| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 21 | 电子飞行仪表系统测试设备的装载机构 | CN03241260.6 | 2003-04-09 | CN2611873Y | 2004-04-14 | 邓福生 |
| 一种电子飞行仪表系统测试设备的装载机构，它包括底座、支座、移动工作台、工作台支架、传动轴、螺旋槽凸轮、活动框、碗形压块、控制杆、圆杆，在底座的前端立着支座，支座的上端连接位移座，底座上连接工作台支架，其特征是工作台支架中间连接传动轴，传动轴中间连接螺旋槽凸轮，前端用并帽固定，工作台支架上端连接圆杆，圆杆两端用档圈固定，移动工作台连在圆杆上，移动工作台上有个活动框，活动框下端有个凸轮，凸轮连接控制杆。本实用新型结构紧凑、性能稳定、维修方便、操作简单、定位准确，能确保所有接触点有良好接触，大大提高了电子飞行仪表系统在检测中的可靠性。 | ||||||
| 22 | 비행체를 이용한 원격 검침 시스템 | KR1020140127565 | 2014-09-24 | KR101700634B1 | 2017-01-31 | 정용철; 신봉조; 조태원; 이재현 |
| 사용되는전기, 가스, 수도, 온도, 압력, 유량중 적어도하나이상의계량데이터를측정하는계량기가구비되고, 상기계량기로부터측정된계량데이터를저장하는제1저장부와, 외부로송, 수신하는제1단말장치; 복수개의설정된범위영역들중 선택된하나의특정영역의상공을비행하고, 제2단말장치가구비되는비행모듈; 상기제2단말장치는상기계량기에인접배치되는상기제1단말장치로부터계량데이터를수신하여, 저장하는제2저장부;를포함하며, 상기비행모듈을원격제어하거나또는상기제2단말장치로부터저장된계량데이터를제공받아과금을산출하는관재부를포함하는것을특징으로하는비행체를이용한원격검침시스템을제공한다. | ||||||
| 23 | 비행체를 이용한 원격 검침 시스템 | KR1020140127565 | 2014-09-24 | KR1020160035797A | 2016-04-01 | 정용철; 신봉조; 조태원; 이재현 |
| 사용되는전기, 가스, 수도, 온도, 압력, 유량중 적어도하나이상의계량데이터를측정하는계량기가구비되고, 상기계량기로부터측정된계량데이터를저장하는제1저장부와, 외부로송, 수신하는제1단말장치; 복수개의설정된범위영역들중 선택된하나의특정영역의상공을비행하고, 제2단말장치가구비되는비행모듈; 상기제2단말장치는상기계량기에인접배치되는상기제1단말장치로부터계량데이터를수신하여, 저장하는제2저장부;를포함하며, 상기비행모듈을원격제어하거나또는상기제2단말장치로부터저장된계량데이터를제공받아과금을산출하는관재부를포함하는것을특징으로하는비행체를이용한원격검침시스템을제공한다. | ||||||
| 24 | Flight instrument | US32536252 | 1952-12-11 | US2701473A | 1955-02-08 | FIELDGATE IVAN O |
| 25 | Flight instrument | US454305 | 1974-03-25 | US3940990A | 1976-03-02 | James R. Younkin |
| Aircraft altitude is visually displayed at a front panel of a flight instrument in analog form by a rotating pointer and in digital form by means of a rotary drum digital indicator. Barometric pressure is converted into rectilinear motion to drive a mechanical-to-electrical transducer providing a signal to a servo amplifier having an output coupled to a servomotor. The servomotor drives both the rotating pointer and the rotary drum digital indicator. Also coupled to the mechanical-to-electrical transducer is a manually adjustable set input signal to correct for atmospheric pressure along a given flight path with respect to sea level. Temperature and altitude error corrections are also coupled to the transducer to correct the servomotor drive signal to give a true indicated altitude display. Also driven by the servomotor is a pressure altitude encoder for providing absolute altitude digital signals for transmission to a ground station. As a further extension, the servomotor drives a velocity generator that functions integrally with an altitude selector to provide vertical velocity control signals to the aircraft autopilot system. | ||||||
| 26 | Flight instrument | US601823 | 1975-08-04 | US4008618A | 1977-02-22 | James R. Younkin |
