IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0890182
(2004-07-14)
|
등록번호 |
US-7366592
(2008-04-29)
|
우선권정보 |
FR-03 08603(2003-07-15) |
발명자
/ 주소 |
- Delaplace,Franck
- Buisson,Dominique
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
9 인용 특허 :
5 |
초록
▼
A control system for an aircraft includes an actuation section that moves lift-enhancing devices as a function of received control orders, a control member operable by a pilot of the aircraft, and a control unit that includes a control section that produces control orders, as a function of actuation
A control system for an aircraft includes an actuation section that moves lift-enhancing devices as a function of received control orders, a control member operable by a pilot of the aircraft, and a control unit that includes a control section that produces control orders, as a function of actuation of the control member, so as to control the actuation section to bring the lift-enhancing devices into a predetermined position. The control unit further includes a device that produces automatically auxiliary control orders which are transmitted to the actuation section to automatically retract the lift-enhancing devices when the aircraft is in a first flight condition and another device that automatically disables control orders produced by the control section following actuation of the control member to deploy the lift-enhancing devices when the aircraft is in a second flight condition.
대표청구항
▼
The invention claimed is: 1. A system for automatically controlling lift-enhancing devices of an aircraft, in particular wing leading edge slats, which are able to be deployed and retracted, said system comprising: actuation means, for moving said lift-enhancing devices, as a function of control or
The invention claimed is: 1. A system for automatically controlling lift-enhancing devices of an aircraft, in particular wing leading edge slats, which are able to be deployed and retracted, said system comprising: actuation means, for moving said lift-enhancing devices, as a function of control orders received; at least one control member able to be actuated by a pilot of the aircraft; and a control unit which comprises a control means which is able to produce control orders, as a function of the actuation of said control member, so as to control said means of actuation so that the latter bring said lift-enhancing devices into a determined position, wherein said control unit furthermore comprises: a first device able to produce, automatically, auxiliary control orders which are transmitted to said actuation means so as to automatically retract said lift-enhancing devices, when the aircraft is in a first flight condition; and a second device for automatically disabling control orders produced by said control means following actuation of said control member so as to deploy said lift-enhancing devices, when the aircraft is in a second flight condition. 2. The system as claimed in claim 1, wherein said first device continuously and automatically verifies whether the aircraft is in said first flight condition, by taking account of the speed and of the angle of incidence of the aircraft. 3. The system as claimed in claim 1, wherein said first device comprises: a first means for monitoring the speed of the aircraft and for emitting as appropriate a first signal indicating an overshoot of a permitted limit speed; a second means for monitoring the angle of incidence of the aircraft and for emitting as appropriate a second signal indicating an overshoot of a permitted limit angle of incidence; and a third means for producing said auxiliary control orders, when at least said first and second means emit said first and second signals at the same time. 4. The system as claimed in claim 3, wherein said first means compares the actual speed of the aircraft with said permitted limit speed corresponding to a permitted maximum speed, which depends on the current configuration and on the weight of the aircraft. 5. The system as claimed in claim 3, wherein said second means compares the actual angle of incidence of the aircraft with said permitted limit angle of incidence corresponding to a stalling angle of incidence which depends on a configuration of the aircraft that one seeks to obtain and on the Mach number of the aircraft. 6. The system as claimed in claim 3, wherein said first device furthermore comprises a fourth means for monitoring the derivative of the angle of incidence of the aircraft and for emitting as appropriate a fourth signal, and wherein said third means produces said auxiliary control orders, only when said fourth signal is emitted at the same time as said first and second signals. 7. The system as claimed in claim 6, wherein said fourth means comprises: a first element for comparing the derivative of the angle of incidence of the aircraft with a predetermined threshold value and for emitting as appropriate a signal indicating an overshoot of this threshold value; a second element for comparing the actual angle of incidence of the aircraft with an angle of incidence value dependent on the stalling angle of incidence and for emitting as appropriate a signal indicating an overshoot of this angle of incidence value; and a third element for producing said fourth signal, when said first and second elements emit overshoot signals at the same time. 8. The system as claimed in claim 1, wherein said second device verifies, automatically, whether the aircraft is in said second flight condition, by taking account of the speed and of the altitude of the aircraft. 9. The system as claimed in claim 1, wherein said second device comprises: a fifth means for monitoring the speed of the aircraft and for emitting as appropriate a fifth signal indicating an overshoot of a permitted limit speed; a sixth means for monitoring the altitude of the aircraft and for emitting as appropriate a sixth signal indicating an overshoot of a permitted limit altitude; and a seventh means for producing disabling orders, when at least one of said fifth and sixth means emits one of said fifth and sixth signals. 10. The system as claimed in claim 9, wherein said fifth means compares the actual speed of the aircraft with said permitted limit speed corresponding to a permitted maximum speed, which depends on the current configuration and on the weight of the aircraft. 11. The system as claimed in claim 10, wherein said fifth means furthermore comprises a hysteresis loop. 12. The system as claimed in claim 9 to 11, wherein said sixth means compares the actual altitude of the aircraft with said permitted limit altitude corresponding to a possible maximum altitude for a configuration of the aircraft that one seeks to obtain. 13. The system as claimed in claim 9, wherein said second device furthermore comprises: an eighth means able to detect any actuation of the control member to deploy-said lift-enhancing devices; and a ninth means which disables the control orders corresponding to such an actuation to deploy said lift-enhancing devices, when, at one and the same time, said eighth means detects such an actuation and said seventh means produces disabling orders.
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