Apparatus for determining the groundspeed rate of an aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G05D-001/08
G06F-015/50
G01C-021/10
G01C-021/00
출원번호
US-0457813
(1983-01-13)
발명자
/ 주소
Graupp Frederick G. (Bellevue WA) van Leynseele Francis J. (Edmonds WA)
출원인 / 주소
The Boeing Company (Seattle WA 02)
인용정보
피인용 횟수 :
7인용 특허 :
11
초록▼
Aircraft gyro (20, 22) signals qf24, 26, 28) signals ax, ay, az, representative of longitudinal, lateral, and normal acceleration, respectively, are processed (30, 32, 34, 36, 38, 40) to produce signals aGSLO, aGSLA, and aGSN, representative of the longitudinal, lateral, and normal groundspeed rate
Aircraft gyro (20, 22) signals qf24, 26, 28) signals ax, ay, az, representative of longitudinal, lateral, and normal acceleration, respectively, are processed (30, 32, 34, 36, 38, 40) to produce signals aGSLO, aGSLA, and aGSN, representative of the longitudinal, lateral, and normal groundspeed rate components, respectively. The component signals are summed (50) to produce a signal representative of total aircraft groundspeed rate.
대표청구항▼
Apparatus for determining the groundspeed rate and a maximum speed error of an aircraft comprising: means adapted to receive a signal qfz, ay, az representative of aircraft longitudinal, lateral, and normal acceleration, respectively; means for producing a signal aGSLO representative of the groundsp
Apparatus for determining the groundspeed rate and a maximum speed error of an aircraft comprising: means adapted to receive a signal qfz, ay, az representative of aircraft longitudinal, lateral, and normal acceleration, respectively; means for producing a signal aGSLO representative of the groundspeed rate of said aircraft due to the longitudinal acceleration of said aircraft, where: aGSLO=axcosqGSLA representative of the groundspeed rate of said aircraft due to the lateral acceleration of said aircraft, where: aGSLA=aysin fqGSN representative of the groundspeed rate of said aircraft due to the normal acceleration of said aircraft, where: aGSN=azcosfqGSLO, aGSLA and aGSN signals to produce a signal aGS representative of the total groundspeed rate of said aircraft; filter means for noise filtering said aGS signal; means for producing a signal VeGS signal and said VeGS signal if said aGS signal is greater than zero and if said aGS signal is greater in magnitude than said Vee
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이 특허에 인용된 특허 (11)
Muller ; Hans Rudolf, Aircraft pitch attitude signal generator.
Weinstein Warren D. (Huntington Station NY) Boudreau Jean A. (Commack NY) Gertz Donald (Carle Place NY), Survivable redundant vector sensors for systems with differing maximum output requirements.
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