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| Number | Title | Issue Date |
| 4689748 | Device for aircraft and spacecraft for producing a digital terrain representation A device for use on aircraft or spacecraft provides data corresponding to the course and orientation of the craft, and a digital display of the terrain over which the craft is travelling. The device includes at least first, second and third sensor lines c... | 08/25/1987 |
| 4658359 | Method for managing redundant resources in a complex avionics communication system A digital computer based system for managing a plurality of redundant sig processing equipment in a complex avionics system provides fast reconfiguration of the signal processing equipment to add, delete, or modify signal processing functions. A single u... | 04/14/1987 |
| 4651282 | Microcomputer based keyboard command entry concept for VHF communication and navigation systems Airborne navigation and communication systems are disclosed including a VOR/LOC (VHR Omnirange/Localizer) receiver and a communication transceiver each with separate control and display panels. Each panel includes a ten push-button press keys numbered 0-9... | 03/17/1987 |
| 4649484 | Avionic control system An all-electric powered flight control system for an aircraft incorporating fault-tolerant avionics combined with a redundant power actuation control system utilizing electro-mechanical devices for actuating aerodynamic control surfaces; and wherein, the ... | 03/10/1987 |
| 4646255 | Gyro simulator An aircraft gyro simulator is operable in a dynamic mode to produce simulated pitch, roll and azimuth signals as a function of control wheel commands, flight control system commands, control surface status and the stored equations of flight for the aircra... | 02/24/1987 |
| 4645141 | Automatic flight control system There is disclosed a system and technique which enables an aircraft (helicopter or VTOL) to be more easily controlled for maintaining precise position or velocity in a hover condition. The system includes operational logic and decision making circuitry wh... | 02/24/1987 |
| 4641268 | Cruise airspeed control for aircraft A cruise speed control apparatus for aircraft wherein small differences between the target Mach command and the actual Mach number of the aircraft are used to displace the aircraft from its reference altitude to either increase or decrease actual Mach num... | 02/03/1987 |
| 4633404 | Automatic deceleration of aircraft during descent Deceleration control apparatus for an aircraft having an automatic altitude capture and hold system and an airspeed hold system, both systems controlled by controlling pitch attitude wherein during a descent from a higher altitude under airspeed-on-pitch ... | 12/30/1986 |
| 4622667 | Digital fail operational automatic flight control system utilizing redundant dissimilar data processing An automatic flight control system that is software fault tolerant fail operational in response to a first generic failure utilizes two independent subsystems each including a dual channel flight control computer. One channel in each flight control comput... | 11/11/1986 |
| 4617633 | Direct lift command blending The rapid and precise control of an aircraft flight path is obtained by a continuous blending of direct lift and conventional longitudinal control system commands by a unit that consists of a combination of a linear gradient and breakout element, a blendi... | 10/14/1986 |
| 4608531 | Test set for testing as a unit an amplifier system having several modules An Automatic Flight Control System for helicopter control includes an amplifier unit having several modules, some of which are in duplicate. The tester comprises plugs with test jacks for connection to an amplifier unit and to a normal flight director ind... | 08/26/1986 |
| 4590475 | Stall avoidance system for aircraft An aircraft stall avoidance system uses flight measurements such as accelerations, aircraft configuration, engine power, atmospheric conditions, and other related characteristics in computing the speed at which a specific aircraft is likely to stall in re... | 05/20/1986 |
| 4580210 | Control system having variably biased manipulatable unit In a control system having a manipulatable unit, such as an aircraft stick, which is biased toward a neutral position to provide control "feel", an input which at each instant signifies the position of displacement of the stick from its neutral position i... | 04/01/1986 |
| 4573125 | Flight control system especially for helicopters A flight control system including a mechanical control link (10) may have herent destabilizing characteristics. Such inherent characteristics may be caused by play in the mechanical control link of the system, by friction losses, by elasticity phenomena, ... | 02/25/1986 |
| 4569021 | Full flight regime autothrottle control system A Mach hold control circuit for an aircraft autothrottle system provides capture of a Mach number and control thereto while providing a low level of throttle activity also stabilizing the aircraft at maximum range cruise (MRC) Mach numbers and above. The ... | 02/04/1986 |
| 4551804 | Approach to hover control system for helicopters An approach to hover control system for a helicopter in which a constant deceleration is commanded at an initial approach speed and then the actual deceleration as a time function of the airspeed from the initial airspeed to a second airspeed is measured.... | 11/05/1985 |
| 4536843 | Total energy based flight control system An integrated aircraft longitudinal flight control system uses a generalized thrust and elevator command computation (38), which accepts flight path angle, longitudinal acceleration command signals, along with associated feedback signals, to form energy r... | 08/20/1985 |
| 4528628 | Shutdown monitor for a helicopter pitch bias actuator An improved PBA shutdown monitor circuit senses collective pitch control position rate of change magnitude and inhibits PBA shutdown in response to the continuous presence of sensed magnitude within a range of selected collective pitch rate magnitudes bou... | 07/09/1985 |
| 4500966 | Super contingency aircraft engine control A fuel control (23) for an aircraft engine (10) employs super contingency logic (76) in response to low rotor speed of a helicopter (130) engine failure (131) or entry into an avoid region of a flight regime following engine failure (133) to alter (161, 1... | 02/19/1985 |
| 4490793 | Cruise speed control for aircraft performance management system A cruise speed control apparatus in an aircraft performance management system wherein target Mach command is supplied to the engine automatic throttle controls to establish an engine thrust to overcome and equate to the aircraft nominal drag characteristi... | 12/25/1984 |
