Abstract: A control device for use in unmanned model aircraft for a constant speed propeller is disclosed. The device comprises a propulsion engine coupled to the propeller. The rotational speed of the propulsion engine is regulated through an automatic change of the angle of attack of the propeller and a manual or automatic adjustment of the throttle. It also comprises an electric servomotor device, a power transmission and a controller. The servomotor device is positively coupled to the propeller via the power transmission. The controller controls the servomotor device. The variable angle of attack of the propeller is adjusted by the power transmission from the servomotor device and the propulsion engine, manually by an operator or automatically by the controller.

Abstract: An unmanned flying vehicle comprises an autonomous flying wing having at least two wing portions arranged substantially symmetrically about a center portion. Each wing portion is pivotally attached to each adjoining portion such that the wing portions are foldable for storage and openable for deployment. A preferred form is the so-called seagull wing having four wing portions. The vehicles may be programmable from a mother aircraft whilst being borne to a deployment zone using a data link which may be wireless.

Abstract: A power and communications connection arrangement for a miniature, unmanned aircraft having data handling capability. The aircraft has a microprocessor for managing flight control, a GPS receiver, a communications radio frequency transceiver, and data handling apparatus. The latter may be any of a sensor for gathering environmental data, sensing aircraft altitude or attitude, a data relay station, or any combination of these. The data handling apparatus is part of a removable module mounted to and detachable from the aircraft. The connection arrangement includes stationary power and communications terminals fixed to the module, and corresponding free power and data cables completing respective power circuits and communications links within the aircraft. In the preferred embodiment, the microprocessor, at least one sensor, and a battery pack are located in the module, and a radio transceiver, a GPS receiver, controls such as rudder and elevator, and other sensors are located in the airframe.

Abstract: An emergency control system permits an aircraft to recover from a catastrophic loss of cabin pressure even if the pilot becomes incapacitated before he is able to activate an emergency oxygen system. An autopilot system is programmed for rapid descent, in response to a cabin depressurization condition detected by an air pressure sensor, to a flight level where there is sufficient oxygen in the atmosphere to sustain full consciousness. When in the rapid descent mode, the autopilot cuts engine power to idle, reduces the angle of attack, maximizes parasitic drag, and initiates a maximum descent rate without exceeding the aircraft's design limitations. As the aircraft approaches a lower altitude capable of sustaining full human consciousness, the autopilot system increases the angle of attack, reduces parasitic drag, and increases engine power, thereby causing the aircraft to fly level at the lower altitude until the pilot reasserts control of the aircraft.

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 reusable first stage (100) includes a booster engine system (102) for providing thrust during launch, a structural assembly (108), canards (118), jet engines (122), wings (124), elevons (126) and retractable landing gear (130). After separation, the jet engines (122) and aerodynamic control surfaces are used to return the first stage to a landing strip. The booster system (102) includes a structurally stable outer skin system such as an isogrid structure. The first stage (100) is thereby adapted for controlled descent and recovery with minimal structural enhancement or added mass.

Abstract: A robotic or remotely controlled flying platform (10) with reduced drag stabilizing control apparatus constructed having an air duct (12) with an air intake (14) on the top and an exhaust (16) at the bottom, containing supported therein a clockwise rotating fan (22) and a counter-clockwise rotating fan (24). Directly below the perimeter of the air duct exhaust are mounted a plurality of trough shaped air deflection assemblies (32) each including a rotatably adjustable half trough (44) for selectively scooping a portion of the drive air, and a stationary adjacent half trough (36) for receiving the scooped drive air and redirecting it outward and upward from the air duct.

Abstract: A redio control device suitable for model aircraft is provided that can quickly correct the rudder following the operation of a stick lever even during a delay operation, so that the manipulated body can be stably controlled according to the operator's direction. The trim switch 8 that can vary the servo output of the servo device for each channel to the neutral position of each of the levers 7A and 7B of the stick unit 7 is provided to the transmitter 2. The arithmetic process means 4 stores plural types of characteristic data representing the servo output to the operation amount of each of the levers 7A and 7B changeable by the changeover switch 8. When the lever 7A (or 7B) is not operated over a set value and when the changeover switch 9 selects the characteristic data corresponding to the operational status of the manipulated body 1, the arithmetic process means 4 delays the operation by the offset of the mixing amount due to the trim switch 8.

