| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 41 | ELECTRONIC FLIGHT INSTRUMENT DISPLAYS | PCT/US0008766 | 2000-03-31 | WO0065423A2 | 2000-11-02 | PRICE RICARDO A |
| The present invention is directed to novel primary flight displays (3), moving map displays (8, 9) and engine parameter displays (15, 16, 17) for aircraft cockpits. These displays process data gathered from various aircraft sensors and, using various electronic databases, generate intuitive symbols (27) that aid the pilot. The present invention also uses various novel algorithms that use data gathered from inexpensive sensors to derive parameters normally requiring far more expensive sensors. | ||||||
| 42 | Aircraft flight instrument displays | US412874 | 1995-03-29 | US5614897A | 1997-03-25 | Simon J. Durnford |
| An aircraft flight instrument display panel (10) has a combined speed and heading indicator in the form of a central square (11) surrounded by a scaled matrix (12). Displacement of an aircraft (100), in which the display is installed, from a desired speed and heading being indicated by displacement of an aircraft symbol (14) in the y and x directions from the central square. The aircraft (100) has an attitude sensor system (102) and the flight instrument display (108) has a flight instrument control system (104), the attitude sensor system and the flight instrument control system having an interconnection (106) with control laws such that, when the aircraft (100) is displaced from its desired speed and heading, pilot adjustment of pitch and roll, respectively, in a manner tending to return the aircraft (100) to the desired speed and heading, causes the aircraft symbol (14) to move towards the central symmetrical square (11). | ||||||
| 43 | Aircraft flight instrument display system | US239422 | 1981-03-02 | US4415879A | 1983-11-15 | Robert H. Brady; Michael L. Beaumont; Arthur C. Pettis |
| A combination directional gyro and navigation radio indicator instrument for use in aircraft which provides a display of compass card, selected course pointer, course deviation indicator, to-from indicator, and glide slope indicator in a unique presentation. The compass card is directly driven by the directional gyro, and the selected course pointer normally rotates with the compass card when it rotates, but can be de-clutched for selection of a new course. The selected course signal is obtained by attenuating, amplifying, and phase shifting the reference signal from a navigation radio such that it can be sent to the rotor of a control transformer which is geared to the compass card. The resulting stator signal is then amplified and sent to the rotor of a differential resolver which is geared to the course selector pointer. The control transformer and the differential transformer rotors turn in opposite directions such that the reference signal does not change when the compass card and the course selector pointer move together, but does change when the course selector is de-clutched and moves independently of the compass card. The resulting signal from the stator of the differential transformer is therefore an electrical representation of the selected course. This signal is then sent back to the navigation radio where it is compared to the signal representing the actual course of the aircraft that is received from a stationary navigation radio transmitter (VORTAC). | ||||||
| 44 | Aircraft flight instrument display system | US788702 | 1977-04-19 | US4149148A | 1979-04-10 | Harry Miller; Parm L. Narveson; William R. Hancock; Joseph P. Hsu |
| Apparatus for providing an integrated display of flight instrument parameters on the screen of a single cathode ray tube is presented. The synthetically generated symbology is equivalent to that typically provided by ten conventional electromechanical instruments including an attitude-director indicator, horizontal situation indicator, pressure altimeter, radio altimeter, vertical speed indicator, radio magnetic indicator, Mach airspeed indicator, autopilot-flight director mode annunciator, load factor indicator and true air-speed indicator. | ||||||
| 45 | Composite aircraft flight instrument | US67411346 | 1946-06-03 | US2538843A | 1951-01-23 | ROY MCGUIRE J |
| 46 | KATAPULT ZUM ABSCHIESSEN EINES FLUGGERÄTS | EP09753514.0 | 2009-04-23 | EP2282939B1 | 2011-12-07 | TENBERGEN, Martin; KRÜGER, Bernhard |
| A catapult for launching an aircraft comprises a carriage (14) for supporting the aircraft, said carriage being movable on a guide rail (2), and at least one cable (10), which can be tensioned and is configured to be elastic at least in sections (12) and by which the carriage can be moved from a start position into a launch position while relaxing the cable. The cable is guided parallel to the guide rail via at least one deflection roller (26). | ||||||
| 47 | LOW COST FLIGHT INSTRUMENTATION SYSTEM | PCT/US2006/009176 | 2006-03-15 | WO2006099436A1 | 2006-09-21 | SHAW, Robert, L. |
A device for providing flight condition information and a method of displaying such information. In one form, the device functions as a backup system to provide flight condition information in the event of partial or complete inoperability of a primary flight instrument system, or to complement such primary flight instrument system. Numerous sensors collect flight data, which can pass through devices to convert and manipulate the data to produce flight condition information that can be displayed in such a way as to reduce a pilot's cognitive workload. The information displayed includes at least flight path angle, lateral acceleration, and turn rate. Additional information that may be displayed includes heading information, as well as information relating to airspeed and altitude, among others. In another form, the device can be part of either a primary or backup system. |
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| 48 | Flight instrument flag annunciator | US126311 | 1987-11-30 | US4821669A | 1989-04-18 | Joe T. Hoffman |
| A flight instrument flag annunciator has a motor, a flag mechanism having a flag shutter driven by the motor, a tension spring for rotating the flag shutter in a counterclockwise direction, a drive cord connected to the motor for rotating the flag shutter in a clockwise direction, support members for supporting the motor and the flag mechanism, and guide members for guiding the drive cord between the motor and the flag mechanism. | ||||||
