Abstract: The Anti Hijacking Fail-safe System with Alert Locator Tracking Capabilities is a tamper-proof computer hardware/software system that could be installed in a commercial aircraft that, in case of an emergency, could be irreversibly engaged by the pilot, or by remote control, to take complete control of all necessary navigation and flight controls. It will then identify and select a predetermined, suitable airport. After this selection is made, the system will then vector the aircraft to the selected airport. After considering many factors, the system will engage an auto-land system. The auto-land system will take the aircraft to a safe landing, full stop, and shut down. The system could then be pre programmed with several other emergency functions, specific to the aircraft in which it is installed.

Abstract: SAFELANDER provides a method of safely operating aircraft, equipped with a Flight Control Unit, Instrument Landing System, and Autopilot, remotely on the ground and/or in congested airspace. The remote pilot, who can concurrently control a plurality of operational aircraft, communicates with Air Traffic Control and operates in a secure, synthetic vision, high fidelity, virtual reality cockpit simulator located in a ground-based facility. The patent saves cost and weight by providing a method for safely piloting traditionally dual piloted operational aircraft with just a single onboard pilot. The invention protects aircraft, edifices and the population from pilot error and/or terrorists. Decreases cost of air travel. Quickly, safely and effectively responds to emergencies. Increases flight safety and security. SAFELANDER ciphers and utilizes the two-way RF ground to aircraft and aircraft to ground telecommunication links and critical aircraft flight control data of U.S. Pat. No.

Abstract: A robot system, operable to perform a task, is integrated on a robot with a sensor, a control module, and a virtual world. The virtual world represents a generic continuum including a collection of information replicating the spatial and temporal properties of a number of articles and related circumstances in an environment of the robot system. As the virtual world provides a common space-time reference for all of the articles, including the robot system itself, the robot system may perform its task in an efficient and robust manner. For example, the robot may move about its environment without colliding with the other articles. Further, the virtual world may include predicted information about the articles, including an anticipated position or condition of the article at a particular time. In this way, the robot system may perform its task in a timely manner, since its operations can be synchronized with the other articles and an idle time may be reduced.

Abstract: An unmanned airborne reconnaissance system, the unmanned airborne reconnaissance system including a lightweight, portable, powered aircraft and a foldable launch rail, the aircraft, in a broken down condition and the launch rail in a broken down condition fitable inside a box, the box capable of being carried by one man. The launch system includes an elongated launch rail with the carriage assembly, and a propulsion means for accelerating the carriage assembly from one end of the launch rail to the other. The carriage assembly releasably engages the aircraft so as to propel the aircraft from one end of the launch rail to the other. The propulsion may be by a cartridge that explodes and releases a gas through a cylinder, or by elastic cords. The aircraft is guided through the air either by a programmed onboard computer which controls the control surfaces of the aircraft and/or by remote control. The aircraft typically contains a camera for recording and transmitting images received from the ground below.

Abstract: This invention, a Protected Primary Focal Node PFN is a Trusted Remote Activity Controller TRAC and mobile communication router platform that provides accountable remote and robotics control to transportation vehicles by interfacing with the vehicles E/E systems. It connects each vehicle either on the earth's surface or near the earth's surface with application specific intranets for air, sea and land travel, via either host commercial servers or agency providers through wireless communication gateways and then further interfaces these vehicles in a larger machine messaging matrix via wireless and IP protocols to further coordinate movement assess and manage equipment use and impact on the world resources, societies infrastructure and the environment. This filing focuses directly on PFN/TRAC System use to augment and upgrade public safety and security in the Airline Industry and restrict any unauthorized use of an aircraft.

Abstract: A method is disclosed for assuming and maintaining secure remote control of and aircraft in the event of an attack upon, or incapacity of the pilot of the aircraft.

Abstract: A flight recorder designed for small aircraft captures various onboard flight data in real-time and stores it in non-volatile memory. Recorded data includes aircraft's instantaneous position, altitude, attitude, engine RPM, G forces, flap position, cockpit voice and others. These data are obtained from various sensors which are integrated into the recorder. At the end of a flight the recorded data is downloaded into a computer using a wireless communications data transceiver also integrated into the recorder. It does not require removal or attaching any equipment to be able to download data. In addition to accident investigation, applications include training, preventive maintenance and asset monitoring.

