Method and system for improving the performance of an aircraft upon take off
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G06F-019/00
G06F-017/10
출원번호
US-0881692
(2010-09-14)
등록번호
US-8437894
(2013-05-07)
우선권정보
FR-09 04421 (2009-09-16)
발명자
/ 주소
Berthereau, Mathieu
출원인 / 주소
Airbus Operations (SAS)
대리인 / 주소
Novak Druce Connolly Bove + Quigg LLP
인용정보
피인용 횟수 :
0인용 특허 :
4
초록▼
A method and system for improving aircraft performances during take-off is described. The system (1) can include means (4, 6, 7) for determining an optimised take-off position of the control surfaces (S1-Sn) of the aircraft, in the case where a regulatory safety criterion relating to the minimum gra
A method and system for improving aircraft performances during take-off is described. The system (1) can include means (4, 6, 7) for determining an optimised take-off position of the control surfaces (S1-Sn) of the aircraft, in the case where a regulatory safety criterion relating to the minimum gradient of climb with a breakdown engine is predominant.
대표청구항▼
1. A method for improving the performance of an aircraft during a take-off phase, said aircraft being provided with aerodynamic control surfaces (S1-Sn) able to have a plurality of separate predetermined take-off positions (P1, P2, P3), each of which corresponds to predefined deflections of said con
1. A method for improving the performance of an aircraft during a take-off phase, said aircraft being provided with aerodynamic control surfaces (S1-Sn) able to have a plurality of separate predetermined take-off positions (P1, P2, P3), each of which corresponds to predefined deflections of said control surfaces (S1-Sn), wherein, before take-off, the following steps are automatically performed: determining a recommended value of the initial rate of climb (V2) of said aircraft, such that at least the following regulatory safety criteria are respected upon take-off: said recommended value of the initial rate of climb (V2) is at least equal to a first predefined speed threshold which is a function of the stalling speed of said aircraft;said recommended value of the initial rate of climb (V2) is at least equal to a second predefined speed threshold which is a function of the minimum control speed with a breakdown engine;the minimum gradient of climb of said aircraft with a breakdown engine is at least equal to a predefined gradient threshold; andselecting among said separate predetermined positions (P1, P2, P3) a take-off position and applying said take-off position to said control surfaces (S1-Sn), wherein:a preliminary step comprises checking whether the safety criterion relating to said minimum gradient of climb with a breakdown engine is predominant with respect to other safety criteria using a theoretical representation (C1, C2, C3) of the take-off mass variations (M) of said aircraft according to the initial rate of climb (V2) thereof, combined with said selected take-off position (P1, P2, P3); andin the case where the minimum gradient of climb with a breakdown engine is a predominant safety criterion, the following steps are performed: i) comparing a predefined value of the initial rate of climb (V2) with said first speed threshold;ii) when the deviation between the predefined value of said initial rate of climb (V2) and said first speed threshold is substantially different from zero, determining optimised deflection commands of said control surfaces (S1-Sn), defining an optimal take-off position (Popt), so as to reduce said deviation upon take-off, with these optimised deflection commands being such that they generate an optimised deflection of said control surfaces less than that of said selected position; andiii) applying the optimised deflection commands thus determined to said control surfaces (S1-Sn), whatever said previously selected take-off position (P1, P2, P3). 2. The method according to claim 1, wherein, at step ii), said optimised deflection commands are such that said deviation is substantially equal to zero. 3. The method according to claim 1, wherein, at step ii), said optimised deflection commands are determined from at least some of the following information: the take-off mass (M) of said aircraft;the flight attitude of said aircraft;the engine thrust level of said aircraft;the initial rate of climb (V2);the outside temperature. 4. The method according to claim 1, wherein said theoretical representation (C1, C2, C3) is formed by the three following successive segments: a first vertical segment (Xa1, Xa2, Xa3) for which the regulatory safety criterion relating to said second predefined speed threshold is predominant;a second intermediate segment (Xb1, Xb2, Xb3) for which the regulatory safety criterion relating to said first predefined speed threshold is predominant; anda third segment (Xc1, Xc2, Xc3) for which the regulatory safety criterion relating to said minimum gradient of climb of said aircraft with a breakdown engine is predominant. 5. The method according to claim 1, wherein steps i), ii) and iii) are performed considering, as a predefined value, the recommended value of the initial rate of climb (V2), determined before take-off. 6. The method according to claim 1, wherein steps i), ii) and iii) are performed considering, as a predefined value, the actual value of the initial rate of climb (V2) upon take-off. 7. A system for improving the performance of an aircraft during a take-off phase, said aircraft being provided with aerodynamic control surfaces (S1-Sn) able to have a plurality of separate predetermined take-off positions (P1, P2, P3), each of which corresponds to predefined deflections of said control surfaces (S1-Sn), said system (1) comprising the following means (3) for which the corresponding operations are implemented, automatically, before take-off: means (3) for determining at least one recommended value of the initial rate of climb (V2) of said aircraft, such that at least the following regulatory safety criteria are respected during take-off: said recommended value of the initial rate of climb (V2) is at least equal to a first predefined speed threshold which is a function of the stalling speed of said aircraft;said recommended value of the initial rate of climb (V2) is at least equal to a second predefined speed threshold which is a function of the minimum control speed with a breakdown engine;the minimum gradient of climb of said aircraft with a breakdown engine is at least equal to a predefined gradient threshold; andmeans (3) for selecting, among said separate predetermined positions (P1, P2, P3), a take-off position to be applied to said control surfaces (S1-Sn); andmeans (A1-An) for applying said selected take-off position to said control surfaces (S1-Sn),wherein: said system (1) further comprises: means (4) for checking, using a theoretical representation (C1, C2, C3) of the variations of the take-off mass (M) of said aircraft according to the initial rate of climb (V2) thereof, combined with said selected take-off position (P1, P2, P3), whether the safety criterion relating to said minimum rate of climb with a breakdown engine is predominant with respect to the other safety criteria; andmeans (6) for comparing a predefined value of the initial rate of climb (V2) with said first speed threshold, in the case where the minimum gradient of climb with a breakdown engine is a predominant safety criterion; andmeans (7) for determining, when the deviation between the predefined value of the initial rate of climb (V2) and said first speed threshold is substantially different from zero, optimised deflection commands of said control surfaces (S1-Sn) which define an optimised take-off position (Popt), such as to reduce said deviation upon take-off, these optimised deflection commands being such that they generate an optimised deflection of said control surfaces (S1-Sn) less than that of said selected take-off position;and said application means (A1-An) are further formed for applying the optimised deflection commands thus determined to said control surfaces (S1-Sn), whatever said previously selected take-off position. 8. An aircraft, comprising a system (1) as specified under claim 7.
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이 특허에 인용된 특허 (4)
Pitard, Fabien; Demortier, Jean-Pierre; Laporte, Serge; Boyer, Serge; Deret, Bernard; Fonteneau, Laurent, Method for checking takeoff or landing parameters, and associated device.
Chatrenet, Dominique; Mathieu, Gerard; Alonso, Fernando; Cart-Lamy, Martine, System for automatically controlling lift-augmentation devices of an aircraft during take-off.
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