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
61	Multiple function generator for aircraft flight instruments	US696457	1976-06-16	US4081730A	1978-03-28	William H. Murtland
A multiple function generator is described in the environment of an airspeed indicator for controlling the maximum allowable airspeed needle in accordance with a plurality of selectable functions of altitude and comprises a cam having a plurality of surface segments shaped in accordance with the functions positioning a cam follower coupled to the maximum allowable airspeed needle. A null-seeking electro-mechanical feedback servo mechanism having an altitude signal applied to its input synchro drives the cam, thereby positioning the needle in accordance with the function of altitude represented by the cam surface segment in contact with the follower. Means are included for altering the null index of the servo thereby selectively engaging the desired cam functionsurface segment with the cam follower in accordance with the function desired. A selection knob is coupled with the indexing means for selecting the function.
62	AIRCRAFT FLIGHT CORRECTION PROCESS	PCT/EP1997000490	1997-02-04	WO1997029438A1	1997-08-14	NFS NAVIGATIONS- UND FLUGFÜHRUNGS-SYSTEME GMBH
Modern flight control systems should be largely automated because of their complexity. A process is disclosed to automatically correct an originally planned aircraft flight after flight-relevant parameters are changed. The process has the following steps: (a) the values of the flight-influencing parameters which determine the planned flight are supplied to a computer and stored therein; (b) when a change occurs, the changed values are also supplied to the computer and compared therein to the stored values; (c) depending on the results of the comparison and on predetermined checking and selection criteria, it is first checked whether the change requires a flight correction, and if that is the case new parameter values for a corrected flight are determined and stored in the computer instead of the previously stored parameter values; (d) the flight correction determined by the new parameter values is initiated; (e) these process steps are repeated whenever necessary every time the parameter values are changed. This process is mainly useful to improve flight planning operations before and during instrument flying in aircraft provided with modern flight equipment.
63	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

64	Redundant avionics for critical flight instruments	US09211103	1998-12-15	US06281810B1	2001-08-28	Richard Factor
Redundant avionics for flight instruments: a plurality of aircraft flight data sensors, which provide data that are normally displayed on indicators in the cockpit, are transmitted to two independent computers. Each computer is associated with and creates images representative of data sensed by the sensors on a respective projected image display creation device which is in the form of a liquid crystal display, for example. Associated illumination sources and one common or two respective sets of optics project the images from each image creation device on a new screen. The image creation device and the optics would cause the image representative of data from the same sensor to be projected to the same location on the screen regardless of which computer and image creation device provided and projected the image. The computers are independently operable for selectively causing the display of information corresponding to data received from none, some or all of the sensors. For example, the computers are operable so that one display device will display information corresponding to data received from some of the sensors and the other display device will display information corresponding to data received from other sensors and the computers are operable so that each computer may cause display of information based on all of the sensors, as required.
65	Glide range depiction for electronic flight instrument displays	US09824181	2001-04-02	US20020140578A1	2002-10-03	Ricardo A. Price
The present invention is directed to novel methods for depicting glide range on moving map displays and on perspective-view primary flight displays. These methods involve processing data gathered from various aircraft sensors and, using a variety of electronic databases, generating intuitive symbols that aid the pilot.
66	Cursor management on a multiple display electronic flight instrumentation system	US09680874	2000-10-06	US06381519B1	2002-04-30	Mark I. Snyder
An aircraft display and control system generally includes a processor, a cursor control and selection device, an aeronautical information database, a geographic database, and a plurality of display devices. Users, 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 members of an aircraft crew to share control of common flight information display areas, aids the crew's situational awareness by providing software-implemented dynamic symbology and highlighting to indicate cursor location, current panel of entry, and current focus for keyboard and cursor events.
67	DISPOSITIF DE COMMANDE DE PALES D'HELICOPTERE OU SIMILAIRE	EP08826478.3	2008-06-12	EP2155553A2	2010-02-24	DE MIRAS, Jérôme; VIDOLOV, Borislav
The invention relates to a device for controlling the blades of a helicopter rotor or similar, including a blade-supporting rotor mast (1). The control device consists of a swash plate (10) extending around the rotor mast and comprising a stationary ring (11) and a rotating ring (12) which is rotationally mounted on the stationary ring and which is connected to the blades and, therefore, rotates with the rotor; and three actuators (23) which generate the controlled movement of the rotating ring both in translation in parallel to the rotor mast and angularly about axes perpendicular to the rotor mast. According to the invention, the three actuators are disposed substantially at the swash plate in the side extension of same, each actuator including a moving part (21) which is directly connected to the stationary ring in order to form therewith a sliding joint such that the movement of the moving part of one of the actuators generates the movement of the associated part of the stationary ring along an axis of the rotor mast (Z).
68	CURSOR MANAGEMENT SYSTEM ON A MULTIPLE DISPLAY ELECTRONIC FLIGHT INSTRUMENTATION	EP01971099.5	2001-09-18	EP1319165A2	2003-06-18	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.
69	GLIDE RANGE DEPICTION FOR ELECTRONIC FLIGHT INSTRUMENT DISPLAYS	PCT/US2002/009960	2002-03-28	WO2002080128A1	2002-10-10	PRICE, Ricardo, A.
