IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0925605
(1997-09-08)
|
우선권정보 |
FR-0010965 (1996-09-09) |
발명자
/ 주소 |
- Larramendy Panxika,FRX
- Zaccaria Patrick,FRX
- Clavel Thierry,FRX
- Garavel Fran.cedilla.ois,FRX
|
출원인 / 주소 |
- Aerospatiale Societe Nationale Industrielle, FRX
|
대리인 / 주소 |
Marshall, O'Toole, Gerstein, Murray & Borun
|
인용정보 |
피인용 횟수 :
12 인용 특허 :
5 |
초록
▼
The present invention relates to a device for controlling the thrust of an aircraft, with several engines (M1, M4), comprising calculation units (UC1, UC4) that formulate first commands for controlling the engine speeds. According to the invention, said device (1) additionally comprises means (CONT1
The present invention relates to a device for controlling the thrust of an aircraft, with several engines (M1, M4), comprising calculation units (UC1, UC4) that formulate first commands for controlling the engine speeds. According to the invention, said device (1) additionally comprises means (CONT1, CONT4) of controlling the two outer engines (M1, M4), calculation means that formulate second commands for controlling the speed of the outer engines (M1, M4) making it possible to obtain a reduction in thrust, and switching means which, during normal operation of the outer engines (M1, M4) send the first commands to these engines and, when one outer engine (M1) fails, send the second commands to the opposite outer engine (M4).
대표청구항
▼
[ We claim:] [1.] A device for controlling the thrust of an aircraft (A), this thrust being generated by a number of engines (M1 to M4) set out more or less in a line (L--L) which is orthogonal to the longitudinal axis (X--X) of the aircraft (A), and are arranged respectively so that they are symmet
[ We claim:] [1.] A device for controlling the thrust of an aircraft (A), this thrust being generated by a number of engines (M1 to M4) set out more or less in a line (L--L) which is orthogonal to the longitudinal axis (X--X) of the aircraft (A), and are arranged respectively so that they are symmetric with respect to said longitudinal axis (X--X), which device comprises:calculation units (UC1, UC4) which are associated respectively with each of said engines, each of said calculation units (UC1, UC4) formulating first commands for controlling the speed of the associated engine and sending said first commands to said associated engine;control means (CONT1, CONT4) which respectively monitor the operation of at least some of said engines (M1, M4) and which detect failures of said monitored engines (M1, M4);calculation means (MC) which are associated respectively at least with the calculation units (UC1, UC4) associated with said monitored engines (M1, M4) and which determine second commands for controlling the speed of said monitored engines (M1, M4) making it possible to reduce the thrust of these engines relative to said first commands; andswitching means (COM) associated with said calculation means (MC) and with the corresponding calculation units (UC1, UC4) and which:when said monitored engines (M1, M4) are operating normally send the corresponding first commands to these engines; and whichwhen one of said monitored engines (M1) fails, send the corresponding second commands to at least one engine (M4) which is on the opposite side of the longitudinal axis (X--X) of the aircraft (A) to said failed engine (M1),wherein said control means (CONT1, CONT4), said calculation means (MC) and said switching means (COM) are associated with each of the engines (M1 to M4) of the aircraft (A) and are intended, when one of the two outer engines (M1) fails, these engines being the ones furthest away from and one on either side of the longitudinal axis (X--X), to reduce the thrust of all the engines on the opposite side of the longitudinal axis (X--X) of the aircraft (A) to said failed engine.
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