Abstract: A nose assembly and method for controlling the rotation and stabilizing the orientation of a vehicle during landing maneuvers. The vehicle includes a nose assembly that is coupled to an airframe thereof and that has a frame and flap assembly. The flap assembly includes an actuating means and a flap coupled to the frame such that the actuating means moves the flap from and between a fully retracted position and a fully extended position in response to a guidance signal received from a flight control computer. In a preferred embodiment of the present invention, the flap assembly includes a plurality of flaps each coupled to the nose assembly frame and an actuating means that selectively positions the plurality of flaps in response to a signal.

Abstract: A combined flying machine comprises a fuselage (1) in the form of a central hick wing with a vertical open tunnel (2), in which there is mounted a lifting rotor (4). Said machine is also provided with outboard wings and a tail unit (8). The machine is equipped with a landing device on an air cushion (19) that surrounds an outlet from the tunnel. A power plant of said flying machine comprises two engine modules (13), disposed from two sides of the tunnel (2) and connected with the lifting rotor (4) and the propulsion propellers (12). The area of the tunnel cross-section in the plane of the lifting rotor rotation amounts to 0.3 to 0.8 of the area of the landing device air cushion, which ensures a safe landing of the flying machine on an unprepared landing site even with a failure of one of the engine modules.

Abstract: It is known to use a rigid cone to provide stability to a body being towed by an aircraft. However, such cones are useful over a limited range of speeds. The invention provides a drag-producing aerodynamic device in which the cross-sectional area of the structure producing drag is variable. The cross-sectional area of the structure producing drag decreases as the towing speed, and hence the dynamic air pressure acting on the structure producing drag, increases and vice versa.

Abstract: A communication system including a constellation of a plurality of artificial satellites orbiting the Earth, each artificial satellite having communication apparatus providing communication with the Earth, characterized in that the plurality of artificial satellites are in triply-geosynchronous (TGS) orbits having a period of eight sidereal hours, or twice-triply-geosynchronous (TTGS) orbits having a period of sixteen sidereal hours, which orbits are inclined with respect to the Equator and synchronized with the Earth's rotation such as to exploit the natural spacing of approximately 120.degree. in longitude of the major land masses of Europe, North America and the Far East for communication with the artificial satellites to provide for higher elevation angles in such land masses than in other areas.

Abstract: This is a ?relatively! simple load lifting apparatus, tongs-like in appearance, with a larger lower portion for grabbing loads of various sizes. It has two embracing halves, pivoted at a selected distance from the apparatus' top. ?Its lower portions tend to be vertical to enable it to hold a containerized load in place, as in previous Gabriel's U.S. Pat. No. 5,209,538.! It is designed to safely and reliably hold a person between its lower portions without injuring one who may be wounded ?on the battlefield or in the ocean!. Sensors are added to enable it to sense the distance of the apparatus' lower portions from the load. When in range of the load, its lower portions automatically separate to straddle the load ?without making contact with it!. When the flexible fingers, extending inward from the bottom of each lower portion, touch a platform surface or terrain, then a motorized gearing may cause the lower portions to come together.

Abstract: A fuselage door for a pressurized aircraft fuselage in which the hoop tension loads caused by cabin pressure are carried through the door rather than around the door. Stationary interlocking moldings in the door and fuselage door seat transfer loads through the door-fuselage intersection. The interlocking portions of the moldings have a sloped engaging portion having an angle such that the inward directed force component of tension due to a pressure differential is less than the outward directed force from cabin pressure on the door.

Abstract: An aircraft of the type having retractable landing gear and a pusher propeller is provided with a twin tail boom. The tail boom has a configuration to prevent the lowermost point of the pusher propeller from contacting a landing surface when landing the aircraft, even with the landing gear retracted, so that the engine of the aircraft is not damaged as a result of the pusher propeller being unable to rotate during the landing.

Abstract: The present invention provides a method and a system for proximate field orientation of an autonomous device and utilizes a transmitted wave having a first frequency of slow propagation, whereby reflections from obstacles within a proximate area are detected. According to the present invention receivers are arranged in a slanted plane or preferably along a curved base-line to, in a simple way, obtain a three-dimensional direction to an obstacle reflecting the frequency of slow propagation. Additionally, an absorber or a screen or a combination thereof is arranged above at least one receiver to act as an "eyebrow" attenuating undesired reflections which at the receiver come from overhead.

Abstract: A triaxially stabilized earth oriented satellite is provided with an attitude control system. The attitude control system contains a controller, final control elements for generating control torques around each of three axes of a system of coordinates (principle axes x, y, z) fixed relative to the satellite. Additionally, the attitude control system comprises, as measuring transducers, exclusively a direction vector measurement device, like a magnetometer or star sensor, a sun sensor array and an earth sensor. The process of the invention makes use of the apparatus as noted above and includes the steps of:A. determining an estimate for the rotating velocity of the satellite from a direction vector measurement;B. searching for the sun, depending on the size of the field of view of the sensor, by one or two search rotations at right angles to the optical axis;C. adjusting the direction of the sun relative to the optical axis; andD. adjusting the direction vector measurement to a reference direction S.sub.

