Abstract: Apparatus for compactly storing and retrieving a plurality of movable devices of the same size and external configuration, particularly containers in an aircraft, includes a support for horizontally supporting the movable devices in the form of a two-dimensional matrix constituted of two columns and a plurality of rows of two devices in each row, with a vacant space for one device in each of the first and last rows of the matrix. The apparatus further includes longitudinal and transverse transfer assemblies for shifting the devices to permit them to be selectively stored or retrieved, and retainer members engageable with the outer faces of the devices for securing them against movement at all times except during an actual storing or retrieving operation.

Abstract: The present invention is generally comprised of a sonotube-compatible unmanned aerial vehicle apparatus, hereinafter referred to as a UAV, and systems for launch and control of the UAV. The UAV is generally comprised of modular sections including a nose section, a payload section, a wing and fuel tank section, and a powerplant section. The modular sections are attached to adjacent sections by uniform lock sealing rings and related components. The present invention comprises an apparatus enabling very small, man portable, ballistically launched, autonomously or semi-autonomously controlled vehicle to be deployed with preprogrammed, communicated, or telemetry mission programming. A wide range of payload packages, including emergency supplies, sensors, and antenna assemblies, may be carried, used or deployed in flight. Man-portable operation is accomplished by the use of a launch canister apparatus.

Abstract: A thin film polymeric membrane is made from a plurality of adjacent sections that are bonded together along longitudinal seams taken with reference to an axis of symmetry. The membrane is reinforced laterally by a continuous helical reinforcing fiber pattern that passes the reinforcing fiber(s) a plurality of times over each of the longitudinal seams. The membrane desirably is in the shape of a parachute or balloon envelope.

Abstract: A main rotor torque compensation apparatus for a helicopter having a main rotor and a tail rotor includes vertical tails that are supported at a variable angle of attack. An actuator adjusts the angle of attack such that the main rotor torque is compensated by the torque of the tails together with the torque of the tail rotor.

Abstract: The improvement to aircraft or high-speed vehicles in this invention comprises an elongated uniform fuselage with a flattened rectangular, oval or circular transverse cross-section, to take a form whose side view is a rhomboid with the longer sides horizontal and in which the inclined flat frontal surface is a ramp beginning in front at the top, dropping along and inclined backward until meeting the base, the inclined surface of the tail is parallel to the front surface, that is, with the rear surface beginning at the top, dropping along and inclined backward until meeting the base having the unions between the other, non-lateral surfaces suitable rounded.

Abstract: A thrust reverser is disclosed for a high bypass ratio turbofan jet engine having a fan cowling forming an outer boundary of an airflow duct and a jet engine structure including a jet engine cowling. The thrust reverser has a casing affixed to the jet engine structure, the casing having a plurality of attaching yokes. A first thrust reverser flap is pivotally connected to a corresponding one of the attaching yokes and is located rearwardly of an exit of the airflow duct, each first thrust reverser flap having a distal end and being movable between a forward thrust position, and a reverse thrust position. A second thrust reverser flap is pivotally connected to the distal end of a corresponding one of the first thrust reverser flaps and is also movable between a forward thrust position, and a reverse thrust position, wherein the second thrust reverser flaps also redirect air flow emanating from the air flow duct.

Abstract: The ground impact velocity of a parachutist is reduced by a single, length-shortening, retraction device mounted between the parachute riser webbings. The gas generator-activated retraction device is activated by a ground proximity device based on electromagnetic or ultrsonic radiation reflected from the ground. The retraction device is fully integrated, eliminating any need for wires or connectors. An alternative design for the ground sensor is a wire-dangled mechanical ground sensor. The system allows steering of the descending parachute.

Abstract: A flow control device and method for eliminating flow-induced cavity resonance within a closed or nearly closed end flow passage (20) having an inlet opening (30) defined between an upstream inlet edge (32) and a downstream inlet edge (34). The passage accepts exterior fluid flow (38) therein via the opening (30). The flow control device includes a stationary inlet guide vane (44) having a leading edge (46), a trailing edge (48), and a number of support members (50) to connect the vane to the inlet. The vane (44) is positioned such that the vane leading edge intercepts the exterior fluid flow shear layer, and the vane trailing edge extends into the passage at the inlet. In a preferred embodiment, the inlet guide vane is located approximately midway between the upstream and downstream inlet edges. The inlet guide vane is cross-sectionally shaped as a cambered airfoil.

