[특허]Anti-crash method and system, an undercarriage, and an aircraft

Eurocopter

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특허 상세정보

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Anti-crash method and system, an undercarriage, and an aircraft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-025/00 B64C-025/52 B64C-025/60
미국특허분류(USC)	244/100.R; 244/102.R; 244/102.A; 244/139
출원번호	UP-0429255 (2006-05-08)
등록번호	US-7575193 (2009-08-31)
우선권정보	FR-05 04746(2005-05-12)
발명자 / 주소	Payen, Herve Malfuson, Vincent
출원인 / 주소	Eurocopter
대리인 / 주소	Young & Thompson
인용정보	피인용 횟수 : 5 인용 특허 : 6

초록

An undercarriage (2) for an aircraft (1) includes anti-crash elements that are specific to a second stage of a crash after the end of a first stage. The undercarriage includes: a device for blocking a retraction actuator (6); a device for retaining the actuator (6) functionally separated from a landing gear leg (9); and a device for applying controlled braking to the pivoting of the leg (9) by irreversible lengthening of a deformable member (25).

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What is claimed is: 1. An on-board anti-crash method for an undercarriage (2) of an aircraft (1), said undercarriage (2) being of the retractable type, and comprises: a landing gear leg (9) hinged to a force take-up structure of the aircraft (1) about a transverse pivot axis (8) in order to enable it to be extended and retracted; a retraction actuator (6) having a coupling end hinged to the take-up structure in order to cause the landing gear leg (9) to be extended and retracted; first anti-crash means for acting during a first stage of a crash to damp shortening of the undercarriage (2); and second anti-crash means (16) for acting during a second stage of a crash to inhibit retraction and to brake pivoting of the leg (9); wherein, during a second stage of a crash, after the end of the first stage, the method comprises: functionally separating the landing gear leg (9) relative to the retraction actuator (6); retaining and blocking the retraction actuator (6); and once the actuator (6) has been blocked, providing controlled braking of the pivoting of the landing gear leg (9) about its transverse pivot axis (8), wherein the step of braking pivoting is performed at least in part by a stage of irreversibly lengthening of a deformable connection (14, 19, 25) between the take-up structure (5) and the landing gear leg (9) at a constant force, the lengthening stage is performed at least in part by a stage of extending by partial destruction a nonpermanent connection (14, 25, 27) between the take-up structure (5) and the leg (9), wherein said connection (14) being obtained by causing a member (25, 31) of said connection (14) to become engaged prior to the second stage of a crash, and said connection (14) is caused to become engaged prior to the second stage of a crash by a sliding tube (12) of the landing gear leg (9) being caused to engage with a collar (31) or the like. 2. The method according to claim 1, wherein the lengthening stage is performed at least in part by at least one partial destruction action (27) enabling the deformable connection (14, 25) to extend in controlled manner, wherein said connection (14) between the take-up structure (5) and the landing gear leg (9) is direct. 3. The method according to claim 1, wherein the lengthening stage is performed at least in part by at least one plastic deformation action enabling the deformable connection (14, 19) to be deployed in controlled manner, wherein said connection (14) between the take-up structure (5) and the landing gear leg (9) is indirect, and including a force-relay function (6) between the structure (5) and the leg (9) 4. The method according to claim 1, wherein the lengthening stage is performed at least in part by a stage of deploying a permanent connection (14, 19) between the structure (5) and the leg (9), wherein said connection (14) actuates tilting between the landing gear leg (9) and the retraction actuator (6), said actuator (6) remaining hinged to the leg (9) during the second stage of a crash. 5. The method according to claim 1, wherein the steps of retaining the actuator (6) in an out-of-the-way position and of applying controlled braking to the landing gear leg (9) are performed simultaneously, at least in part, or indeed together in parallel. 6. The method according to claim 1, wherein the functional separation of the landing gear leg (9) relative to the retraction actuator (6) is performed by separation proper by means of a shear bolt which, once sheared by the leg (9) shortening, releases a mechanism for retaining the actuator (6) in its functional position so that a connection end (23) of the actuator (6) is detached from the leg (9). 