Abstract: An airborne remote piloted vehicle does not require onboard fuel to greatly extend its endurance and payload capability. Photovoltaic cells are provided on substantially the entire bottom surface of the RPV to receive high intensity radiation beamed up from a ground station. The photovoltaic cells can be made responsive to visible light, infrared light and/or ultraviolet light emitted from lasers that direct narrow, high energy beams, or other directable narrow beams of other wavelengths of high energy radiation, including but not limited to microwaves. The cells convert the beamed up radiation to power at least one electrical motor driven propeller and instrumentation for onboard components including sensors, lasers, radio transmitters, and associated instrumentations. Control signals may also be beamed up or otherwise transmitted to the vehicle to control its transport to and hovering at an on-station location and to activate the onboard components for reconnaissance, monitoring, and relaying data.

Abstract: Apparatus for estimating a first height (1) of a vehicle (2) above a first reference surface (3), including a system (4) for determining position, velocity and attitude incorporating at least one sensing means (4b) operable to provide an output signal (5) indicative of a vertical specific force of the vehicle, error-estimating means (6) for receiving as input signals a horizontal reference velocity and position (4a) of the vehicle (2), and a radar altimeter measurement (7) of a second height (1b) of the vehicle (2) above a second reference surface (8) and for providing as an output signal (9) estimates of errors associated with the sensing means output signal (5), and integrating means (10) for receiving said sensing means and error-estimating means output signals (5, 9), and for subtracting the estimates of errors from the signal (5) indicative of vertical specific force while performing a double integration of the results of the subtraction, to provide an output indicative of the required estimated first he

Abstract: A process for real-time reconfiguring of trajectories or airborne vehicles in order to adapt a mission to suit a new situation that has arisen through the occurrence of a disrupting event. The process updates real-time context data modified by the occurrence of the disrupting event and analyzes the new real-time context thus obtained in order to select a predefined reconfiguration method chosen from a set of different predefined methods stored in memory, each of these methods directly translating operational strategies customarily employed by aircrew in a given real-time context so as to determine a new trajectory which best suits the current real-time context.

Abstract: Trimming process for adapting a first control loop of a controllable, automatically controlled reference system, which is or represents an aircraft, to a second control loop which simulates the reference system, Flying condition values including controlled variables, which are returned in each control loop for the purpose of the control, are detected, and both control loops are acted upon by the same desired input data. In the first process loop, a conversion of the unreturned flying condition values of the airplane model takes place to the values of the corresponding flying condition values of the reference system. The second process loop is provided for the adaptation of the returned condition values of the airplane simulation system to the corresponding condition values of the reference system.

Abstract: A gyroscope suitable for a remote-controlled helicopter is provided that can improve the control characteristics to a disturbance factor such as wind as well as the response characteristics under yaw-axis control in a correct pitch operation. The angular velocity detection signal from the yaw-axis angular velocity sensor 10 is added to the yaw-axis control signal and the angular velocity reference value from the controlling gear. The PID controller 2 receives the resultant addition signal. The control signal from the PID controller 2 is added to the correct pitch control signal and the yaw-axis control signal sent via the correct pitch to yaw-axis control mixing unit 3. The actuator 6 receives the resultant addition signal and controls the yaw-axis driving unit 7. The yaw-axis angular velocity detection sensor 10 detects the angular velocity around the yaw-axis of the airframe 9.

Abstract: A global communications network comprises a plurality of aerial platforms or vehicles deployed at an altitude in or near the stratosphere and permitted to drift in a controlled manner such that each platform adjusts its position relative to other aerial platforms. Each aerial platform has a propulsion system and control surfaces and preferably includes a lighter-than-air component to maintain lift in an economical manner. Each aerial platform also includes a payload, means for communicating with other aerial platforms and a control system including location-finding equipment and a processor adapted for directing the platform's propulsion system and control surfaces to effectuate changes in the aerial platform's position relative to other aerial platforms based on position information, and optionally on other factors such as terrestrial demand for services provided by the payload of the aerial platforms.

