Abstract: A missile has a body with a substantially circular nose opening therein, and a ceramic radome sized to cover the nose opening. A compliant metallic circular transition element is disposed structurally between the radome and the body. The transition element includes an elongated compliant arm region and an upper crossbar region positioned adjacent to the radome such that the lower margin surface of the radome is adjacent to an upper side of the crossbar region. A brazed butt joint is formed between the lower margin surface of the radome and the upper side of the crossbar region of the transition element. A second brazed butt joint is formed between the vehicle body and the lower side of a lower crossbar region joined to the arm region. The brazed joints are formed with a single active braze alloy which permits the entire joining operation to be accomplished in a single furnace cycle.

Abstract: An electronic control system is an in-line module for addition to or partial replacement of automotive vehicle seat control systems for providing massage and improved features of functional control, especially human lumbar massage and diagnostics. The module provides the following improved functions and features: an enhanced driver for automatic lumbar massage, or user taught lumbar massage cycle, and a transparency simulator for low power standby operation, motor stall protection, open motor circuit detection, short motor circuit protection, motor low current protection, motor over current protection, seat position sensor malfunction detection, electrical motor noise attenuation, electrical noise filtering, and also other options. These improvements do not require alternative wiring harness changes and do not affect existing operations of a memory or non-memory seat control mechanism.

Abstract: Apparatus is disclosed for moving an aircraft across a deck surface from a landing position to a stowed position. The apparatus comprises a pair of control beams (26, 28). The control beams are propelled along longitudinal (6, 8) and transverse rails (22, 24) to engage and then position a landed aircraft ready for the aircraft to be guided securely to its hangar by a self-propelled shuttle unit (58). When not in use, the control beams may be stored in the hangar.

Abstract: A mobile mapping system is designed to generate a geometrically precise three-dimensional detailed model of an unknown indoor environment. There is no limit on the distance the mobile system may travel, nor on the type of details that can be mapped. The same design is used for environments ranging from simple office hallways to long winding underground mine tunnels. Surfaces and features can be mapped from images acquired by a unique configuration of different types of optical imaging sensors and positioning devices. This configuration ensures that all the information required to reconstruct the three-dimensional environment is included in the collected images. Provided a sufficient overlap between two-dimensional intensity images and combining such with three-dimensional range images, the method reconstructs an environment by adjusting a plurality of images simultaneously.

Abstract: A method of operating a control system for controlling the electrically-operated components of a motor vehicle in which a central processor and satellite processors for the components are connected with a multiplex single-conductor bus and master signals and control signals are transmitted bidirectionally between the processors along the bus. The central processor and the satellite processors can both operate as masters with respective characteristic addresses and the satellite or central processor upon receipt of a master signal and/or control signal can issue master or control signals with a priority determined by the bus access times of the respective signals.

Abstract: A safety system that will evacuate passengers on an airplane while in flight. The In-Flight Evacuation System operates while the airplane is still in flight. While in operation the In-Flight Evacuation System will systematically evacuate passengers from the airplane. During the process the seats will rotate 180 degrees to face the rear of the plane. The seats will move towards the rear of the plane due to a rotating device connected along the bottom of the seats. When evacuation is deemed necessary, the rear doors on the plane will opened. The seats will continue to be rotated until it reaches the evacuation doors. At that point the seats will disengage. The top portion of the seat complete with a survival kit will be released with the passengers as the bottom of the seat rotates into a open compartment beneath the passenger cabin. A parachute will be activated as the passengers leave the rear of the plane. The passengers will slowly ascend to earth.

Abstract: A multiple altitude satellite relay system is disclosed in which Medium Earth Orbit satellites are continuously linked with at least one geosynchronous satellite to provide uninterrupted relaying of messages and data. The Medium Earth Orbit satellites are synchronized with the geosynchronous satellites to produce continuous links. A parameter to achieve the synchronization involves the positions of the Medium Earth Orbit satellite relays relative to the positions of the geosynchronous satellite relays. Another parameter to achieve synchronization involves the ratio between the orbital periods of the geosynchronous satellite relays relative to the orbital periods of the Medium Earth Orbit satellite relays. These parameters may be further adjusted to provide continuous links above the horizon of the earth.