Abstract: A space platform assembly designed to be attached to the outer surface of a space station structure for deployment of a tethered space platform into isolation orbit alongside the space station. The space platform is designed to carry payloads such as for research experimentation in the microgravity environment of space. The tether comprises a loose power/data umbilical for the deployed space platform while it orbits free of the vibration and g-jitter problems of the space station.

Abstract: The invention relates to a surface of a body exposed to circumfluent fluid with elevations protruding from the base surface.In order to design the surface of a body exposed to circumfluent fluid with elevations protruding from the base service with an even more favorable flow, it is provided that when the surface is viewed from the top the elevations are bordered in each case by two boundary lines of which the one boundary line is longer and possesses a greater curvature than the other boundary line so that the cross-section area of an airfoil is produced.

Abstract: An aircraft modal suppression system which recognizes that the frequency and phase of the body bending mode varies when the weight of the aircraft differs from the design gross weight. An active damper notch filter which is tabulated as a function of aircraft gross weight is utilized, thereby enabling not only the frequency, but also the width and depth of the notch filter to vary according to the gross weight of the aircraft.

Abstract: Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) with a belt drive system for turning wing-situated propellers; compound landing gear integrating ski, pontoon and wheel subcomponents; pivotal mounting armatures for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure featuring extendable wing panels that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water.

Abstract: One embodiment of a mechanical emergency dual-release mechanism for use in combination with a helicopter external cargo hook system that includes a cargo hook assembly that is operative to jettison an externally-attached cargo includes an interface member for mounting the dual-release mechanism in rigid combination with the cargo hook assembly, a pulley axle mounted in rigid combination with the interface member, a cockpit pulley assembly mounted in rotatable combination with the pulley axle, a cabin pulley assembly mounted in rotatable combination with the pulley axle, and a displacement transfer member that operatively interconnects the cockpit pulley assembly and the cabin pulley assembly. The cabin pulley assembly is functionally interconnected to the cargo hook assembly and operative in response to a mechanical stimulus generated by means of the cockpit pulley assembly or the cabin pulley assembly to activate the cargo hook assembly to jettison the externally-attached cargo.

Abstract: A reduced amplitude corrugated web spar for use in airplane wings and the like is disclosed. The amplitude of the corrugation is determined based upon general stability requirements of the spar, and the fasteners are offset from the center line of the web corrugations. The resulting spar is easier to manufacture and still provides the structural integrity required of the wings.

Abstract: An effective method for diminishing hydrocarbon vapors in fuel tanks and thereby avoiding expensive, complicated and risky procedures for capturing purged hydrocarbon vapors during refueling. The method involves filling the fuel tank with multiple pieces of expanded metal net formed in the shape of ellipsoids, to inhibit the formation of hydrocarbon vapors and to promote condensation of such vapors as may be formed.

Abstract: A cover and method for applying the cover unto the wing comprising a flexible material to cover the top surface of said wing, said material having a leading edge to cover the leading edge of said wing and a trailing edge to cover trailing edge of said wing; a first set of spaced apart attachment straps each said first attachment strap extending from said trailing edge of said cover under said wing for quick release attachment to said leading edge of said cover, so as to attach and quickly release said cover to said wing; a second set of spaced apart removal straps, each said straps extending from said leading edge of said cover over said wing for quick release attachment to said trailing edge of said cover so as to remove said cover from said leading edge to said trailing edge of said wing by pulling said removal straps.

Abstract: A modular launch pad for a launch vehicle which comprises a frame and a plurality of building units separably connected to the frame by means of connectors. The building unit comprise a concrete slab and a peripheral frame made of U-shaped channel sections connected to one another to form a frame, wherein the legs of the U are directed inwardly to engage the major surfaces of the slab. At least one of the legs of the channel sections is partially embedded in the slab so that the outer surfaces of the legs lie flush with the portion of the major surface extending between the legs. A plurality of longitudinally and transversely extending reinforcement bars are embedded in the concrete slab and a plurality of connecting means are secured to the slab. The pad has a launch vehicle mount for supporting a launch vehicle and defines exhaust gas channels in flow communication with an exhaust gas opening in the mount.

Abstract: The present invention provides a method of fastening an outer composite aircraft skin (12) to an inner substructure (14), which may be the wall of a fuel tank. The method includes the steps of incorporating an electrically conductive layer (26) in an outer surface of the outer composite skin (12), inserting a bolt (11) through the electrically conductive layer (26) and the outer composite skin (12) and through the inner substructure (14), securing the bolt (11) by means of a nut (22) directly or indirectly engaging the inner surface of the inner substructure (14), and applying insulating material (34) over the head (16) of the bolt.

Abstract: A modular payload structure providing standardized thermal, electrical and mechanical interfaces. The modular arrangement of the present invention has fixed radiator panels that have standard thermal and mechanical interfaces, allowing communication modules to "plug in" directly to the payload structure. In the case of high thermo-energy dissipating modules, heat pipes on the modules connect to the thermal interfaces and move energy from the modules to the thermal interfaces of the radiator panel.