| 49 | Aircraft flight instrument display system | US936275 | 1978-08-23 | US4247843A | 1981-01-27 | Harry Miller; Parm L. Narveson; William R. Hancock; Joseph P. Hsu |
| Apparatus for providing an integrated display of flight instrument parameters on the screen of a single cathode ray tube is presented. The synthetically generated symbology provides the pilot with an integrated display of substantially all aircraft attitude and flight path command and control parameters including attitude and magnetic heading, barometric and radiometric attitude, vertical spread, critical take-off speeds, true airspeed and Mach airspeed, flight path angle, flight director path control commands, and mode annunciation for the flight director and automatic pilot systems. | ||||||
| 50 | Remote selector for flight instruments | US591559 | 1975-06-30 | US4042867A | 1977-08-16 | Richard Earl Schaffer; Paul Allen Rauschelbach |
| Apparatus for remotely adjusting reference indicia of display instruments such as flight instruments wherein a knob affixed to the shaft of a d.c. generator, remotely disposed from the flight instrument produces a d.c. signal, the magnitude and polarity of which are dependent on the speed and direction, respectively, of rotation of the knob. The d.c. signal is coupled to a d.c. motor mechanically connected to said flight instrument reference indicia and adjusts the same accordingly. The apparatus further includes circuitry, electrically connected between the d.c. generator and the d.c. motor for producing compensating voltages equal to the start-up voltages of the d.c. motor, which when added to the d.c. signal insure a continuous response by the d.c. motor to the d.c. signal, and also for isolating the output impedance of the d.c. generator from the d.c. motor. | ||||||
| 51 | Aircraft flight instrument system | US28770263 | 1963-06-13 | US3277484A | 1966-10-04 | BOSTWICK DUNBAR W |
| 52 | Integrated flight instrument system | US81150759 | 1959-05-06 | US3206974A | 1965-09-21 | ANDRESEN JOHN H |
| 53 | Attitude-indicating flight instrument | US47125943 | 1943-01-04 | US2404603A | 1946-07-23 | SUMMERS JR THOMAS O |
| 54 | 飛行時間型機器におけるM/Z標的減衰 | JP2013558512 | 2012-03-15 | JP6057924B2 | 2017-01-11 | リチャードソン・キース |
| 55 | Low cost flight instrumentation system | US11375486 | 2006-03-14 | US09057627B2 | 2015-06-16 | Robert L. Shaw |
| A device for providing flight condition information and a method of displaying such information. In one form, the device functions as a backup system to provide flight condition information in the event of partial or complete inoperability of a primary flight instrument system, or to complement such primary flight instrument system. Numerous sensors collect flight data, which can pass through devices to convert and manipulate the data to produce flight condition information that can be displayed in such a way as to reduce a pilot's cognitive workload. The information displayed includes at least flight path angle, lateral acceleration, and turn rate. Additional information that may be displayed includes heading information, as well as information relating to airspeed and altitude, among others. In another form, the device can be part of either a primary or backup system. | ||||||
| 56 | Electronic flight instrument displays | US10420602 | 2003-04-22 | US20030193411A1 | 2003-10-16 | Ricardo A. Price |
| The present invention is directed to novel primary flight displays, moving map displays and engine parameter displays for aircraft cockpits. These displays process data gathered from various aircraft sensors and, using an various electronic databases, generate intuitive symbols that aid the pilot. The present invention also uses various novel algorithms that use data gathered from inexpensive sensors to derive parameters normally requiring far more expensive sensors. | ||||||
| 57 | Electronic standby flight instrument | US564728 | 1983-12-23 | US4598292A | 1986-07-01 | Vincent A. Devino |
| A self-contained, standby flight instrument includes sensors, processing circuitry, rechargeable power supply, voltage regulation circuitry, and display hardware arranged to provide a continuous display of aircraft airspeed, altitude, roll, pitch and heading regardless of any partial or complete failure in the primary instrumentation, an interrelated subsystem, or the electric power supply. | ||||||
| 58 | Integrated flight instrument system | US81150859 | 1959-05-06 | US3112644A | 1963-12-03 | SCHROEDER EVERETT H |
| 59 | CURSOR MANAGEMENT ON A MULTIPLE DISPLAY ELECTRONIC FLIGHT INSTRUMENTATION SYSTEM | PCT/US2001/029001 | 2001-09-18 | WO02025211A2 | 2002-03-28 | |
| An aircraft display and control system (100) generally includes a processor (106), a cursor control and selection device (104), an aeronautical information database (110), a geographic database (108), and a plurality of display devices (114). Users (102), such as an aircraft pilot and copilot, can perform flight plan entry and modification by manipulating graphical information on the display devices using cursor control. In one embodiment, the present invention allows multiple membes of an aircraft crew to share control of common flight information display areas, aids the crew's situational awareness by providing software-implemented dynatic symbology and highlighting to indicate cursor location, current panel of entry, and current focus for keyboard and cursor events. | ||||||
| 60 | CURSOR MANAGEMENT SYSTEM ON A MULTIPLE DISPLAY ELECTRONIC FLIGHT INSTRUMENTATION | EP01971099.5 | 2001-09-18 | EP1319165B1 | 2008-01-16 | SNYDER, Mark, I. |
| An aircraft display and control system (100) generally includes a processor (106), a cursor control and selection device (104), an aeronautical information database (110), a geographic database (108), and a plurality of display devices (114). Users (102), such as an aircraft pilot and copilot, can perform flight plan entry and modification by manipulating graphical information on the display devices using cursor control. In one embodiment, the present invention allows multiple membes of an aircraft crew to share control of common flight information display areas, aids the crew's situational awareness by providing software-implemented dynatic symbology and highlighting to indicate cursor location, current panel of entry, and current focus for keyboard and cursor events. | ||||||
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