Abstract: The aircraft air conditioning energy recovery device exploits the high level energy in relation to the exterior, in the air conditioning air flow required for renewal, and involves the placement of the aircraft outflow valve in a duct through which all the air flows the duct being arranged from the pressurized cabin to the inside of the engine inlet diffuser, through the pylon and in some cases through the wing, with the air-conditioning flow being fed back to the input air flow through multiple openings on the inside wall of the inlet diffuser. The openings or grooves run at a slight angle to the direction of flow to avoid turbulence. The air conditioning input may be introduced through hollow radial guide vanes attached at the front end to the vanes of the first stage of the low-pressure compressor and to the hollow vanes, open at the back, in the first stage or stages of the low-pressure compressor stator where the pressure is lower than that of the cabin air.

Abstract: A Satellite Weather Modification System (SWMS) uses earth satellites to harness solar energy to modify the thermodynamics and composition of the earth's atmosphere. SWMS has three subsystems: The first subsystem includes a network of earth satellites called Satellite Engines (SEs) used to reflect solar energy and/or transform solar energy into other forms of energy beams discharged at specified locations. The media at these locations and the media through which the energy beams pass absorb these energies and change them into heat. The second subsystem includes a large network of Remote Sensing Devices (RSDs). These sensors are used to measure local media compositions, dynamic parameters and thermodynamic properties. Sensor measurements are fed back to the third subsystem, which includes a network of Ground Control Stations (GCSs). GCSs provide energy beam guidance by estimating each beam's characteristics and its aim point trajectory as functions of time.

Abstract: An ascent vent cover (24) for covering and sealing vent holes (22) in a payload launch vehicle (21) is disclosed. The ascent vent cover (24) includes a magnetic sheet (32) for covering the vent hole (22) and attaching the ascent vent cover to the payload launch vehicle, a plurality of magnets (34a, 34b, 34c, . . . ) for augmenting the holding strength of the magnetic sheet, and a stiffening panel (38) for facilitating the peeling of the ascent vent cover away from the payload launch vehicle (21). The magnets (34a, 34b, 34c, . . . ) are secured to the magnetic sheet (32) so that some are positioned in a circular pattern so as to surround the underlying vent hole (22) and others are positioned along a leading edge of the magnetic sheet (32). The stiffening panel (38) includes a cover portion (39) and a tab portion (40) for securing to the magnetic sheet (32). The magnets (34a, 34b, 34c, . . . ) are embedded in the cover and tab portions.

Abstract: An actuation activation system for an aircraft engine thrust reverser system is provided including an improved locking actuator (29), a sleeve sensor mechanism, and auto-restow control logic. The locking actuator (29) includes a lever (57) corresponding to whether the actuator is locked or unlocked. A slide-by first proximity sensor (45) is positioned near the lever and set to normally far and triggering near. The first proximity sensor produces a first trigger signal for use in the auto-restow control logic. The sensor mechanism includes a second slide-by proximity sensor and a target in communication with a thrust reverser translating sleeve. The second sensor is connected to the forward side of an engine torque box. A preferred embodiment sensor mechanism (78) is provided and includes a pivotable target arm (96) having a proximal end (98), a distal end (100), and a middle portion pivotably connected to fixed engine structure, preferably torque box (30).

Abstract: The invention relates to a communications and/or navigation system based on a constellation of non-geostationary satellites in orbit around the terrestrial globe. The constellation has satellites grouped in pairs, and has orbital planes that are also grouped in pairs. The pairs of orbital planes are mutually spaced apart by an angle that is different from the spacing between the orbital planes in a pair of orbital planes, and the satellites in a pair have orbital phase offsets different from the orbital phase offset between pairs of satellites in different pairs of orbital planes. This type of constellation makes it possible to ensure continuous coverage, via at least one satellite, of a geographical zone of interest, while taking into consideration the frequency-coordination constraint.

