IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0565827
(2009-09-24)
|
등록번호 |
US-8162264
(2012-04-24)
|
우선권정보 |
FR-08 05298 (2008-09-26) |
발명자
/ 주소 |
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출원인 / 주소 |
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대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
6 |
초록
▼
The present invention relates to a method and an associated device for automatically jettisoning an external load (4) that is reversibly suspended from a release-hook (12) of an aircraft fuselage (2) by a sling (13), which method comprises: measuring the angle (θ) between said sling (13) and a verti
The present invention relates to a method and an associated device for automatically jettisoning an external load (4) that is reversibly suspended from a release-hook (12) of an aircraft fuselage (2) by a sling (13), which method comprises: measuring the angle (θ) between said sling (13) and a vertical axis in elevation of the aircraft; andactivating automatic jettisoning when firstly said angle (θ) exceeds an upper limit (LSUP), and secondly said sling (13) is directed towards the rear (4′) of the aircraft, thereby making it possible, optionally, to proceed with jettisoning said external load (4).
대표청구항
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1. A method of automatically jettisoning an external load (4) suspended reversibly from a release-hook (12) of an aircraft fuselage (2) by means of a sling (13) liable to extend at an angle (θ) of varying magnitude relative to a vertical axis in elevation (AX) of the aircraft (1) parallel to the yaw
1. A method of automatically jettisoning an external load (4) suspended reversibly from a release-hook (12) of an aircraft fuselage (2) by means of a sling (13) liable to extend at an angle (θ) of varying magnitude relative to a vertical axis in elevation (AX) of the aircraft (1) parallel to the yaw axis (Z) of the aircraft (1) and passing via a connection point (100) connecting support means (11) for the release-hook (12) to the fuselage (2) of the aircraft (1), the method comprising: measuring said angle (θ); andactivating automatic jettisoning when firstly said angle (θ) exceeds an upper bound (BSUP), and secondly said sling (13) is directed towards the rear (4′) of the aircraft thereby making it possible, optionally, to proceed with jettisoning said external load (4). 2. A method according to claim 1, wherein, when said angle (θ) lies between a lower bound (BINF) and said upper bound (BSUP), a first alarm is triggered. 3. A method according to claim 1, wherein a first value (V1) is determined for a quotient (Q) of a tension (T) exerted on the sling (13) as divided by an evaluation term (N) that depends on a load factor (n) of said fuselage (2) along and a gravity axis (P), and a second value (V2) is determined for the time derivative (ⅆQⅆt) of said quotient (Q). 4. A method according to claim 3, wherein said evaluation term (N) is equal to said load factor (n). 5. A method according to claim 3, wherein said evaluation term (N) is equal to the product of said load factor (n) multiplied by an acceleration due to gravity (g). 6. A method according to claim 3, wherein a second alarm is triggered when firstly automatic jettisoning is not activated as a result of said angle (θ), and when secondly said first and second values (V1, V2) reach respective predetermined levels. 7. A method according to claim 3, wherein automatic jettisoning is triggered by ordering said release-hook (12) to release said sling (13) when firstly automatic jettisoning is activated as a result of said angle (θ), and when secondly said first and second values (V1, V2) reach respective predetermined levels. 8. A method according to claim 3, wherein automatic jettisoning is triggered by ordering the release-hook (12) to release said sling (13) when firstly automatic jettisoning is activated as a result of said angle (θ), and when secondly said first value (V1) exceeds an upper limit (LSUP), independently of the value of said second value (V2). 9. A method according to claim 3, wherein automatic jettisoning is triggered by ordering the release-hook (12) to release said sling (13) when firstly automatic jettisoning is activated as a result of said angle (θ), and secondly said first value (V1) lies between a lower limit (LINF) and an upper limit (LSUP) and said second value (V2) exceeds a threshold (S). 10. An aircraft (1) provided with an attachment device (10) for attaching an external load (4) to a fuselage (2) of the aircraft (1), said attachment device (10) being provided with a release-hook (12), with support means (11), and with a sling (13), said the release-hook (12) being fastened to an attachment point (100) for attaching to the fuselage (2) by the support means (11), said sling (13) being secured reversibly to said the release-hook (12) and being liable to extend at an angle (θ) relative to a vertical axis in elevation (AX) of the aircraft parallel to a yaw axis (Z) of the aircraft (1) and passing via an attachment point (100) for attaching said support means (11) for the release-hook (12) to the fuselage (2) of the aircraft, wherein the aircraft includes measurement means (30) for determining said angle (θ), and a processor unit (20) connected to said release-hook (12) and to said measurement means (30), said processor unit (20) being suitable for receiving a first signal (S1) from the measurement means (30) relating to said angle and to the position of the sling, so as to implement the automatic jettisoning method according to claim 1. 11. An aircraft according to claim 10, wherein said measurement means (30) are provided with an arch (31) arranged on said support means (11) and with a sensor (32, 33) suitable for being arranged on said fuselage (2). 12. An aircraft according to claim 11, wherein said sensor is provided with a movable paddle (32) and with an angle sensor (23) for determining the position of said paddle (32). 13. An aircraft according to claim 10, wherein said attachment device comprises a load cell (22) arranged on said support means (11), said load cell (22) being connected to said processor unit (20) to send thereto a second signal (S2) relating to the tension (T) of said sling (13). 14. An aircraft according to claim 10, wherein said attachment device (10) includes an accelerometer (21) connected to said processor unit (20) to send thereto a first signal (S3) relating to the accelerations to which said fuselage (2) is subjected so as to enable the processor unit (20) to determine a first value of (V1) for a quotient (Q) of the tension (T) exerted on the sling (13) as divided by an evaluation term the depends on the load factor (n) of said fuselage (2) along the gravity axis (P), and a second value (V2) for the time derivative (ⅆQⅆt) of said quotient (Q). 15. An aircraft according to claim 10, wherein said attachment device (10) includes a display unit (40) controlled by the processor unit (20) to display alarms and/or information relating to the attachment operation. 16. An aircraft according to claim 10, wherein said attachment device (10) includes manual control means (50) for controlling the release-hook (12).
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