two differential gears, which are arranged in parallel and are accommodated in housings in which a steering line is wound up on a roller with a larger diameter and a main line is wound up on the other roller with a small diameter. Gears, which can be driven by pinions driven by electric motors, are flanged onto the larger rollers.

Abstract: A stabilizing in-flight parachute system for an airplane comprising a retractable canopy built into a top portion of a fuselage of the airplane. A parachute is under the canopy, while a framework is attached to the parachute. A device is for winding and unwinding the parachute on the framework. A facility is for retracting the canopy and exposing the parachute. A mechanism is for accelerating deployment of the parachute out from the fuselage of the airplane, when the canopy is retracted.

Abstract: An aircraft having variable airframe geometry includes an elongate fuselage having top and bottom sides, a swept back, high-speed wing mounted to the top of the fuselage, and a high aspect ratio, low-speed wing pivotally mounted adjacent to the bottom of the fuselage. The low-speed wing is adapted to pivot between a slow speed flight position in which a longitudinal axis of the low-speed wing is generally perpendicular to a longitudinal axis of the fuselage, and a high-speed flight position in which the longitudinal axis of the low-speed wing is generally parallel to the longitudinal axis of the fuselage. A fairing extends from the fuselage for receiving at least a portion of the low-speed wing when pivoted into the high-speed flight position. The low-speed wing further includes landing gear.

Abstract: A method and apparatus for reducing the unwanted sideways motion of an airplane by reducing the lateral side loads and upsets caused by atmospheric turbulence and gusts is disclosed. A rudder modification command that causes the rudder command of the airplane to be changed in a manner that relieves the net force across the vertical stabilizer of the airplane caused by atmospheric turbulence and gusts is produced. More specifically, the pressure differential across opposite sides of the vertical stabilizer is measured and used to produce a rudder deflection value that is roll rate and yaw rate compensated. The compensated deflection value is high-pass filtered with a corner frequency that is twenty-five percent (25%) of the Dutch roll frequency of the airplane. The result is a first rudder deflection value that is subtractively combined with a second rudder deflection value.

Abstract: A special set of elliptical satellite orbits are described which allow preferential coverage of one parameter over another. According to a first modification, the orbits are retrograde, and preferentially cover one geographical location or time of day as compared with another. A second modification uses prograde orbits and allows the apogee of the orbit to be offset a constant amount with respect to the sun, to thereby cover a different time of day relative to the others. According to a special preferred mode of the invention, the apogee is always pointing towards the sun.

Abstract: A reusable single-stage-to-orbit spacecraft and a reusable launch assist platform provide a new system for space transportation. The platform has a frame with a cradle for supporting the spacecraft. Rocket engines attached to the launch assist platform propel the launch assist platform and the spacecraft substantially vertically through the atmosphere for release of the spacecraft. The launch assist platform returns to a predetermined landing site in a power-controlled, vertical descent.The spacecraft is in the shape of a cone having a large, rounded base with a primary load-bearing structure substantially perpendicular to the base. The spacecraft reenters the atmosphere in a base-first reentry, and is slowed and guided to a landing site by using a rocket engine in the base. The spacecraft lands base first on a resilient landing device.