IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0839545
(1986-03-14)
|
우선권정보 |
FR-0005077 (1985-04-03) |
발명자
/ 주소 |
- Cavasa Victor (Pibrac FRX) Fontaine Jean-Marc (Ramonville FRX)
|
출원인 / 주소 |
- Aerospatiale Societe Nationale Industrielle (Paris FRX 07)
|
인용정보 |
피인용 횟수 :
9 인용 특허 :
5 |
초록
▼
This invention relates to a system for supplying fuel to an aircraft engine, wherein an electronic computer subdivides the stroke of the throttle lever into a plurality of zones, in each of which the thrust of the engine varies between a maximum value and a minimum value. The computer ensures a modu
This invention relates to a system for supplying fuel to an aircraft engine, wherein an electronic computer subdivides the stroke of the throttle lever into a plurality of zones, in each of which the thrust of the engine varies between a maximum value and a minimum value. The computer ensures a modulation of the thrust about the value corresponding to that displayed by the position of said throttle lever. No mechanical link is provided between the lever and the fuel admission valve.
대표청구항
▼
In a system for supplying fuel to an aircraft engine, of the type comprising: a controlled valve, controlling the flowrate of fuel admitted into said engine; a throttle lever, mobile in two opposite directions in a stroke defined by two end positions, said lever being associated with a resolver capa
In a system for supplying fuel to an aircraft engine, of the type comprising: a controlled valve, controlling the flowrate of fuel admitted into said engine; a throttle lever, mobile in two opposite directions in a stroke defined by two end positions, said lever being associated with a resolver capable of delivering a continuous signal indicative of the position of said lever; a transmission arranged between said throttle lever and said controlled valve, to cause one position of said valve to correspond to one position of said lever, said transmission comprising a correction device which, on the one hand, receives a plurality of parameters concerning both the operation of the engine and the environment of said aircraft, as well as the signal from the resolver, and, on the other hand, is capable of correcting the control of said valve by said lever to take into account said parameters; an electronic thrust-adjusting device receiving at least certain of said parameters and the signal from the resolver, and delivering a signal indicative of a reference thrust; and switching means enabling said controlled valve to be controlled: either by voluntary manual actuation of said throttle lever, or, at least at cruising speed of the aircraft, automatically via said electronic thrust-adjusting device, said correction device is entirely electrical and controls said valve via its output signal; the electrical connection between said resolver and said correction device is the sole link between said throttle lever and said correction device; said correction device comprises: first means for subdividing the signal from said resolver into a plurality of consecutive portions; second means for converting each of said portions of signal from the resolver into an elementary valve-control signal, which is characteristic of a control phase of said aircraft and whose ends, except possibly for that elementary valve-control signal which corresponds to idling of the engine, constitute, one, the maximum value and the other, the minimum value of said corresponding elementary signal, the output signal of said correction device being constituted by the juxtaposition of said elementary valve-control signals, with the result that, on the one hand, there is established a mathematical function which ensures that a thrust for the motor corresponds to each position of the throttle lever, and on the other hand, the stroke of said throttle lever is subdivided into a plurality of consecutive zones of which each is associated with a control phase, and corresponds to a thrust range for said engine, the ends of each zone corresponding, one, to the maximum value and the other, to the minimum value of the thrust in the corresponding range; and third means which, when the electronic thrustadjusting device is switched off by action of said switching means, and when said throttle lever lies within such a zone and as a function of said parameters, automatically cause the thrust to vary within the corresponding range, the variation in thrust being effected, from the value corresponding to the position of the throttle lever, both towards said maximum value and towards the minimum value of said range, said maximum and minimum values constituting limits not to be overstepped.
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