Abstract: A shoulder launched unmanned reconnaissance system for providing overhead visual surveillance of remote targets is disclosed. The present system includes a reconnaissance air vehicle which may be fired from a portable launcher, accelerated to flight speed, and remotely controlled using a ground control system. The vehicle is flown to the target area to enable an onboard wide angle video system to transmit video images of the target by radio or fiber optics link to the ground control system for processing and display. The ground control system enables the reconnaissance vehicle to be flown to a recovery area and to descend in a stall mode after the flight is completed for maintenance prior to reuse. The air vehicle includes collapsible wings which are deployable after launch by a spring actuated mechanism. The fuselage of the air vehicle carries an onboard video camera, an electric motor, a battery, a global positioning system receiver, flight controls, and a data link system.

Abstract: A system for framing a canopy has a carrier sheet and a coating of adhesive deposited onto the carrier sheet. A transparent film is cast over the coating of adhesive, and the film defines a plurality of slits configured for forming frames or masks which conform to the shape of the canopy. Alternatively, in a method for framing a canopy having interior and exterior sides, a first coat of paint having a first color is applied onto a first side of a transparent film, and a second coat of paint having a second color is applied onto the first coat of paint. A second side of the film is then adhered to the exterior side of the canopy so that the first coat of paint is visible on the interior side of the canopy, and the second coat of paint is visible on the exterior side of the canopy.

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: Apparatus and method for remote rotational control of various equipment control members and surfaces by means of a coaxially disposed flexible shaft, such as a torsion-cable, and housing or tube combination. One particular application of the invention is the remote, servo-activated rotational control of throttles for radio-controlled aircraft. In radio-controlled aircraft applications, rotational activation of the servo output shaft causes the relatively smaller twist or torsion cable, and therefore the throttle plate, to rotate and thereby to adjust the flow of fuel and air mixture through the carburetor and into the engine.

Abstract: A smoke generator for radio controlled aircraft having an internal combustion engine. The smoke generator includes a bracket for attachment to the radio controlled aircraft and a cradle releasably secured to the bracket. A container, a valve assembly, and a servo are all carried by the cradle. The container holds a pressurized, smoke-generating liquid and is placed in fluid communication with the internal combustion engine by a conduit. The valve assembly regulates the flow of pressurized, smoke-generating liquid from the container into the conduit. The servo has a motor-driven crank for operating the valve assembly in response to radio signals received from a remote transmitter.

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: An control mechanism apparatus is shown which electromechanically actuates a control board of a radio transmitter. The radio transmitter transmits radio signals to a receiver on board a model aircraft for actuating the various parts thereof. The apparatus comprises a base frame for providing a stable platform with a seat mounted at the rear of the base frame. A plurality of controls emulating the controls found in a cockpit of an actual aircraft are mounted to the base frame. A plurality of mechanical linkages are provided which transmit the position of each of the plurality of controls to a corresponding plurality of electrical devices. Each of the corresponding electrical devices is in electrical communication with the control board and the output of each of the electrical devices varies in accordance with the position of the controls. The radio signals are transmitted by the radio transmitter control board and vary in accordance with the electrical output of each of the electrical devices.

Abstract: Apparatus and method for performing satellite proximity operations such as inspection recovery and life extension of a target satellite through operation of a "Satellite Inspection Recovery and Extension" (SIRE) spacecraft which can be operated in the following modes (teleoperated, automatic, and autonomous). The SIRE concept further consists of those methods and techniques used to perform certain (on-orbit) operations including, but not limited to, the inspection, servicing, recovery, and lifetime extension of satellites, spacecraft, space systems, space platforms, and other vehicles and objects in space, collectively defined as "target satellites." The three basic types of SIRE proximity missions are defined as "Lifetime Extension", "Recovery", and "Utility." A remote cockpit system is provide to permit human control of the SIRE spacecraft during proximity operations.