Abstract: A vehicle yawing behavior control apparatus for controlling the vehicle behavior to bring the actual vehicle yawing motion into agreement with the calculated target value calculated based on the parameters representing a condition of vehicle movement. At least vehicle yaw rate and slip angle representing an actual value of vehicle yawing motion is detected. When the detected vehicle slip angle is directed outside with respect to the vehicle movement and is greater than a reference slip angle, the calculated target vehicle yawing motion value is corrected outside with respect to the vehicle movement to a greater degree at a greater deviation of the detected vehicle slip angle from the reference slip angle. The reference slip angle is increased as the calculated target vehicle yawing motion value increases.

Abstract: The boundary layer of a fluid travelling in a mean-flow direction relative to a surface of a wall of a body is controlled by generating in the fluid a magnetic field B having flux lines along the surface of the wall and an electric current density J traversing the magnetic flux lines in the fluid to form a control region. The magnetic field B and the electric current density J create in the control region a force J.times.B that introduces a vorticity distribution .omega. (x,y,z,t) into the flow. A plurality of such control regions is arranged in an two-dimensional array of control tiles that are actuated such that over the array the vorticity at the wall in the direction transverse to the free-stream direction is reduced and creation of the boundary layer vorticity concentrations in the free-stream direction is inhibited.

Abstract: The present invention provides a radio navigation emulating GPS device. In one embodiment, the radio navigation emulating GPS device receives an identifier associated with a conventional radio navaid. The present radio navigation emulating GPS device then retrieves latitude and longitude information corresponding to the received conventional radio navaid from a database. A satellite based position information system generates position information for the aircraft on which the present radio navigation emulating GPS device is disposed. The present radio navigation emulating GPS device then generates navigation information for the aircraft using the retrieved latitude and longitude information and the satellite based position information for the aircraft. The present radio navigation emulating GPS device then presents the navigation information in a manner which emulates the presentation of navigation information generated by a conventional radio navigation device.

Abstract: A low earth orbiting satellite control arrangement according to the invention has an earth sensor for measuring roll and pitch of the satellite relative to an earth oriented moving reference system, a spin wheel mounted along an axis perpendicular to the orbital plane of the satellite for measuring spin of the satellite, and two magnet coils for generating control. A first of the two magnet coils is aligned substantially in parallel to a roll axis of the satellite, and the second is aligned substantially parallel to the yaw axis. Alternative control algorithms are disclosed for controlling attitude, nutation and spin of the satellite based on information from the earth sensor, spin wheel and an observer which is also mounted on the satellite.

Abstract: A controller for a motor vehicle device, such as a transmission. The transmission ratio is automatically controlled in dependence on at least the accelerator pedal position and the driving speed, using stored characteristic maps. A fuzzy logic circuit has at least one rule base. Various signals, which characterize driving states and the load state of the motor vehicle, are evaluated by the fuzzy logic circuit and control signals are generated in response. The control signals define the transmission ratio. At a predefined dynamic driving state, an additional control signal is generated by the fuzzy logic circuit, by means of which signal a change to the transmission ratio is carried out. That change is independent of the respective characteristic map. Dynamic driving states of this type are, for example, the occurrence of an impermissible wheel brake slip or driving down relatively long downhill gradients.

Abstract: The disclosed flight control system includes a rotor blade speed monitor for monitoring the rotor blade speed of the jet powered tri-mode aircraft and for outputting a rotor blade speed command. The flight control system also includes an aircraft attitude controller for controlling the aircraft attitude of the jet powered tri-mode aircraft. Weighted rotor blade attitude stabilization commands and weighted aero surface attitude stabilization commands are output from the aircraft attitude controller to distribute power, control, and lift between the rotor blade and the aero surfaces. Relative weights of the weighted rotor blade attitude stabilization commands decrease with increasing aircraft travelling velocities, and relative weights of the weighted aero surface attitude stabilization commands increase with increasing velocities.

Abstract: A method of enhancing vehicle stability and response in a vehicle having an active roll control system with front and rear suspensions each including an anti-roll bar, and the control system including a hydraulic system for providing an anti-roll moment which acts on the vehicle by means of hydraulic cylinders connected to the anti-roll bars, includes the following steps: a) determining the vehicle speed; b) determining the steering wheel angle; c) calculating the desired vehicle yaw rate based upon the determined speed and steering wheel angle; d) sensing the actual yaw rate; e) comparing the desired yaw rate to the actual yaw rate; f) increasing the percentage of the anti-roll moment provided to the rear anti-roll bar if the actual yaw rate is less than the desired yaw rate, thereby decreasing understeer, increasing yaw rate, and enhancing vehicle response; and g) increasing the percentage of the anti-roll moment provided to the front anti-roll bar if the actual yaw rate is greater than the desired yaw rate