7. The method according to claim 1, wherein the functional separation of the landing gear leg (9) relative to the retraction actuator (6) is performed by tilting the connection (14, 19) which is permanent and indirect, a shear bolt, which, once sheared by the leg (9) shortening, releases a mechanism for retaining the actuator (6) in its functional position so that a connection end (23) of the actuator (6) is released relative to the leg (9), while a stationary hinge (22) enables the connection (14, 19) to tilt to a position in which the connection end (23) and the stationary end (22) of the actuator (6) are in alignment with an attachment zone (24) where the permanent connection (19) is attached to the leg (9). 8. The method according to claim 1, wherein the leg (9) is allowed to pivot freely prior to braking through a predetermined amplitude (E) lying in the range 1° to 30°, when the total amplitude of pivoting movement of the leg (9) is about 90°. 9. A method according to claim 8, wherein the range is about 9° to about 22°. 10. A method according to claim 8, wherein the range is about 9°. 11. A method according to claim 8, wherein the range is about 22°. 12. An on-board anti-crash method for an undercarriage (2) of an aircraft (1), said undercarriage (2) being of the retractable type, and comprises: a landing gear leg (9) hinged to a force take-up structure of the aircraft (1) about a transverse pivot axis (8) in order to enable it to be extended and retracted; a retraction actuator (6) having a coupling end hinged to the take-up structure in order to cause the landing gear leg (9) to be extended and retracted; first anti-crash means for acting during a first stage of a crash to damp shortening of the undercarriage (2); and second anti-crash means (16) for acting during a second stage of a crash to inhibit retraction and to brake pivoting of the leg (9); wherein, during a second stage of a crash, after the end of the first stage, the method comprises: functionally separating the landing gear leg (9) relative to the retraction actuator (6); retaining and blocking the retraction actuator (6); and once the actuator (6) has been blocked, providing controlled braking of the pivoting of the landing gear leg (9) about its transverse pivot axis (8), wherein the step of braking the leg (9) about the transverse axis (8) is provided in part by putting the leg (9) into contact with a stop (39) for absorbing energy of the crash during the second stage of a crash, followed by the stop being deformed plastically by the leg (9), by means of a sliding top end tube (12) of the landing gear leg (9) deforming a stop that comprises a front wall (39) of a well (11) for receiving the landing gear (2) at the end of the second stage of a crash. 13. An onboard anti-crash method for an undercarriage (2) of an aircraft (1), said undercarriage (2) being of the retractable type, and comprises: a landing gear leg (9) hinged to a force take-up structure of the aircraft (1) about a transverse pivot axis (8) in order to enable it to be extended and retracted; a retraction actuator (6) having a coupling end hinged to the take-up structure in order to cause the landing gear leg (9) to be extended and retracted; first anti-crash means for acting during a first stage of a crash to damp shortening of the undercarriage (2); and second anti-crash means (16) for acting during a second stage of a crash to inhibit retraction and to brake pivoting of the leg (9) wherein, during a second stage of a crash, after the end of the first stage, the method comprises: functionally separating the landing gear leg (9) relative to the retraction actuator (6) retaining and blocking the retraction actuator (6); and once the actuator (6) has been blocked, providing controlled braking of the pivoting of the landing gear leg (9) about its transverse pivot axis (8), wherein, during the first stage of a crash, a top portion (12) of the landing gear leg (9) slides substantially upwards and strikes a releasable zone (37) in a top wall (38) of a well (11) for receiving the landing gear (2), and separates said zone (37) from the top wall (38), without significant absorption of energy.

이 특허에 인용된 특허 (6)

이 특허를 인용한 특허 피인용횟수: 5

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Anti-crash method and system, an undercarriage, and an aircraft

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Anti-crash method and system, an undercarriage, and an aircraft

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