The present invention is directed to novel methods for depicting glide range (16, 34) on moving map displays (3) and on perspective-view primary flight displays. These methods involve processing data gathered from various aircraft sensors and, using a variety of electronic databases, generating intuitive symbols that aid the pilot.
70	Support device for a motorised flying instrument in a wind tunnel	US10189260	2002-07-03	US20030024304A1	2003-02-06	Francoise Arnaud; Antoine Scotto D'Appolonia
A support device for a motorised flying instrument in a wind tunnel. To carry out tests in a wind tunnel on a motorised flying instrument (10), with the motor on, under different attitudes hands off, the instrument is connected to the fixed structure (15) of the wind tunnel (11) by a mounting device (12) at least one of the supports (14, 16) of which is fitted with a length adjustment system, such as a hydraulic jack (28). This jack (28) is remote controlled, in real time, by a control system (42).
71	Support device for a motorised flying instrument in a wind tunnel	US09884161	2001-06-20	US20020023484A1	2002-02-28	Jean-Paul Demay; Laurent Carton
A support device for a motorized flying instrument in a wind tunnel. To carry out tests in a wind tunnel on a motorized flying instrument (10), with the motor on, under different attitudes hands off, the instrument is connected to the fixed structure (15) of the wind tunnel (11) by a mounting device (12) at least one of the supports (14, 16) of which is fitted with a length adjustment system, such as a hydraulic jack (28). This jack (28) is remote controlled, in real time, by a control system (42).
72	Support device for a motorized flying instrument in a wind tunnel	US09884161	2001-06-20	US06571618B2	2003-06-03	Jean-Paul Demay; Laurent Carton
A device supports a motorized flying instrument in a wind tunnel. To carry out tests in a wind tunnel on a motorized flying instrument (10), with the motor on, under different attitudes hands off, the instrument is connected to the fixed structure (15) of the wind tunnel (11) by a mounting device (12) at least one of the supports (14, 16) of which is fitted with a length adjustment system, such as a hydraulic jack (28). This jack (28) is remote controlled, in real time, by a control system (42).
73	METHOD AND APPARATUS FOR TRACKING THE POSITION AND VELOCITY OF AIRBORNE INSTRUMENTATION	EP93919927.9	1993-08-06	EP0664008B1	1998-12-23	MACDORAN, Peter, F.; CALL, David, B.; GOLD, Kenneth, L.; SCHREINER, William, S.; ZIEL, Fred, A.
A method and system for tracking the position of at least one moving object, such as an airborne meteorological instrument (20) from a ground processing station by intercepting wideband spread spectrum signals transmitted from a plurality of satellites in which the code sequence of the signals is not known, comprises a receiver circuit in the moving object which compresses the wideband signals received into a narrow band, removes any frequency bias with a reference oscillator (12) having a frequency offset value, forms a narrow analog baseband (9) and transmits (14) to the processing station at which spectral lines are produced and compared with synthetic spectrum values to determine the identity of each satellite, the reference oscillator frequency offset value is estimated, and the location and velocity of the moving object is determined.
74	METHOD FOR CONTROLLING AN AIRCRAFT IN THE FORM OF A MULTICOPTER AND CORRESPONDING CONTROL SYSTEM	PCT/EP2013060267	2013-05-17	WO2013174751A3	2014-01-16	WOLF STEPHAN; RUF THOMAS
A method and a system are proposed for controlling an aircraft in the form of a multicopter which has a plurality of redundant rotors (4), preferably arranged in a common rotor plane, in order, on the one hand, to generate lift, and, on the other hand, also propulsion by inclining the at least one rotor plane, wherein the regulation of the position and the control of the multicopter are carried out by changing rotor rotational speeds as a function of pilot control instructions. The system is characterized in that the rotors (4) are connected to one another in terms of data technology via a failsafe network (8), and they communicate their respective operating state, in particular their rotor rotational speed, in the network (8), and in that the network contains a first multiplicity of redundant sensors which determine control-relevant data and make it available in the network, in particular inclination, acceleration, rotational speed and/or position in all three spatial axes of the multicopter.
75	Flight instrument displaying a variable rotational speed of a main rotor of an aircraft	US14607162	2015-01-28	US09409655B1	2016-08-09	Jean-Baptiste Vallart; Patrick Hellio; Patricia Gauthier; Setareh Taheri
A flight instrument that displays the rotational speed of a main rotor of a rotary-wing aircraft, with the flight instrument including display means, a first indicator of a setpoint for the rotational speed of the main rotor, a second indicator of the first current value of the rotational speed of the main rotor, and third and fourth indicators of the limit values of the rotational speed. The setpoint for the rotational speed of the main rotor is variable and the first indicator is stationary on the display means, with the second, third and fourth indicators being movable in relation to the first indicator.