Abstract: A hybrid system for stabilizing the attitude of an instrument relative to a dynamic platform includes a plurality of (roll, pitch and yaw) inertial rate sensors, whose outputs are sampled at a rate sufficient to provide real time tracking of changes in orientation of the platform, and a global positioning system (GPS) receiver, whose precision platform attitude output is updated periodically, but at a rate less than the rate of change of attitude of the platform. The inertial rate sensors provide effectively continuous motion (e.g., angular rate) data signals representative of three-dimensional changes in attitude (position derivative signals) of the platform. The inertial rate output are integrated to provide output signals representative of the dynamic orientation of the platform. Sequential outputs of the integration-processing circuitry are also coupled to a sample buffer, which is controllably read-out in accordance with the periodic updates from the GPS receiver.

Abstract: An aerial cargo container system for transporting cargo from an aircraft to the ground having a cargo box with a continuous side wall with six rectangular side panels, and rotor blades having stowed positions against alternating box side panels and deployed positions extending outwardly from the box in a generally horizontal plane. Each blade may include a lower panel and an upper panel that has two triangular sections behind the leading edge that forms an aerodynamic camber. The blades are hinged to a rotor hub secured across the top of the box. The upward deployment of the blades is limited by tethers extending from the blades down to a tether attach frame secured across the bottom of the box. The box and blades are preferably formed of corrugated paper or plastic material. The entire unit rotates with the load to create aerodynamic braking and lower cargo to the ground with a minimum of energy being translated to the cargo on impact.

Abstract: The apparatus of this invention includes a pilot-induced oscillation (PIO) detector, a PIO compensator and a pilot input modifier. The PIO detector is coupled to receive aircraft state signal including the aircraft's pitch, roll and yaw attitudes. The PIO detector is also coupled to receive pilot control signal generated by the aircraft's pilot by manipulation of flight control instruments. Preferably, the PIO detector includes a feature calculator and a discriminator. Based on the aircraft state signal and the pilot control signal, the feature calculator generates at least one feature signal indicative of whether a PIO or non-PIO condition exists in the aircraft. The feature calculator supplies the feature signal to the discriminator, that uses the feature signal to determine whether or not a PIO condition exists.

Abstract: The thrust reverser for a turbo-fan engine is comprised of: a plurality of oors located in openings radially spaced in a shroud enclosing the engine and canalizing the jet flow from the engine, the doors being adapted to be pivoted, within a fixed structure, from a stowed position, in which they do not interfere with the jet flow, to a deployed position in which they block the jet flow and deflect it through the openings; an actuator having a body attached to the fixed structure and a rod attached to the center of each pivoting door for moving the door from the stowed position to the deployed position, and vice versa; and sealing elements comprising a main seal provided on the fixed structure and a separate annular seal located around the actuator body, the sealing elements mating with each door, when in the stowed position, and with the fixed structure to prevent pressure leakage of the jet flow.

Abstract: A non-geostationary low earth orbit satellite constellation using elliptical orbits with apogees in the Northern Hemisphere to provide continuous coverage over the Continental United States of America (CONUS), and by extension to the other points in the Northern Hemisphere situated above 25.degree. north latitude. The constellation provides time-continuous visibility with at least one satellite to any point above 25.degree. North latitude. An extension of the constellation has a combination of the elliptical orbits and at least one equatorial orbit to provide virtual global coverage. The distribution of capacity is deployed in proportion to the distribution of populations in the land masses of the earth. Time continuous visibility with at least one satellite is maintained by any point on earth north of the 50.degree. South latitude, with a minimum number of satellites deployed.

Abstract: The craft is for hovering flight, vertical takeoff and landing, and horizontal forward flight. It has a tail-sitting fuselage and a ducted fan mounted to the fuselage aft to provide propulsion in both (a) hovering and vertical flight and (b) horizontal forward flight. At each side is a floating wing, supported from the fuselage for passive rotation (or an actuator-controlled optimized emulation of such rotation) about a spanwise axis, to give lift in forward flight. The fuselage attitude varies between vertical in hovering and vertical flight, and generally horizontal in forward flight. Preferably the fuselage is not articulated; there is just one fan, the sole source of propulsion, rotating about only an axis parallel to the fuselage; and thrust-vectoring control vanes operate aft of the fan.