Abstract: A learning autopilot for a vehicle provides the capability to command complex maneuvers or maneuver the vehicle when control by its ground station is not possible. A memory is used during a piloted rehearsal mission and position and time information for the aircraft is stored in the memory. This memory is incorporated into the vehicle control system, and during automatic operation of the aircraft, the recorded position and relative time information is retrieved and compared against position and relative time information occurring during automatic flight. The difference between the recorded information and the actual flight information is used to generate error signals which are converted to command signals for the vehicle. Maneuvers which were initiated and completed by the pilot during the rehearsal mission are then repeated during the automatic flight from the flight information stored in the memory.

Abstract: An unmanned aerial vehicle that includes symmetrical wings, tail section and internal compartments. The wings which include the only control surfaces can be attached to either side of the aircraft. An engine and a payload are non-symmetrically attached modules. Assembly and disassembly is performed with quick release pin and plate latches, quarter turn fasteners and guides that prevent improper assembly. The compartments include quick release hatch covers for the various internal craft compartments.

Abstract: A vertical performance limit compensator is provided for a rotary wing aircraft. The compensator modifies a vertical velocity command signal for the aircraft's autopilot. The vertical velocity command signal represents a desired vertical velocity for the aircraft, and results in an associated engine power demand. Existing engine power remaining beyond that required for level flight is excess engine power. An engine performance signal is provided as an indication of an engine power demand that exceeds the excess engine power. A compensated vertical velocity command signal having a magnitude lower than the vertical velocity command signal is provided in response to the vertical velocity command signal and the presence of the engine performance signal.

Abstract: The disclosure relates to the deployment and maintenance of a belt of autonomous sensors fitted out with warning sensors to monitor the area surrounding one or more sensitive points. It relates especially to anti-missile and anti-aircraft warning systems for naval surface ships against missiles and aircraft flying at low and very low altitudes. It consists in controlling the paths of the drones solely by means of their radius of curvature for which they receive an instructed value from the reference point or points. This instructed value is encoded by a frequency of a radioelectric signal sensitive to the Doppler effect. A modification of this instructed value of radius of curvature as a function of the signal of a proximity sensor makes it possible to avoid all problems of collision and to keep the drones at equal distance from one another. This mode of control proves to be particularly efficient and, at the same time, very simple.

Abstract: An automatic landing system for guiding an unmanned aerial vehicle along a predetermined path to a predetermined point on the ground. The system includes an image processing means resident in the motion compensation processor that computes aerial vehicle parameters. The computed parameters are altitude, changes in altitude, changes in pitch and yaw angles, roll angle and changes thereto, and changes in cross range and down range position. These computations are based on the movement of elements in the video of an imaging sensor onboard the aerial vehicle. The motion compensation processor also measures the distance (in pixels or picture elements) between two beacons placed a known distance apart on either side of the apparent touchdown point. A recovery control processor uses these parameters to compute both desired and actual altitude as a function of range from the vehicle to the apparent point of touchdown and to provide offset error in azimuth from the desired flight path to the landing area.

Abstract: Apparatus and method for controlling an unmanned generally aerodynamically symmetric aircraft includes detecting the presence of misalignment between the horizontal component of the center of gravity vector and the horizontal component of the direction of flight vector and further includes rotating the aircraft to align the horizontal components of the vectors.

Abstract: In a method and apparatus for remotely controlling a formation of drones. A single drone is chosen as a formation leader. Each other drone in the formation has one other drone in the formation as its leader. A follower drone will sense relative movement parameters as well as inquire of its leader drone as to its other movement parameters. The follower drone will then control itself to follow the movements of its leader.

Abstract: The present invention relates to an automatic detector for a control device for controlling the flying state of a remote-control toy airplane, which can provide automatic correction to maintain the remote-control toy airplane in a flying state in a level or horizontal manner. The detector is a digital or analogic device located at a proper position within the housing of the airplane. The detector includes a device locating plate, fixing racks, a suspension cord, a movable light-obstructing sheet or a movable light-permeable sheet, light emitting element, and one or more detecting elements the light-obstruction sheet is swingingly mounted on the suspension that in turn is connected to the cord fixing racks. When light emitting element emits light and the airplane maintains a horizontal or level attitude, the effect of gravity on light-obstruction sheet will cause it to obstruct light.

