Abstract: In a novel hovering aircraft, an airfoil blade structure rotatable about a vertical axis comprises a set of upper blades and a set of lower blades, all having variable lift, the upper blades converging toward the lower blades from root to tip. Struts, located inboard of the blade tips, keep the tips of the upper and lower blades separate from each other to reduce interference effects, and also support motors and propellers.

Abstract: An system is provided for testing emergency lighting units using a receiver connected to the emergency lighting unit and a portable transmitter operable remotely with respect to the emergency lighting unit. The emergency lighting comprises a transfer relay for switching a battery between a primary power source and a lamp. A TEST button and the receiver each include a normally closed contact switch connected in series with each other, as well as with a primary power source input and transfer control circuitry. The transmitter generates encoded signals for wireless transmission to the receiver as long as a control switch on the transmitter is being activated by a user. The receiver receives and decodes the encoded signals and opens its normally closed relay as long as encoded signals are being received, causing the transfer control circuitry to activate the transfer relay to switch the battery from the primary power source to the lamp.

Abstract: An earth chord sensor on board a satellite produces an electrical pulse as the satellite spins and sweeps the sensor across the earth. If the satellite is spinning at a low spin rate or if the sensor is measuring a long earth chord, the sensor produces an irregular pulse with sharp voltage peaks rather than a near trapezoidal pulse. The present invention digitizes the output of the earth chord sensor and a processor processes the digitized output through a data buffer to detect the leading edge peak and trailing edge peak of the pulse. The processor may detect the peaks through parabolic curve fitting among the digitized data points of the sensor output. The processor calculates the earth chord time as the time width of the pulse between the detected leading edge peak and trailing edge peak of the pulse and transmits, by telemetry, the calculated earth chord time to a ground station for use in satellite positioning.

Abstract: A fuzzy logic control method for controlling an electrical motor aided, manually powered vehicle is disclosed which is used to assist a rider of the vehicle. The vehicle comprises a gear transmission for driving the vehicle, a manually powered operator for receiving a manual force inputted by the rider for manual operation of the gear transmission, a servo motor for generating a torque output, a reduction gear and a clutch for coupling the torque output of the motor to the gear transmission, a brake for reducing speed of the vehicle, a force sensor for sensing the manual force applied by the rider to the manually powered operator, a speed sensor for sensing speed of the vehicle, a brake sensor for sensing on and off of the brake; and a motor sensor for sensing output of the motor.

Abstract: A roadable helicopter according to various aspects of the present invention comprises a vehicle that drives like a conventional car in its road configuration, and converts to fly like a helicopter in its flight configuration. The operator of the helicopter only needs to press a button to initiate the conversion from one configuration to the other. To facilitate the flight configuration, the helicopter is preferably equipped with a dual, coaxial counterrotating rotor system to provide lift, propulsion, and control in the flight configuration. In the road configuration, however, the rotor system automatically folds into a rotor bay formed in the rear of the helicopter. The roadable helicopter may also include an automatic control/stability/navigation system that permits fully automatic flight.

Abstract: A constellation (100) comprising a plurality of man-made satellites (1-27). The satellites (1-27) orbit a celestial body (110) along a plurality of orbits (120-128), which are located at a substantially common altitude and have a substantially common inclination. The satellites (1-27) are positioned in a predetermined order substantially along a wave (130). Each satellite (1-27) maintains its position in the predetermined order along the wave (130) while orbiting the celestial body (110). A system in accordance with the invention may further include a ground station adapted for enabling communication with at least one of the satellites (1-27). The satellites (1-27) may be positioned based on a Walker code T/P/F, where T is the total number of satellites (1-27) in a full Walker rosette corresponding to the Walker code, P is the number of distinct orbits (120-128), and F/T is the phase shift between adjacent orbits (120-128).

Abstract: Herein disclosed is a flight control system comprising a control member, a control surface controllable to assume different angle positions within a control angle range, a transmission linkage provided between the control member and the control surface to transmit the control force from the control member to the control surface, and a power assist actuator associated with the control member and the transmission linkage to control the control surface.

Abstract: In a satellite (20), two-axis solar panel drives (56, 58) allow two degrees of rotational freedom of movement for solar panels (22, 24). Regulation of electrical current loops (46, 48) within the solar panels (22, 24) generates a magnetic field. When the solar panels (22, 24) are tilted about an overturning axis (28), the magnetic field provides a component of a control torque about a pitch axis (30). An on-board processor (52) commands the panel drives (56, 58) and a magnetic torque actuator (60) to instantaneously and simultaneously damp disturbance torques about a windmill axis (26), an overturning axis (28), and a pitch axis (30). The processor (52) allows disturbance torque to be corrected continuously rather than periodically over the course of an orbit. Counter-disturbance torques (90) are applied (88) in synchronism with a satellite nutation frequency (76) but out of phase with the nutation so that nutation is damped.

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 deployment control method for distributed architecture SIR system provides improved fault tolerance and ensures that signals generated by various remote sensor modules are properly considered in determining whether to deploy restraint devices. The deployment control method establishes a succession of states, wherein entry into each state is conditioned upon the achievement of predetermined criteria, and deployment of a respective restraint device is conditioned upon the successive achievement of each state. The states include an inhibit state, an enabled state, an armed state and a deployment initiated state. The predetermined criteria include correct occupant position, collision verification or safing, and collision severity. Deployment can only be initiated when the initiator module has been advised that all three criteria have been met within a given time constraint.

