Fin buzz system and method for assisting in unlocking a missile fin lock mechanism
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F42B-015/01
F42B-010/64
출원번호
US-0570280
(2012-08-09)
등록번호
US-8975566
(2015-03-10)
발명자
/ 주소
Black, Thomas A.
Reyes, David J.
Von Mayr, Robert W.
Fjerstad, Erik A.
Willems, John D.
출원인 / 주소
Raytheon Company
대리인 / 주소
Renner, Otto, Boisselle & Sklar, LLP
인용정보
피인용 횟수 :
0인용 특허 :
11
초록▼
By removing the aerodynamic fin forces from the fin lock mechanism, achieved by actuating the fin control system to apply a controlled force that counters the aerodynamic forces acting on the control fins, the system can reduce the transmission of aerodynamic forces onto the fin lock mechanism, whic
By removing the aerodynamic fin forces from the fin lock mechanism, achieved by actuating the fin control system to apply a controlled force that counters the aerodynamic forces acting on the control fins, the system can reduce the transmission of aerodynamic forces onto the fin lock mechanism, which makes the fin lock mechanism easier to unlock with less force. Accordingly, a method for unlocking a fin lock mechanism that releasably holds one or more missile control fins in a locked position, where the control fins are prevented from rotating, includes the steps of (i) applying an alternating positive and negative rotational force to a control fin; (ii) monitoring the position of the control fin during the applying step; and (iii) while the position of the control fin does not exceed a predetermined value, repeating the applying step for a predetermined number of times or for a predetermined period.
대표청구항▼
1. A method for unlocking a fin lock mechanism that releasably holds one or more missile control fins in a locked position where the control fins are prevented from rotating, the method comprising the steps of: initiating application of a force to rotate a missile control fin to a desired orientatio
1. A method for unlocking a fin lock mechanism that releasably holds one or more missile control fins in a locked position where the control fins are prevented from rotating, the method comprising the steps of: initiating application of a force to rotate a missile control fin to a desired orientation;detecting the failure of the control fin to rotate to the desired orientation;following foregoing initiating and detecting steps, applying an alternating positive and negative rotational force to the control fin;monitoring the position of the control fin during the applying step; anduntil the position of the control fin exceeds a predetermined value, repeating the applying step a predetermined number of times or for a predetermined period. 2. A method as set forth in claim 1, comprising the step of indicating a failure after the repeating step is complete and the position of the control fin has not exceeded the predetermined value. 3. A method as set forth in claim 1, where if during the monitoring step the position of the control fin exceeds the predetermined value, stopping the applying step. 4. A method as set forth in claim 1, where the predetermined value is approximately 0.83 degrees. 5. A method as set forth in claim 1, comprising the step of moving a piston to engage a control fin to prevent the control fin from rotating. 6. A method as set forth in claim 1, where the applying step includes outputting a predetermined signal profile with a predetermined amplitude. 7. A method as set forth in claim 6, where the outputting step includes outputting a signal profile that is a 50 Hz sine wave with an amplitude of 1.325 degrees. 8. A method as set forth in claim 1, where the repeating step occurs at least three times. 9. A method as set forth in claim 1, where the repeating step allows the applying step to apply rotational force to cause the control fin to rotate alternately no more than three times clockwise and no more than three times counterclockwise. 10. A method as set forth in claim 1, where the repeating step only occurs when the monitoring step detects rotation of the control fin of less than 0.83 degrees. 11. A method as set forth in claim 1, where the applying step includes outputting a signal to a motive device that is coupled to the control fin. 12. A method as set forth in claim 1, where the applying step includes applying a predetermined torque. 13. A method as set forth in claim 1, where after the monitoring step detects movement of the control fin in excess of the predetermined value, comprising the step of rotating the control fin to provide flight control using a torque that is greater than the torque applied during the applying step. 14. A method as set forth in claim 1, comprising the step of disengaging a locking device from connection to the control fin. 15. A system for assisting in unlocking a fin lock mechanism that releasably holds one or more missile control fins in a locked position where the control fins are prevented from rotating, the system comprising: a motor operatively connected to the control fin to selectively rotate the fin about a fin axis;a sensor capable of detecting the position of the control fin; anda controller in communication with the motor and the sensor, the controller being configured to generate a first motor control signal to rotate the control fin to a desired orientation;where, in response to a signal from the sensor indicating that the control fin did not rotate to the desired orientation in response to the first motor control signal, the controller being configured to generate a second motor control signal to direct the motor to directionally oscillate the control fin in opposing positive and negative directions until the control fin rotates more than a predetermined value or until the motor has applied a force to the control fin a predetermined number of times or for a predetermined time. 16. A system as set forth in claim 15, comprising a fin lock mechanism;a control shaft coupled to a control fin for controllably rotating the control fin about a fin axis;where the fin lock mechanism includes a locking piston that is axially movable along a piston axis transverse the fins axis;where the control shaft and the piston include corresponding features that cooperate to lock the control shaft to prevent the control fin from rotating; andwhere the controller generates the motor control signal to directionally oscillate the control shaft while attempting to unlock the control shaft by causing the locking piston to move axially, away from the control shaft, to minimize the force required to move the locking piston to unlock the control fin. 17. A system as set forth in claim 15, where the second control signal includes a series of sequential values corresponding to instructions to the motor to apply an alternating positive and negative rotational force to the control fin.
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이 특허에 인용된 특허 (11)
Steinmetz Harold F. (Ferguson MO) Wisdom Gerald H. (Florissant MO), Automatic fin deployment mechanism.
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