Abstract: A three-axis stabilized spacecraft having roll, pitch, and yaw axes and when on station in orbit about the earth having a north face and a south face is equipped with a first and second thruster which may be electric thrusters. A first support device mounts the first thruster adjacent the north face and the first thruster is positioned a spaced distance away from the north face in a first direction parallel to the pitch axis and spaced from the pitch axis in a second direction normal to the pitch axis. A second support device mounts the second thruster adjacent the south face, the second thruster being positioned a spaced distance away from the south face in a third direction opposite the first direction and spaced from the pitch axis in the second direction. A gimbal mechanism pivotally mounts the first and second thrusters on the first and second support devices, respectively, for selectively positioning the attitude of the first and second thrusters.

Abstract: The detonating valve for releasing openings of air bag landing systems for aircraft and spacecraft has a wedge type charge and a cover closing the opening, which cover is shorn off during the ignition of the wedge type charge. The cover is a thin-walled disk or a membrane, which is integrated either within the aircraft and spacecraft or within the air bag landing system.

Abstract: A rotor for rotary wing aircraft has a tip to tip flex-beam spar and torsionally stiff hollow blades bonded to the spar throughout the tip-most portion of the blades. The spar spaced-apart spar caps which have a dual beam cross section in the region not bonded to the blades so that the spar is twistable for pitch control. The rotor spindle and controls pass through a central hole between the spar caps. An intermediate section of the rotor has shear webs bonded above and below spaced-apart spar caps, providing a stiff box beam cross section. The spar caps join each other outboard of the intermediate section. The collective control for pitch change employs a coil spring mounted between a pitch horn and a hub.

Abstract: A brake control apparatus for a vehicle employs a pressure-amplifying device which reduces a quantity of brake fluid generating a first brake-fluid pressure in a first conduit connected to a master cylinder, and increases second brake-fluid pressure in a second conduit, applied to a wheel cylinder simultaneously with the reduction in brake-fluid quantity in the first conduit. As a result, increase in the first brake-fluid pressure is suppressed even when a driver depress a brake pedal and load to generate the first brake-fluid pressure is alleviated. Additionally, the pressure-amplifying device applies the increased second brake-fluid pressure to the wheel cylinder. Therefore, it is possible to ensure sufficient braking force.

Abstract: A water-impact release mechanism has a hub with a first sleeve coupled thto. The first sleeve has a plurality of circumferentially distributed holes therein. A spring assembly, coupled to the hub, extends into the first sleeve. In a relaxed state, the spring assembly obstructs the holes while, in a compressed state, the spring assembly does not obstruct the holes. A second sleeve, concentric with the first sleeve, is elastically coupled to the hub and biased away therefrom. The second sleeve has an inwardly-facing annular groove. A ball resides in each of the holes and is large enough to extend beyond the confines of its hole. When the bias of the second sleeve is overcome, the annular groove aligns with the holes in the first sleeve thereby allowing the radial outward movement of the balls. A plate, coupled to the second sleeve, extends radially outward therefrom to define a water-impact surface.

Abstract: A satellite system and method comprises a satellite 10 induced to roll 46 and pitch 52 in its orbit 12 to keep antennae 34 36 pointing ever directly at the nadir 40 as the nadir moves over the surface of the earth 14. The satellite 10 has a yaw rotation 54 designed to keep the solar panels, which rotate only about one axis, ever pointing at ninety degrees to the direction of the sun 42 for maximum solar panel efficiency. The beam pattern of the antennae 34 36 is counter-rotated to oppose the yaw motion 54. Compensation for the season of the year is applied.

Abstract: Roller skate comprising the body of a shoe (11) wherein the skater's foot and part of the leg are housed, associated with a support (12) on which the skating elements (13) are mounted, there being included at least a front skating element (13a), a middle skating element (13b) and a rear skating element (13c), the roller skate in that the shoe (11) being constrained to the support (12) at least by means of an articulated oscillation connection (19) and cooperating with the support (12) by means of a guide element (18), the skating elements (13) having a diameter of between 90 and 120 mm and the support (12) including assembly seatings for the skating elements (13) defining a first position where the skating elements (13) are substantially aligned, and a second position of vertical limit where at least the front skating element (13a) is in a raised position with respect to the skating surface (20), by a value at least one sixth of the diameter of the middle skating elements (13b) and in any case not less than 1