Abstract: A supersonic flight aircraft having a longitudinally forwardly extending fuselage having an axis in the direction of flight, and a wing, and which comprises the wing extending generally laterally relative to the axis, and having a leading edge angled forward or rearwardly relative to a normal to the axis at an angle , and the wing having leading edge sharpness defined by upper and lower wing surfaces, which taper toward the leading edge to define an angle .delta., closely proximate the leading edge at all spanwise locations; the angle and sharpness .delta.

Abstract: A vehicle tracking method and system using the cellular network infrastructure is disclosed. A cellular transceiver which is installed in a vehicle that requires tracking, operates on a continuous standby mode to remain constantly accessible to the cellular security provider. The cellular transceiver is turned to an active mode when tracking of the vehicle is initiated. The general location of the stolen vehicle can be determined by paging the cellular transceiver located in the stolen vehicle to identify one or more cell sites located near the stolen vehicle. The information is then relayed to a tracking vehicle which makes use of a radio direction finder to obtain an accurate bearing on the location of the stolen vehicle.

Abstract: A hybrid vehicle includes an engine for producing propulsive forces, an electric motor for selectively generating assistive drive forces in addition to the propulsive forces and generating electric energy converted from the propulsive forces, and an energy storage unit for selectively supplying electric energy to the electric motor and storing electric energy converted by the electric motor.

Abstract: A process and an arrangement for determining the position of a vehicle moving on a given track by using a map matching process is provided. At least three types of position measuring data in the form of object site data, path length data and route course data are obtained. By use of a computer unit, for each type of measuring data, a data correlation is carried out with a respective pertaining stored desired data quantity for the determination of respective position results which then are evaluated, in an m-out-of-n decision making process. In this process, a given number m of the n determined position results is taken into account. With comparatively low expenditures, this permits a reliable and error-tolerant vehicle position determination for use, for example, for railway vehicles.

Abstract: An aircraft with automated means to transport. Spherical or one of its segments, without airfoils for lift or guidance. Means for flight are housed within the aircraft. The outer-most sureface is configured to disrupt the air-flow, over its surfaces, in flight. This, to reduce skin-friction and drag coefficients, and mollify heat build-up on the skins outer surfaces as speeds increase to and beyond mach 1. The weight of gas per unit volume, with temperature variations, is the means to reduce the gross-weight and adjust for temperature and weight changes during flight. Propulsion, within the propulsion component, is provided by turbojet engines. They are secured within an inner compression pod and an outer combustion pod. The compression pod and the attached vertical-air-duct, rotate through three hundred sixty degrees, as the means for directional guidance and direct thrust. Augmented power-thrust-tubes extend outward from the combustion pod to the mid-horizontal circumference of the aircraft.

Abstract: A control system for monitoring and controlling the operation of a mobile material distribution apparatus including at least one boom having a plurality of distribution nozzles or distribution ports located along its length for distributing material is disclosed. The control system monitors various sections of the booms and provides the user with a graphical representation of the operating states of the nozzles/distribution ports in each monitored boom section. By taking into account the actual operating states of each of the sections of the monitored booms, the disclosed control system provides more accurate mapping of the materials distributed by the controlled apparatus. In addition, the disclosed control system considers the operating states of any fence row nozzles disposed on the monitored booms in determining the amount of material to be supplied to the monitored booms to achieve a desired distribution rate.

Abstract: A passenger door control set simulates the electrical sequencing and control circuits that controls the operation of an aircraft's passenger doors, allowing the door to be opened and/or closed, and substitutes for the normal sequencing and control circuits that were removed from the aircraft during its conversion to a freighter configuration. The set contains a portable equipment box and a portable door switch box, and a set of adapter cables in a kit. The equipment box is connected by selected cables to the overhead equipment panel connectors and the door switch box is connected to the door bulkhead connectors for the selected aircraft door. Indicators are provided at each box to perceptibly indicate the correctness of the hook up and availability of electrical power.

Abstract: A monitoring system for detecting failures, or impending failures, in subsystems of a fly-by-wire primary flight control system of an aircraft. The system monitor a critical variable of at least two controllers acting in concert, in real time. Differences between the critical variables are calculated and, after filtering to remove insignificant variations, structural fatigue damage is estimated based on significant detected variations. Depending upon the relative severity of the estimated fatigue damage, the aircraft's primary flight control computer is programmed to shut down the malfunctioning subsystem, display a message indicating need for repair, or take other appropriate action.

Abstract: The present invention describes a process for a vehicle including an electronic control system, which processes input signals representative of the rotational behavior of the individual wheels, and wherein the differences of the tire tread circumferences of the individual wheels are determined by way of short-time and long-time correction factors. The long-time correction factors LZ.sub.n. are determined from the differences D.sub.R1 between the short-time correction factors KZ.sub.R1 and the long-time correction factors LZ.sub.R1 of the respective wheel by averaging LM.sub.r1 the differences during a predetermined time interval and by evaluating and weighting the average value. For the quick identification of an emergency wheel, every time the vehicle engine is started, the long-time factor LZ.sub.R1 is equalled once to the short-time factor KZ.sub.

Abstract: A system for circulating heated gases within the circular leading edge of a jet engine housing to prevent ice build-up thereon, or to remove accumulated ice thereform. Hot gases such as air from a hot, high pressure section of the jet-engine are directed through a conduit. The conduit enters the annular leading edge housing, usually from the aft side through a bulkhead, then turns about 90.degree. to a direction tangential to the leading edge annulus. The hot gases exiting the tube entrain the cooler air in the housing, causing a much larger mass of air to swirl circularly around the annular housing. The entering hot gasses heat the mass of air to an intermediate, but still relatively hot, temperature. This large mass of circularly moving hot air is quite efficient in uniformly transferring heat to the skin of the leading edge without leaving any relatively cold areas and preventing the formation of ice thereon.