76	VERFAHREN ZUR KORREKTUR DES FLUGABLAUFS EINES FLUGGERÄTES	EP97902315.7	1997-02-04	EP0892962B1	2001-07-04	ONKEN, Reiner; PREVOT, Thomas

77	VERFAHREN ZUR KORREKTUR DES FLUGABLAUFS EINES FLUGGERÄTES	EP97902315.0	1997-02-04	EP0892962A1	1999-01-27	ONKEN, Reiner; PREVOT, Thomas
Modern flight control systems should be largely automated because of their complexity. A process is disclosed to automatically correct an originally planned aircraft flight after flight-relevant parameters are changed. The process has the following steps: (a) the values of the flight-influencing parameters which determine the planned flight are supplied to a computer and stored therein; (b) when a change occurs, the changed values are also supplied to the computer and compared therein to the stored values; (c) depending on the results of the comparison and on predetermined checking and selection criteria, it is first checked whether the change requires a flight correction, and if that is the case new parameter values for a corrected flight are determined and stored in the computer instead of the previously stored parameter values; (d) the flight correction determined by the new parameter values is initiated; (e) these process steps are repeated whenever necessary every time the parameter values are changed. This process is mainly useful to improve flight planning operations before and during instrument flying in aircraft provided with modern flight equipment.
78	VERFAHREN ZUM STEUERN EINES FLUGGERÄTS IN FORM EINES MULTICOPTERS UND ENTSPRECHENDES STEUERUNGSSYSTEM	PCT/EP2013/060267	2013-05-17	WO2013174751A2	2013-11-28	WOLF, Stephan; RUF, Thomas
Vorgeschlagen wird ein Verfahren und ein System zum Steuern eines Fluggeräts in Form eines Multicopters, welcher mehrere, vorzugsweise in einer gemeinsamen Rotorebene angeordnete, redundante Rotoren (4) aufweist, um einerseits Auftrieb und andererseits durch Neigung der wenigstens einen Rotorebene auch Vortrieb zu erzeugen, wobei Lageregelung und Steuerung des Multicopters durch Veränderungen von Rotordrehzahlen in Abhängigkeit von Piloten-Steuerbefehlen erfolgen, welches dadurch gekennzeichnet ist, dass die Rotoren (4) über ein ausfallsicheres Netzwerk (8) miteinander datentechnisch verbunden sind und ihren jeweiligen Betriebszustand, insbesondere ihre Rotordrehzahi, in dem Netzwerk (8) kommunizieren; in dem Netzwerk eine erste Mehrzahl an redundanten Sensoren enthalten sind, die steuerungsrelevante Daten ermitteln und in dem Netzwerk bereitstellen, insbesondere Neigung, Beschleunigung, Drehrate und/oder Position in allen drei Raumachsen des Multicopters; weiterhin in dem Netzwerk eine zweite Mehrzahl an Reglern enthalten sind, die autonom und dezentral anhand der Sensordaten, und vorzugsweise außerdem anhand der Rotor-Betriebszustände, jeweils ein Regelsignal für jeweils wenigstens einen Rotor bestimmen und in dem Netzwerk bereitstellen; die Rotoren mittels der Regelsignale so geregelt werden, dass ein Flugverhalten des Multicopters im Wesentlichen der Vorgabe durch den Piloten-Steuerbefehl entspricht.
79	DISPOSITIF DE COMMANDE DE PALES D'HELICOPTERE OU SIMILAIRE	EP08826478.3	2008-06-12	EP2155553B1	2011-05-18	DE MIRAS, Jérôme; VIDOLOV, Borislav
The invention relates to a device for controlling the blades of a helicopter rotor or similar, including a blade-supporting rotor mast (1). The control device consists of a swash plate (10) extending around the rotor mast and comprising a stationary ring (11) and a rotating ring (12) which is rotationally mounted on the stationary ring and which is connected to the blades and, therefore, rotates with the rotor; and three actuators (23) which generate the controlled movement of the rotating ring both in translation in parallel to the rotor mast and angularly about axes perpendicular to the rotor mast. According to the invention, the three actuators are disposed substantially at the swash plate in the side extension of same, each actuator including a moving part (21) which is directly connected to the stationary ring in order to form therewith a sliding joint such that the movement of the moving part of one of the actuators generates the movement of the associated part of the stationary ring along an axis of the rotor mast (Z).
80	Edit area algorithm for navigation display of an electronic flight instrument system	US594672	1990-10-09	US5041982A	1991-08-20	Vijayakumar Rathnam
In the navigation display of the electronic flight instrument system, the arc mode and Rose Nav mode of a navigation display require computation of parameters for a greater surface (modified Edit) area than the Edit area for each display scale. When the icons representing selected navigational features are included on the navigation display, the retrieved and stored icons can be positioned external to the viewable Edit area. Because access to a dictionary defining the position of the icons is sequential and because the display buffer storage unit from which the screen display is created has a limited capacity, the arc or Rose Nav display can include features in the non-viewable modified Edit area while not including important features in the Edit area. An algorithm is described that determines when a feature with which an icon is associated is in the Edit area and selects the data associated with those features in the Edit area to be stored in the display buffer storage unit. Data associated with features only in the modified Edit area are not stored in the display buffer storage unit. In the arc display mode and the Rose Nav display mode, the display screen can be continuously updated requiring the algorithm to operate with a dynamically changing display.

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