| 4488235 | Speed control system for aircraft Speed control apparatus for use in an aircraft performance management system of the type wherein a target Mach number command is supplied to the aircraft pitch controls to attain the target Mach and is simultaneously supplied to the aircraft throttles to ... | 12/11/1984 |
| 4467429 | Aircraft thrust control scheme for terrain following system This system permits speed variation within certain constraints. The minimum speed is derived from a stall avoidance or acceleration margin condition and the maximum speed may be the lower limit of the transonic region or other design limit. Assuming the t... | 08/21/1984 |
| 4454582 | Method and apparatus for continuously determining a chronodrasic interval A method and apparatus for determining the time remaining for maximum control action to be taken in order to achieve a desired objective (i.e., the chronodrasic interval) is disclosed. The method and apparatus continuously determines the amount of a param... | 06/12/1984 |
| 4443853 | Optical digital servo control system An electrically controlled (16) mechanical actuator (13) is driven by optically generated (23) electrical power through an optically controlled (28) switch (26) in an electrically isolated module (20). Optical transducers (54, 62, 70) and feedback (29), a... | 04/17/1984 |
| 4432060 | Earth center pointing phase locked horizon sensor electronic loop An electronic logic circuit utilized in conjunction with a scanning infrared detector to generate pulses which accurately indicate the precise location of the center of a preselected astronomical radiant body, such as the earth, notwithstanding a wide sca... | 02/14/1984 |
| 4419731 | Apparatus for estimating slant visibility in fog Apparatus for estimating the slant visibility in obscured atmospheres such as fog, whereby an indication is derived as to when, during an aircraft landing approach in such conditions, the aircrew are likely to be able to see the runway lights. The apparat... | 12/06/1983 |
| 4413316 | Data processing system for pre-planning the flight of an aircraft A data processing system for pre-planning the flight of an aircraft includes a plotting board arranged to supply position coordinates of selected points on a route to a processor. Other inputs to the processor provide details of known aircraft parameters ... | 11/01/1983 |
| 4409658 | Apparatus for landing loads from transport aircraft, especially low flying aircraft A landing gear for loads including cargoes and/or personnel is removably ured to the load. At least one tiltable jet engine forms part of the landing gear and automatically controls the descent movement. A stabilizing mechanism forms part of the landing ... | 10/11/1983 |
| 4398242 | Electronic controller A pair of input sense signals are processed and passed to inputs of two servo amplifiers. The amplifier outputs are summed and converted to a corresponding hydraulic pressure in a T-valve. Transducers monitor the produced pressure and provide feedback sig... | 08/09/1983 |
| 4382281 | Helicopter force feel actuator automatic static null compensation A bias voltage, which can be added to force commands applied to a helicopter control stick actuator, to compensate for static null offset errors, is generated as the average of the summation or integral of actuator pressure, or pressure differential, sens... | 05/03/1983 |
| 4376979 | Updated lock-positioning of foldable helicopter blades The foldable rotor blades (12) of a helicopter are automatically adjusted to pitch angles where they can be locked as a prerequisite to folding, by commands generated (98, 112) to cause trim actuators (39-41) to drive swash plate servos (17-19) to the cor... | 03/15/1983 |
| 4373184 | Vertical flight path steering system for aircraft Disclosed is a vertical flight path angle steering system for aircraft, utilizing a digital flight control computer which processes pilot control inputs and aircraft response parameters into suitable elevator commands and control information for display t... | 02/08/1983 |
| 4363098 | Electric command spoiler system An aircraft spoiler control system wherein each of a plurality of spoilers is driven by an electrically responsive actuator. Sense signals representative of the aircraft's control wheel rotation, speedbrake lever deflection, flap position and air/ground s... | 12/07/1982 |
| 4355358 | Adaptive aircraft actuator fault detection The operation of an actuator (16) is monitored by comparing its position (21) with the position (31, 136) indicated by a model which integrates (45, 135) a limited amount of the difference between the position command (24) applied to the actuator and the ... | 10/19/1982 |
| 4354234 | Automatic lock-positioning of foldable helicopter blades The foldable rotor blades (12) of a helicopter are automatically adjusted to pitch angles where they can be locked as a prerequisite to folding by commands generated (98, 112) to cause trim actuators (39-41) to drive swash plate servos (17-19) to the corr... | 10/12/1982 |
| 4354245 | Cyclic or periodic analog signal processing circuit This circuit makes it possible to produce in digital form position data corresponding to analog signals supplied by linvar transducers for processing by a digital computer. It comprises a multiplexer for successively transmitting the linvar signals to a p... | 10/12/1982 |
| 4313165 | Force feel actuator with limited proportional/integral error feedback A system which provides feel-force to the control stick of an aircraft by means of hydraulic pressure is provided with non-nulling, proportional, direct feedback loop, and a limited integral feedback loop in the drive of the pressure control servo valve t... | 01/26/1982 |
| 4312041 | Flight performance data computer system A flight performance data system comprises a control and display unit operably connected to a computer. The computer has input means responsive to real air mass parameters and real aircraft dynamic measurements. The computer is programmed to respond to th... | 01/19/1982 |
| 4303212 | Vertical seeking aircrew escape system An aircraft ejection seat which seeks the upward vertical direction to ene safe ejection from inverted aircraft at low altitude. An attitude control processor processes signals from three-axis attitude sensors and controls servo valves which regulate the... | 12/01/1981 |
| 4249159 | Aircraft docking system An aircraft ground guidance and parking system consisting of a lighting display unit adapted to be mounted at a parking station pointing directly down the on-course center line to be followed by the incoming taxying aircraft and at an elevation for viewin... | 02/03/1981 |