Abstract: An unmanned, remotely controlled microwave-powered aircraft for use as a stationary communications platform. The aircraft is generally a flying wing with a large, flat inner wing having a rectenna on the underside. Rectennas may also be provided on the underside of the wings, the combined output from the rectenna being used to provide power to two electric motors housed within torpedo-shaped nacelles which drive two rear propellers. The rectenna converts a microwave signal at 35 GHz generated by a ground power station utilizing dual gyrotrons and a 34-meter diameter antenna dish. The aircraft has a preferred airfoil cross section throughout and is constructed of lightweight but strong materials in order to provide an enhanced flying time of several months. A power management and distribution system manages the DC power produced by the rectenna to supply power to the flight controls, propulsion system and payload.

Abstract: The present invention relates to a device for a motorized aircraft, said device having a room for containing an inspection apparatus, said device comprising at least two elements, a first element absorbing essentially vibrations with a frequency higher than a specific frequency, while the second element absorbs essentially vibrations with a frequency lower then said specific frequency, said first and second elements being linked together and placed the one with respect to the other, so that the .second element is adjacent to the said room. The invention relates also to an aircraft, such as a helicopter, with a camera placed in such a device.

Abstract: A servo-wheel for use in a control system for model craft having a servo-motor and movable control members. The servo-wheel is a rigid disc having opposed planar surfaces. A hub is at the geometric center of the disc and includes a bore extending through the disc. A raised portion protrudes from one of the planar surfaces and forms a first part of the hub. The raised portion also defines a first part of the bore having an inner circumferential surface of a first diameter. A keyed receiver is formed in the inner circumferential surface of the raised portion. An insert is mounted in the disc to form a second part of the hub. The insert defines a second portion of the bore and has an inner circumferential surface of a second diameter, less than the first diameter. A keyed driver is received by the keyed receiver. The keyed driver is rotatably connected to the servo-motor at one end and attached to the servo-wheel hub at the other end, so that the servo-wheel is rotated by the servo-motor.

Abstract: Devices and means to conduct indoor model aircraft flight, in an indoor/enclosed space using radio controlled model aircrafts. The aircraft is controlled by available multi channel radio control transmitter/receiver set and available micro size servo motors for control of aircraft surfaces and electric motor. The indoor/enclosed space is lighted, provide with upward air flow, marked by laser light beams and separated from public by transparent barrier to provide a controlled space for engaging in flight of model aircrafts.

Abstract: Kinematic data is generated onboard an aircraft for describing its state of motion as it flies over a tracking range. The kinematic data is transmitted to a plurality of remote stations on the tracking range and tracking data is generated which represents the actual state vector of the flying aircraft. Also generated is pseudo tracking data, identical to the tracking data but delayed in time, for representing the motion and trajectory of a pseudo aircraft. Utilizing the pseudo tracking data an image of the flying aircraft is generated from the viewpoint of the cockpit of the pseudo aircraft. A person may then view the image to observe the dynamics of the flying aircraft as if the person were chasing the actual aircraft in the pseudo aircraft. The method permits sophisticated maneuvers in the remote piloting of aircraft as well as flight performance analysis.

Abstract: The disclosed invention is a generic Drone Control System or alternatively method to remotely pilot an air vehicle. The present invention essentially comprises a converted aircraft or other air vehicle and a ground station from where the drone is remotely controlled. Also disclosed as part of the Drone Control System are a plurality of means to transfer information and data between the ground station and the drone.

Abstract: A radio controlled hot air balloon, particularly suitable for use by hobbyists, includes a balloon envelope, a burner assembly and a radio control system. The altitude of the balloon is remotely controlled by adjusting the amount of hot air produced by the burner assembly.

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: The invention relates to a control system for a remote controlled aircraft. This system comprises on one hand, an substructure on the ground provided with computing means, data acquisition means and radio transmission means, and on the other hand, an on-board apparatus provided with analogous means and sensors for the parameters of the behavior of the aircraft. The substructure on the ground and the on-board apparatus are adapted to exchange data in order to assure the stabilization and the piloting of the aircraft, and the provide specific orders as a function of the application.

Abstract: A servo control system for a radio controlled co-axial rotor helicopter includes a receiver 4 to provide signals indicative of operator desired pitch, yaw, roll, and collective commands to an electronic mixer unit 30 which translates these command signals into six control signals 34-42 utilized by servos 50-60 to properly displace the rotor blades 256, 258.

