Method for determining a minimum control speed for an aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G05B-009/03
G05B-015/02
G05D-001/00
출원번호
US-0814172
(2001-03-22)
우선권정보
FR-0003719 (2000-03-23)
발명자
/ 주소
David Burson FR
출원인 / 주소
Eads Airbus SA FR
대리인 / 주소
Stevens, Davis, Miller & Mosher, LLP
인용정보
피인용 횟수 :
4인용 특허 :
4
초록▼
A method for determining a minimum control speed for an aircraft includes measuring, during at least one flight of the aircraft, the values of predefined parameters, recording these values in a memory, and determining, on the basis of these measurements and of at least one predefined certification v
A method for determining a minimum control speed for an aircraft includes measuring, during at least one flight of the aircraft, the values of predefined parameters, recording these values in a memory, and determining, on the basis of these measurements and of at least one predefined certification value received from memory, a certification value (Cnfcertif) for the yaw moment (Cnf) created by the shutting down of one engine of the aircraft. The certification value (Cnfcertif) is used to determine the minimum control speed. On the basis of measured values of the sideslip (.beta.), the lateral force (Cy), and a certification value (Cycertif), a certification value (.beta.certif) is determined, and, on the basis of the measured value of the sideslip (.beta.), the lateral force (Cy), the yaw moment (Cnf), and the certification values (Cycertif) and (.beta.certif), the certification value (Cnfcertif) is determined.
대표청구항▼
1. A method for determining, on an aircraft equipped with a plurality of engines, a minimum control speed with at least one engine shut down, said method comprising the steps of:(a) measuring, during at least one flight of said aircraft, values of predefined parameters on said aircraft, (b) determin
1. A method for determining, on an aircraft equipped with a plurality of engines, a minimum control speed with at least one engine shut down, said method comprising the steps of:(a) measuring, during at least one flight of said aircraft, values of predefined parameters on said aircraft, (b) determining, on the basis of said measurements and at least one predefined certification value, a certification value (Cnfcertif) for a yaw moment (Cnf) created by a shutting down of said at least one engine; (c) calculating, on the basis of said certification value (Cnfcertif), a value of a parameter (K) to allow forming of a first relationship: .DELTA.fn=K.Vc2, in which:.DELTA.fn illustrates a asymmetry of thrust due to the shutting down of the at least one engine; and Vc represents a speed of the aircraft; and (d) determining, on the basis of said first relationship and of engine thrust curves, said minimum control speed, wherein step (b) comprises: (i) deducing, on the basis of simultaneously measured values of, respectively, the sideslip (.beta.) and the lateral force (Cy), a second relationship between said sideslip (.beta.) and said lateral force (Cy) is deduced; (ii) determining, on the basis of said second relationship and a certification value (Cycertif) of said lateral force (Cy), a corresponding certification value (.beta.certif) for the sideslip (.beta.); (iii) deducing, on the basis of the simultaneously measured values of , respectively, said sideslip (.beta.), said lateral force (Cy) and said yaw moment (Cnf), a third relationship between said sideslip (.beta.), said lateral force (Cy) and said yaw moment (Cnf); and (iv) determining said certification value (Cnfcertif) on the basis of said third relationship and said certification values (Cycertif) and (.beta.certif).
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이 특허에 인용된 특허 (4)
Cleary Patrick J. (Federal Way WA) Kelman Lloyd S. (Redmond WA) Horn Richard L. (Seattle WA), Aircraft performance margin indicator.
Larramendy Panxika,FRX ; Zaccaria Patrick,FRX ; Clavel Thierry,FRX ; Garavel Fran.cedilla.ois,FRX, Device for controlling the thrust of a multi-engine aircraft.
Delporte, Martin; Lambeaux, Sophie; Ronceray, Didier; Legier, Jean-Philippe, Method and device for limiting the roll command of an aircraft as a function of a thrust asymmetry.
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