Abstract: A method and apparatus for conducting proximity operations is disclosed. The method called inverser proximity operations includes maneuvering an active vehicle into general proximity to a target vehicle, transmitting from the target vehicle to the active vehicle data representing relative position and velocity between the target vehicle and the active vehicle, and maneuvering the active vehicle in accordance with the data to effect a desired proximity operation. Another method called distributed proximity operations includes maneuvering a carrier vehicle into general proximity to a target vehicle, releasing one or more active vehicles from the carrier vehicle, transmitting from the carrier vehicle to the active vehicle(s) data representing relative position and velocity between the target vehicle and the active vehicle, and maneuvering the active vehicle(s) in accordance with the data to effect a desired proximity operation.

Abstract: Differential Global Positioning System receivers (60) are located at the corners of a confined zone and receive signals from Global Positioning System satellites (62). The Differential Global Positioning System receivers (60) aid an aircraft (16) to fly and flight path or combing patten (20) over the confined zone. A vehicle (12) with a trailer (14) may be used to transport the aircraft (16) for use over the confined zone.

Abstract: A method and apparatus for providing an Aircraft Emergency Safety Control System (AESCS) capable of regaining control of an aircraft that may have been lost due to incapacitation of the crew includes an airborne segment, a ground segment, and a communications segment wherein control of the aircraft is removed from the control of unauthorized person(s) onboard the aircraft, and the aircraft is directed to a destination that is considered a safe location for the aircraft given it's status, and to facilitate a reasonably safe emergency landing.

Abstract: An airplane security system, particularly for a commercial airliner, includes an on-board device for allowing a person not on-board the airplane to override an on-board piloting system for the airplane. This on-board device is used together with an off-board device for allowing the person not on-board the airplane to contact the on-board device for overriding the on-board piloting system. The person off-board the airplane can then utilize a device for directing a flight path for the airplane that would differ from the flight path originally intended by those on-board and piloting the airplane, including providing for the safe landing of the airplane.

Abstract: A control system for a UAV includes control translations which maximize operational employment of the UAV payload. By determining spatial references, and then using the references to transform the control stick commands, the operator treats the UAV as a point source. For control through imagery from onboard mission sensors, the transformations provide for the UAV to move itself and achieve payload orientation.

Abstract: The invention is a system for ferrying at least one aircraft by a ferrying aircraft, the at least one aircraft and ferrying aircraft having vehicle management systems. In detail, the invention includes an attachment device for joining a wing tip of the at least one aircraft to one of the wing tips of the ferrying aircraft. A system is included for controlling the at least one aircraft and the ferrying aircraft such that the at least one aircraft flight characteristics are controlled by the ferrying aircraft.

Abstract: The invention concerns a remote-controlled flying machine, in particular for surveillance and inspection, capable of hovering and comprising a spherical open-worked resistant shroud integral with a cylindrical fairing wherein rotates a propeller powered by an engine housed in a fuselage secured to the fairing with radial arms and straightening vanes.

Abstract: A remote-control powered parafoil aircraft has an aircraft body (1) that is engine powered and hung with lines (2) from an air-expandable wing (3, 30). The lines include control lines (15) with which air flow and aerodynamic shape of the air-expandable wing are variable selectively from a foil controller (18, 19, 20) on the aircraft body for flight-mode control. Sight from a television camera (8) on the aircraft body is televised to a control unit (9) from which control data is transmitted selectively from proximate the control unit to the foil controller (14) with a multi-axis joystick or similar control, to an engine (6) on the parafoil body from an engine controller (24) and to an item servo (29) for control of optional items (45) on the aircraft body.

Abstract: A device for programming industry standard autopilots by unskilled pilots. The effect of the invention is such that when the invention is employed in a flying body comprising an industry standard autopilot with a digital flight control system, the invention provides for the safe operation of any aircraft by an unskilled pilot. The device additionally affords skilled pilots a more rapid and simplified means of programming autopilots while in flight thus reducing a skilled pilot's cockpit workload for all aircraft flight and directional steering, way points, and aircraft flight functions reducing the possibility of pilot error so as to effect safer flight operations of an aircraft by affording a skilled pilot to direct aircraft steering and function while under continuous autopilot control.

Abstract: A system and method for intervention control of an aircraft in the event of pilot command error whether voluntary or involuntary. Impending detection of a chaotic condition associated with a maneuvering aircraft enable early prediction and control of the aircraft where solutions based upon performance prediction are available. A further feature of the present intervention control of the aircraft enables an equipment malfunction detection signal substitution of a satisfactory equipment signal.

Abstract: A portable, re-usable, battery-powered, electronic device for storing, displaying and modifying air traffic control information. The electronic flight data strip receives input data from an external data source via infrared or radio transmission, stores the data in an on-board memory device, displays selected portions of the received data for viewing by an air traffic controller, and receives and displays inputs from the air traffic controller either directly through integral switches or via aforesaid communications channels. All input and output data messages and air traffic controller commands may be stored and time tagged for later retrieval. The contents of the stored memory can also be interrogated and modified by external data processing devices. Following completion of the flight, the contents of the internal memory can be interrogated for the purpose of archiving or investigation and/or cleared for subsequent re-use on another flight.