Abstract: A terrain surveillance, powered aircraft is disclosed to have an on-board video camera that is not gimballed relative to the aircraft, the aircraft typically comprising multiple components; the method of the invention including: assembling the components into aircraft configuration at or near a launch site; launching the aircraft at that site with no human pilot on board same; remotely controlling the flight path of the aircraft by radio or cable link, to fly to a location for terrain surveillance; operating the on-board video camera to survey the terrain while varying yaw of the aircraft to provide sweep viewing of the terrain; and recovering the aircraft by controlling its flight to steeply descend to a landing zone.

Abstract: A remote controlled helicoper having a video radio frequency link to a fixed control location has a video camera with a field of view including the terrain forward of the helicopter, an airspeed display, a relative wind direction indicator, and a pitch indicator. A video monitor at the fixed location displays received video signals of the terrain, airspeed, relative wind direction and pitch permitting control of the helicopter over a radio link from the fixed location to the helicopter. The system provides training, experience, and practice in operation of the helicopter.

Abstract: A sacrificial seagoing vessel comprises an automatic navigation system which is operable remotely to maintain the sacrificial vessel in a predetermined orientation and position with respect to a predetermined conventional vessel which is to be safeguarded from enemy projectiles, the sacrificial vessel being attractive to projectiles. The attraction may be provided by enhanced radar signature or by emission of signals at a substantially greater level occurring from a conventional seagoing vessel.

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: A transmitter for use in an aircraft navigation system, the transmitter comprising a body portion (35) having an end (36, 37) adapted for implanting into the ground and an opposite end fitted with an antenna (38,39), and stabilizing means (41) arranged to be rendered operative on impact of the transmitter with the ground.

Abstract: A navigation system for an aircraft fitted with an autopilot, the system comprising at least one ground-based transmitter (2), receiver means (7,8) mounted in the aircraft and including two antenna (5,6) oriented such that their polar diagrams overlap and are inclined with respect to the fore-and-aft axis of the aircraft.

Abstract: A reduced-scale racing apparatus having at least one self-powered, remotely controlled vehicle, and at least one operator's booth containing a control console for operating the vehicle, the vehicle having a wheeled body provided with a first control for controlling the vehicle, a forwardly trained video camera on the body, a rearwardly trained video camera on the body, a transmitter on the body for the wireless transmission of respective signals from the forwardly and rearwardly trained video cameras, and a receiver on the body responsive to wireless signals for operating the first control, while the operator's booth has a housing for containing a driver/operator and the control console, with a second control in the housing for generating wireless signals receivable by the receiver for operating the first control, the housing being further provided with a first video display screen responsive to the transmitted signals from the forwardly trained video camera for displaying the path in front of the vehicle, an

Abstract: A remote-controlled autogyro visually and functionally simulates a helicopter with stub wings (e.g. the Hind D), so that an expendable helicopter-simulating target is produced. The target has a fixed angle rotor shaft, the rotor being solely aerodynamically controlled. The rotor blades have a negative pitch angle, and a positive conning angle. The engine is mounted at the front of the fuselage and has a downthrust angle, and the horizontal stabilizer also slopes downwardly aft. The rotor is at about the center of lift (horizontally) of the wings, and the wing span is about 50-60 percent the length of the fuselage. The ailerons and tail rudder are electrically interconnected. Remote control is provided for the elevators ailerons, and engine speed.

Abstract: Pulse position coding is used to transmit several channels of data from a ground radar transmitter to a receiver in an airborne, remotely-piloted vehicle. The system is designed to ignore interfering pulses, especially those which are synchronized with the transmitter's PRF, by combining a number of noise reduction devices. These include the redundant transmission of address and channel information, the transmission of true and complemented data, the tracking of channels transmitted in a predetermined order, developing an interference count to recognize synchronous pulses, comparing data received for a given channel with data subsequently received for that channel, the use of windows around the expected positions of pulses, and the use of parity. There is also a novel programming arrangement which enables several programs to be stored in a reduced amount of memory space.