IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0990656
(2009-04-30)
|
등록번호 |
US-8814102
(2014-08-26)
|
우선권정보 |
FR-08 02539 (2008-05-07) |
국제출원번호 |
PCT/FR2009/000514
(2009-04-30)
|
§371/§102 date |
20101102
(20101102)
|
국제공개번호 |
WO2009/138596
(2009-11-19)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
Novak Druce Connolly Bove + Quigg LLP
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
5 |
초록
▼
The method of the invention comprises imparting to the flaps (6G, 6D) of said aircraft either a nose-up deflection (αF) corresponding to the maximum sharpness if the nose-up order is higher than a predetermined threshold, or a deflection (α0) corresponding to the minimum drag if the nose-up order is
The method of the invention comprises imparting to the flaps (6G, 6D) of said aircraft either a nose-up deflection (αF) corresponding to the maximum sharpness if the nose-up order is higher than a predetermined threshold, or a deflection (α0) corresponding to the minimum drag if the nose-up order is lower than said threshold.
대표청구항
▼
1. A method for reducing the takeoff run of an aircraft (AC) provided with at least one steering joystick (14), with ailerons (6G, 6D) carried by the wings (2G, 2D) of said aircraft and with mobile aerodynamic rudder surfaces (7, 9G, 9D), such a takeoff run during which said aircraft (AC) runs on a
1. A method for reducing the takeoff run of an aircraft (AC) provided with at least one steering joystick (14), with ailerons (6G, 6D) carried by the wings (2G, 2D) of said aircraft and with mobile aerodynamic rudder surfaces (7, 9G, 9D), such a takeoff run during which said aircraft (AC) runs on a takeoff runway (RW) while accelerating and at the end of which the pilot of said aircraft communicates to said steering joystick (14) a tilted nose-up takeoff position (βD) so that said mobile aerodynamic rudder surfaces (7, 9G, 9D) cause said aircraft (AC) to take off, comprising the steps of: determining a nose-up tilting threshold (βs) of said steering joystick (14), lower than said takeoff position (β0); andcontrolling said ailerons (6G, 6D) so that they take: a symmetric position (αF) deflected downwards corresponding to a maximum fineness for said aircraft, if the nose-up tilting (β) of said steering joystick (14) is higher than said tilting threshold (βs), anda symmetric position (α0) at least substantially close to that being in continuation of said wings (2G, 2D) and providing a minimum drag for said ailerons, if the nose-up tilting of said steering joystick is lower than said tilting threshold (βs);establishing a velocity threshold (Vs) for the aircraft running on said takeoff runway (RW) and in that said ailerons (6G, 6D) take: said symmetric position (αF) deflected downwards corresponding to a maximal fineness for said aircraft, if the nose-up tilting (β) of said steering joystick is higher than said tilting threshold (βs) or if the running velocity (V) of said aircraft is lower than said velocity threshold (Vs) andsaid symmetric position (α0), at least substantially close to that being in continuation of said wings and providing a minimum drag for said ailerons (6G, 6D), if the nose-up tilting (β) of said steering joystick (14) is lower than said tilting threshold (βs) and if the running velocity (V) of said aircraft is higher than said velocity threshold (Vs); establishing: a ground criterion (CS), being equal to 1 when said aircraft is on flight and being equal to 0 when said aircraft is on the ground;a velocity criterion (CV), being equal to 1 when the running velocity (V) of said aircraft is lower than said velocity threshold (Vs) and being equal to 0 when said running velocity (V) is higher than said velocity threshold (Vs); anda steering joystick criterion, being equal to 1 if the nose-up tilting (β) of said joystick is higher than said tilting threshold (β3) and being equal to 0 if said nose-up tilting (β) is lower than said tilting threshold (βs); and addressing each of the three criteria (CS, CV, Cβ) at a respective input of an OR logic gate or similar (18), having its outlet controlling said ailerons (6G, 6D): to said symmetric position (αF) deflected downward corresponding to a maximum fineness for the aircraft, if a 1 appears therein; orto said symmetric position (α0) at least substantially close to that being in continuation of said wings (2G, 2D) and providing a minimum drag for the ailerons, if a 0 appears therein. 2. The method according to claim 1, wherein said nose-up tilting threshold (βS) corresponds at least approximately to one third of the maximum nose-up stroke (βM) of said steering joystick (14). 3. The method according to claim 1, wherein said velocity threshold (Vs) is equal to a few tens of knots. 4. The method according to claim 3, wherein said velocity threshold (Vs) is at least approximately equal to 40 kts. 5. An aircraft implementing the method according to claim 1.
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