飞行仪表相关的专利数据

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	WO0065423A9	2002-06-20	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	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.
43	Aircraft flight instrument system	US28770263	1963-06-13	US3277484A	1966-10-04	BOSTWICK DUNBAR W

44	Integrated flight instrument system	US81150759	1959-05-06	US3206974A	1965-09-21	ANDRESEN JOHN H

45	Integrated flight instrument system	US81150859	1959-05-06	US3112644A	1963-12-03	SCHROEDER EVERETT H

46	Attitude-indicating flight instrument	US47125943	1943-01-04	US2404603A	1946-07-23	SUMMERS JR THOMAS O

47	ELECTRONIC FLIGHT DATA DISPLAY INSTRUMENT	EP07872237.8	2007-07-05	EP2044545A1	2009-04-08	BETHEL, Jeffrey
An electronic display instrument configured to secure in a desired position over multiple pre-existing instrument holes in a dashboard of an aircraft in place of multiple conventional display instruments, each conventional instrument having a conventional readout. The instrument comprises a display screen having a plurality of readouts corresponding to the conventional readouts of the multiple conventional instruments that the electronic display instrument replaces. The instrument further includes a body having a front and a back opposite the front and a top and a bottom opposite the top. The body is positioned adjacent and connected to the display screen. The instrument also includes an electronics module protruding from the back of the body to position in one of the pre-existing instrument holes in the dashboard panel of the aircraft.
48	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.
49	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).
50	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.
51	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.
52	AIRCRAFT FLIGHT INSTRUMENT DISPLAYS	PCT/US1996004121	1996-03-26	WO1996030722A1	1996-10-03	THE SECRETARY OF STATE FOR DEFENCE IN HER BRITANNIC MAJESTY'S GOVERNMENT OF THE UNITED KINGDOM OF GREAT BRITAIN AND NORTHERN IRELAND
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). In a preferred embodiment, a linear slip meter (52) is included to indicate the necessary rudder input to maintain a coordinated turn. In a further embodiment, modes of operation (54) are indicated which, when selected, prompt the pilot to fly and climb or descend with standard rate turns.
53	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.
54	LOW COST FLIGHT INSTRUMENTATION SYSTEM	PCT/US2006009176	2006-03-15	WO2006099436B1	2006-11-23	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.
55	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.
56	Protective cover for flight instrument filter glass	US339329	1989-04-14	US4992881A	1991-02-12	Robert J. Tomasek; Sharon E. Runyon
A protective cover for a flight instrument filter glass mounted in a cockpit instrument panel having a display screen mounted in the display unit. The display unit includes a chassis and a frame-like bezel mounted on the chassis in front of the filter glass. The bezel masks the peripheral interface between the filter glass and the display unit opening. The bezel includes a front surface adjacent to the front of the filter glass and a rear edge spaced from the front surface and adjacent to the instrument panel. The protective cover comprises a faceplate portion having a sidewall and a lip spaced from the faceplate and extending from the sidewall in a direction parallel to the plane of the faceplate. The space between the lip and faceplate being approximately equal to the space between the front surface of the bezel and rear edge of the bezel for retaining the faceplate in spaced relationship from the filter glass.
57	Electronic flight instrument design and evaluation tool	US418105	1982-09-14	US4573925A	1986-03-04	C. James Styers
A design and evaluation system is disclosed which enables the computer generation of graphic displays and symbology used in the design of electronic instrument displays. The graphics and symbology may be positioned, rearranged, altered, and replaced with other graphics or symbology representative of that used in the intended instrument. The display may then be dynamically tested in accordance with programmed or selected manual inputs to determine the aesthetic and functional interactions between symbols or groups of symbols and to evaluate their acceptability in their intended environment. The proposed display may be repeatedly updated, altered and modified during testing until a final version has been selected for the instrument display.
58	KATAPULT ZUM ABSCHIESSEN EINES FLUGGERÄTS	PCT/DE2009/000568	2009-04-23	WO2009143798A1	2009-12-03	TENBERGEN, Martin; KRÜGER, Bernhard
Ein Katapult zum Abschießen eines Fluggeräts weist einen auf einer Führungsschiene (2) bewegbaren Schlitten (14) zur Lagerung des Fluggeräts und zumindest ein spannbares Seil (10), welches zumindest abschnittsweise (12) elastisch ausgebildet ist und mit welchem der Schlitten unter Entspannung des Seils von einer Startposition in eine Abschussposition bewegbar ist, auf. Das Seil ist über zumindest eine Umlenkrolle (26) parallel zu der Führungsschiene geführt.
59	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).
60	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.

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