Abstract: A camera assembly 10 images a distant landscape and a downward landscape every a predetermined period of time. A position recognizing unit 30 of a moving object (autonomous running vehicle) detects the movement of the moving object on the basis of the movement between the imaged pictures of the distant and downward landscapes, which are imaged at different imaging times. That is, the movements of the distant-view and down-view images are converted to the moving amounts in the actual space on the basis of the distance images thereof, respectively, and the component of rotational speed based on the movement of the distant-view image is removed from the component of velocity based on the movement of the down-view image to derive a pure component of translation speed.

Abstract: A stabilization system is disclosed in which stabilization pitch and roll signals effective for stabilizing the aircraft are combined with respective pilot provided elevator and aileron position demand signals in accordance with a function which reduces the effects of the stabilizing signals in dependence on increasing values of the respective elevator and aileron position demand signals.

Abstract: A method and apparatus that allows a remote aircraft to be controlled by a remotely located pilot who is presented with a synthesized three-dimensional projected view representing the environment around the remote aircraft. According to one aspect of the invention, a remote aircraft transmits its three-dimensional position and orientation to a remote pilot station. The remote pilot station applies this information to a digital database containing a three dimensional description of the environment around the remote aircraft to present the remote pilot with a three dimensional projected view of this environment. The remote pilot reacts to this view and interacts with the pilot controls, whose signals are transmitted back to the remote aircraft. In addition, the system compensates for the communications delay between the remote aircraft and the remote pilot station by controlling the sensitivity of the pilot controls.

Abstract: The life of a target satellite is modified, i.e., extended or terminated by docking an extension spacecraft with the target satellite to form a docked satellite-spacecraft combination. The extension spacecraft is docked with and mechanically connected to the target satellite and includes guidance, navigation, and control systems for performing the rendezvous and docking maneuvers and for controlling the position of the docked spacecraft-satellite combination. The extension spacecraft also includes an onboard propellant supply for accomplishing the rendezvous and docking of the spacecraft with the satellite and for controlling the position of the docked spacecraft-satellite combination. A remote cockpit system is provided to permit human control of the extension spacecraft during proximity operations.

Abstract: The present invention is directed to an apparatus and method a flat-side model rocket. In the preferred embodiment, the model rocket is four-sided, and may be constructed by a user from wooden pieces that are pre-cut and pre-engraved with a sealed-CO.sub.2 laser. The model rocket of the present invention is compatible with existing model rocket engines, launching apparatuses, and parachute-type recovery apparatuses.

Abstract: A fuselage structure for use on a model helicopter includes a longitudinally extending keel defined by a vertical flat plate oriented to lie in parallel relation to a longitudinal axis of the model helicopter. A radio control system component is mounted to the vertical flat plate. The fuselage structure also includes a laterally extending floor perpendicular to the keel, a front bulkhead appended to the keel and a forward end of the floor, and a firewall appended to the keel and a rearward end of the floor. A landing gear assembly is coupled to the fuselage structure at a junction positioned to lie adjacent to a forward portion of a bottom edge of the keel.

Abstract: A primary or backup flight control system for controlling the flight path of an aircraft or spacecraft using wireless transmitters (15 and 16) located near the flight deck (14) and positioned within, or on, the outer skin of the fuselage (10). These transmitters (15 and 16) send pilot-generated, wireless, e.g. infra-red, flight control signals (17 and 18) to receivers (19 and 21) located within, or on, the engines, wings, and tail assembly surfaces. These signals (17 and 18) are then directed to their respective engines or moveable flight control surfaces. These wireless control signals (17 and 18) are transmitted externally of the fuselage structure (10) and the transmission and receipt of these signals takes place on a single aircraft or spacecraft structure. In case of fuselage damage, e.g., due to structural failure, internal explosions, air-to-air collision, or military combat, which damages the primary flight control system (hydraulic, wire or cable), the present system will remain operative.

Abstract: A radio controlled toy airplane has an airframe with a fixed vertical tail plane, a fixed horizontal tail plane, and at least one set of rightside and leftside propellers. The rotational outputs of the propellers are controlled discretely and continuously or in a staged manner, respectively, via a remotely located radio transmitter. This transmitter has two manual control sticks, one for controlling total combined power to the propellers and the other for adjusting the power distribution between the propellers, and in this way flight of the toy airplane is solely controlled by controlling motors which separately drive the propellers. The motors may be battery powered.

