Automatic re-initialization of resonant sensors in rocket and missile guidance systems
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G06F-011/07
G06F-011/30
F41G-009/00
G01C-019/00
F41G-007/36
출원번호
US-0378070
(2011-04-08)
등록번호
US-8563909
(2013-10-22)
국제출원번호
PCT/US2011/031657
(2011-04-08)
§371/§102 date
20120309
(20120309)
국제공개번호
WO2012/005786
(2012-01-12)
발명자
/ 주소
Janiak, Derek P.
Steenson, Jr., James H.
Schorr, David
Bartlett, Stephen W.
출원인 / 주소
BAE Systems Information and Electronic Systems Integration Inc.
대리인 / 주소
Long, Daniel J.
인용정보
피인용 횟수 :
1인용 특허 :
20
초록▼
An apparatus and method improves the fault tolerance of a rocket or missile guidance system which includes a resonant sensor. When improper initialization is detected, the resonant sensor is reinitialized, repeatedly if necessary, until normal operation is achieved. Improper initialization is detect
An apparatus and method improves the fault tolerance of a rocket or missile guidance system which includes a resonant sensor. When improper initialization is detected, the resonant sensor is reinitialized, repeatedly if necessary, until normal operation is achieved. Improper initialization is detected by comparing data from the guidance system with pre-specified physical limits to roll, pitch, yaw, and/or other features of the flight scenario. Embodiments can also detect a fault condition due to an error signal from a “Built-in-Test” (BIT) module. The initialization sequence initiated by the invention can be identical to the power-on sequence, or it can be a separate, reinitiating sequence. Subsequent resets are initiated as needed, for example until the burn of the rocket fuel and the associated vibrations have ceased and the resonant sensor has been successfully initialized.
대표청구항▼
1. An apparatus for improving a fault tolerance of a rocket or missile guidance system, the rocket or missile guidance system including a resonant sensor, the apparatus comprising: a fault detection module configured to receive guidance data originating from the resonant sensor, compare the guidance
1. An apparatus for improving a fault tolerance of a rocket or missile guidance system, the rocket or missile guidance system including a resonant sensor, the apparatus comprising: a fault detection module configured to receive guidance data originating from the resonant sensor, compare the guidance data with specified physical performance limits of the rocket or missile, determine if the guidance data exceeds the physical performance limits, and transmit a fault detection signal if the guidance data exceeds the physical performance limits; anda reset module configured to receive the fault detection signal from the fault detection module, the reset module being configured to initiate a reinitializing sequence which will reinitialize the resonant sensor when the fault detection signal is received from the fault detection module. 2. The apparatus of claim 1, further comprising a Built-In Test (BIT) module cooperative with the resonant sensor and configured to detect at least one failure modality of the resonant sensor, the BIT module being configured to transmit a BIT error signal if it detects at least one failure modality, the fault detection module being configured to receive the BIT error signal and to transmit the fault detection signal when it receives the BIT error signal. 3. The apparatus of claim 1, wherein the reinitializing sequence is substantially identical to a power-up initializing sequence which initializes the resonant sensor upon activation of the rocket or missile. 4. The apparatus of claim 1, further comprising a data output module cooperative with the resonant sensor and configured to receive the fault detection signal from the fault detection module, the data output module being configured to prevent the rocket or missile from acting upon the guidance data when the fault detection signal is received from the fault detection module. 5. The apparatus of claim 1, wherein the specified physical performance limits include at least one limit pertaining to roll of the rocket or missile. 6. The apparatus of claim 1, wherein the specified physical performance limits include at least one limit relating to pitch of the rocket or missile. 7. The apparatus of claim 1, wherein the specified physical performance limits include at least one limit relating to yaw of the rocket or missile. 8. A method for improving a fault tolerance of a rocket or missile guidance system, the rocket or missile guidance system including a resonant sensor, the method comprising: receiving guidance data from the guidance system;comparing the guidance data with specified physical performance limits of the rocket or missile;determining if the guidance data exceeds the physical performance limits; andif the guidance data exceeds the physical performance limits, initiating a reinitializing sequence which will reinitialize the resonant sensor. 9. The method of claim 8, further comprising: determining if a Built-In Test (BIT) module cooperative with the resonant sensor has detected improper operation of the resonant sensor; andinitiating the reinitializing sequence if the BIT has detected improper operation of the resonant sensor. 10. The method of claim 8, wherein the reinitializing sequence is substantially identical to a power-up initializing sequence which initializes the resonant sensor upon activation of the rocket or missile. 11. The method of claim 8, further comprising preventing the rocket or missile from acting upon the guidance data when the fault detection signal is received from the fault detection module. 12. The method of claim 8, wherein the specified physical performance limits include at least one limit pertaining to roll of the rocket or missile. 13. The method of claim 8, wherein the specified physical performance limits include at least one limit pertaining to pitch of the rocket or missile. 14. The method of claim 8, wherein the specified physical performance limits include at least one limit pertaining to yaw of the rocket or missile.
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이 특허에 인용된 특허 (20)
Alsenz Evert C. (Long Beach CA) Juptner William F. (Laguna Beach CA) Macy David F. (Mission Viejo CA), Angular rate sensor system.
Dare James M. (St. Charles MO) Farm Jerome A. (Richmond Heights MO) Mears Barry C. (Auburn IL), Self-initializing internal guidance system and method for a missile.
Wang Zhe,SGX ; Sridhar Uppili,SGX ; Lin Rong Ming,SGX ; Lim Mong King,SGX, Structural design for improving the sensitivity of a surface-micromachined vibratory gyroscope.
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