| Aircraft altitude is visually displayed at a front panel of a flight instrument in analog form by a rotating pointer and in digital form by means of a rotary drum digital indicator. Barometric pressure is converted into rectilinear motion to drive a mechanical-to-electrical transducer providing a signal to a servo amplifier having an output coupled to a servomotor. The servomotor drives both the rotating pointer and the rotary drum digital indicator. Also coupled to the mechanical-to-electrical transducer is a manually adjustable set input signal to correct for atmospheric pressure along a given flight path with respect to sea level. Temperature and altitude error corrections are also coupled to the transducer to correct the servomotor drive signal to give a true indicated altitude display. Also driven by the servomotor is a pressure altitude encoder for providing absolute altitude digital signals for transmission to a ground station. As a further extension, the servomotor drives a velocity generator that functions integrally with an altitude selector to provide vertical velocity control signals to the aircraft autopilot system. | ||||||
| 27 | AIRCRAFT FLIGHT INSTRUMENT DISPLAYS | EP96910569.0 | 1996-03-26 | EP0817952A1 | 1998-01-14 | DURNFORD, Simon, J.; BRAITHWAITE, Malcolm, G. |
| 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. | ||||||
| 28 | AIRCRAFT FLIGHT INSTRUMENT DISPLAYS | EP96910569.1 | 1996-03-26 | EP0817952B1 | 2002-11-27 | DURNFORD, Simon, J.; BRAITHWAITE, Malcolm, G. |
| 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. | ||||||
| 29 | Indicator for flight instrument | JP4642978 | 1978-04-19 | JPS53143261A | 1978-12-13 | HARII MIRAA; UIRIAMU REI HANKOTSUKU; PAAMU RII NAABISUN; JIYOSEFU PUUKOU SHIYUU |
| 30 | 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. | ||||||
| 31 | 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. | ||||||
| 32 | Flight instrument for aircraft | US60262645 | 1945-06-30 | US2569473A | 1951-10-02 | HOOVER GEORGE W; EASTON ERVING E |
| 33 | Universal flight instrument | US32366240 | 1940-03-13 | US2300685A | 1942-11-03 | WALTER MCKAY |
| 34 | Combination flight instrument | US60510232 | 1932-04-13 | US2063764A | 1936-12-08 | SMITH WESLEY L |
| 35 | Aerial flight instrument | US51624431 | 1931-02-16 | US1955488A | 1934-04-17 | CRANE CARL J; OCKER WILLIAM C |
| 36 | Basic flight instrument | US816453 | 1986-01-06 | US4638660A | 1987-01-27 | Richard D. Henry |
| A basic flight instrument to provide the pilot the means, by which, he can easily remain upright during instrument conditions. This flight instrument will be highly trustworthy, in that it will be absolutely tumble free due to its basic input derivatives. The instrument will be provided with two separate erection systems, whereby, the roll erection system will consist of a gimbal cage, spring tension erected and the pitch erection system will consist of a drum, the rotation of which will be properly erected by means of a gravitational weight and rotational reversing system. The pilot will be provided with simultaneous display of roll and pitch of reliable derivative. The roll rate of the gyro may be speed and altitude compensated if desired. | ||||||
| 37 | Aircraft flight instrument | US52853444 | 1944-03-29 | US2424511A | 1947-07-22 | STANLEY ROBERT M; STRICKLER JR JOHN F |
| 38 | Aerial flight instrument | US968935 | 1935-03-06 | US2280797A | 1942-04-28 | CRANE CARL J |
| 39 | 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. | ||||||
| 40 | 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. | ||||||
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