Abstract: A remotely-controlled aircraft comprises a sensor for sensing the actual rate-of-turn of the aircraft and for generating a rate-of-turn signal proportional thereto, which signal, inherently also proportional to the actual bank-angle of the aircraft, is applied to the aileron drive as a negative feedback signal with the bank-angle command signal to thereby stabilize the bank-angle of the aircraft. The aircraft includes a further sensor for sensing the actual rate-of-climb of the aircraft and for generating a rate-of-climb signal proportional thereto, which latter signal, inherently also proportional to the actual pitch-angle of the aircfaft, is applied to the elevator drive as a negative feedback signal with the pitch-angle command signal to thereby stabilize the pitch-angle of the aircraft.

Abstract: This invention provides a helicopter flight training device. The device comprises, in combination, a free-flying, radio-controlled, scale model of a helicopter and a flight station that is a substantially actual size simulation of a helicopter cockpit with its associated individual flight controls. The individual flight controls of the flight station incorporate means to convert their operation into a radio signal transmitted to the scale model helicopter to actuate the appropriate flight controls therein to control the flight thereof. In a preferred embodiment of this invention, the flight station consists of dual flight stations with dual flight controls to facilitate teaching student pilots. The device of this invention provides the utmost in safety to the student and instructor during the early, most hazardous, stages of flight training.

Abstract: A throttle governor/collective pitch control apparatus for radio controlled model helicopters for proportionally controlling either the model helicopter rotor speed or the rotor collective pitch, including sensing and timing means determining the rotor speed and any changes thereof, comparison means for comparing a subsequently sensed rotor speed with a first sensed rotor speed and developing an error signal, and control means responsive to the error signal to provide a control signal proportional to any changes in the rotor speed. In the throttle governor mode any variations in rotor speed result in a proportional control signal to vary the model helicopter throttle so as to maintain constant rotor speed. In the auto-collective mode changes in rotor speed result in a proportional control signal coupled to the collective pitch servo for proportionally varying the model helicopter collective pitch.

Abstract: An area navigation system capable of operating during an ILS approach to provide the pilot range and bearing with respect to the outer and middle markers for a front course approach, and with respect to the final approach fix and the end of the runway for a back course approach. The system operates by automatically connecting the # 2 NAV receiver to the RNAV during ILS operation while the ILS localizer converter is connected to the # 1 NAV receiver. At the same time the RNAV is disconnected from the left side indicator so this may be used for the localizer.

Abstract: Apparatus for use with an area navigation system wherein the craft is maintained on a predetermined vertical flight path. Specifically, a pitch command signal for controlling the vertical flight of the craft, which is substantially free of discontinuities, is produced by summing a signal indicative of the vertical displacement of the craft from the flight path with a damping signal representative of the vertical deviation rate of the craft from the vertical velocity required to maintain the craft on the flight path. Additionally, the vertical displacement signal is limited to a maximum amplitude to compensate for discontinuities therein, with respect to passage of the craft through the vicinity of a VOR/TAC station.

Abstract: Control apparatus for an aircraft area navigation system provides a vertical path control signal to cause the aircraft to ascend or descend along a helical surface as the craft executes a transition laterally from the inbound course to the outbound course of a waypoint whereby the craft attains the waypoint altitude when crossing the course bisector thereof while maintaining a predetermined vertical flight path angle when steered on a predetermined lateral course transition path.

Abstract: Control apparatus for an aircraft area navigation system computes a predetermined curved path from the inbound course to the outbound course of a waypoint or the inbound course to the next waypoint and provides aircraft steering signals with regard to the predetermined curved path. A bank angle bias command is applied to the apparatus for effecting transition from the inbound course to the curved path and is removed when the aircraft transitions from the curved path to the outbound course. Cross track and track angle error signals are generated with regard to the predetermined curved path for steering the aircraft thereon as the course transition is effected.

Abstract: For use with a microwave landing system of the type including a ground based station for generating a relatively wide aircraft navigational beam and airborne equipment for deriving precision azimuth, elevation, and range data therefrom, airborne equipment utilizing the data to guide the craft along a multi-segment path so that each of the segments is asymptotically captured by the craft.

Abstract: A vertical navigation steering control for aircraft for providing vertical steering of an aircraft along flight paths defined by waypoints which recognizes the problems introduced by lateral steering and accounts for shortening of horizontal distance between waypoints due to lateral path changes. Further features include means for capturing a NAV path, following a path between waypoints, transitioning from one path to another at a waypoint, and means for protection against excessive climb rates.