| 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 | 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. | ||||||
| 62 | 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. | ||||||
| 63 | 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. | ||||||
| 64 | 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). | ||||||
| 65 | 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. | ||||||
| 66 | 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. | ||||||
| 67 | 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). | ||||||
| 68 | 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). | ||||||
| 69 | VERFAHREN ZUR KORREKTUR DES FLUGABLAUFS EINES FLUGGERÄTES | EP97902315.7 | 1997-02-04 | EP0892962B1 | 2001-07-04 | ONKEN, Reiner; PREVOT, Thomas |
| 70 | 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. |
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| 71 | 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. |
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| 72 | 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. | ||||||
| 73 | 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. | ||||||
| 74 | 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). | ||||||
| 75 | 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. | ||||||
| 76 | 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). | ||||||
| 77 | 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. | ||||||
| 78 | VERFAHREN ZUM STEUERN EINES FLUGGERÄTS IN FORM EINES MULTICOPTERS UND ENTSPRECHENDES STEUERUNGSSYSTEM | EP13724240.0 | 2013-05-17 | EP2852528A2 | 2015-04-01 | 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, which 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); 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; furthermore the network contains a second multiplicity of regulators which determine in an autonomous and decentralized fashion in each case a regulating signal for in each case at least one rotor on the basis of the sensor data and preferably also on the basis of the rotor operating states, and make said regulating signal available in the network; the rotors are regulated by means of the regulating signals in such a way that flight behaviour of the multicopter corresponds substantially to the prescription by the pilot control instruction. | ||||||
| 79 | METHOD AND APPARATUS FOR TRACKING THE POSITION AND VELOCITY OF AIRBORNE INSTRUMENTATION | EP93919927.0 | 1993-08-06 | EP0664008A1 | 1995-07-26 | 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. | ||||||
| 80 | 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. | ||||||
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