Method of determining the mean wind speed with respect to the ground during the flight of an aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G06F-015/20
G06F-015/54
출원번호
US-0464876
(1990-01-17)
우선권정보
FR-0000533 (1989-01-18)
발명자
/ 주소
Arethens Jean P. (Drme FRX)
출원인 / 주소
Sextant Avionique (Valence FRX 03)
인용정보
피인용 횟수 :
3인용 특허 :
0
초록▼
A method is provided for determining the speed of the mean wind with respect to the ground during the flight of an aircraft. At each time of rank i of a succession of n times spread out over a flight period, the modulus Vi of the air speed of the aircraft and the three components SNi, SEi and SVi of
A method is provided for determining the speed of the mean wind with respect to the ground during the flight of an aircraft. At each time of rank i of a succession of n times spread out over a flight period, the modulus Vi of the air speed of the aircraft and the three components SNi, SEi and SVi of the ground speed of the aircraft are measured. Then, using the method of least squares, the system of n(n-1)/2 equations with three unknowns WN,WE and WV is solved: 2(SNi-SNj)WN+2(SEi-SEj)WE+2(SVi-SVj)WV =SNj2+SEi2-SEj2+SVi2-SVj2+Vj2-Vi2 (5) in which WN,WE and WV are the three components of the mean wind speed, during the flight period. In response to the components thus determined, the equipment of the aircraft which is sensitive to the wind, for example the firing equipment, is controlled.
대표청구항▼
A device for providing the three components WN, WE and WV, in an Earth reference frame, of speed with respect to the ground of the wind during a flight period of an aircraft, for use by equipment of said aircraft which is sensitive to the wind, comprising: means for measuring including an anemobarom
A device for providing the three components WN, WE and WV, in an Earth reference frame, of speed with respect to the ground of the wind during a flight period of an aircraft, for use by equipment of said aircraft which is sensitive to the wind, comprising: means for measuring including an anemobarometric sensor and an inertial unit which comprises accelerometers, at each time of rank i of a succession of times spread out over said flight period, a value Vi of the modulus of the speed of said aircraft with respect to the air mass in which it moves and values SNi, SEi, SVi of the three components, in said Earth reference frame, of the ground speed of said aircraft; a digital memory for storing said measured values; and computer means including a microprocessor, for solving, using the method of least squares, a system of equations with three unknowns WN, WE, and WV, in which system a current equation is: 2(SNi-SNR)WN+2(SEi-SER)WE+2(SVi-SVR)WV=SNi2-SNR2+SEi2-SER2+SVi2-SVR2+VR2-Vi2 VR, SNR, SER and SVR being values, stored before the time of rank i in said digital memory, of said modulus and of said three components of the ground speed of said aircraft, respectively, wherein said three components are output to said equipment.
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