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Fault discrimination method under gyroscope double five-meter configuration

A fault identification and gyro technology, applied in the field of inertial navigation, can solve the problems of large system misjudgments and missed judgments, inability to effectively use redundant information, and limited fault adaptability, so as to avoid misjudgments and missed judgments.

Pending Publication Date: 2021-06-11
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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Problems solved by technology

[0003] The existing inertial group navigation cannot meet the requirements of reliable work in the case of second-degree and above single-meter-level faults, and cannot effectively use redundant information. The adaptability to faults is limited, and the probability of system misjudgment and missed judgment Big

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  • Fault discrimination method under gyroscope double five-meter configuration
  • Fault discrimination method under gyroscope double five-meter configuration
  • Fault discrimination method under gyroscope double five-meter configuration

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Embodiment Construction

[0051] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0052] figure 1 It is a schematic flow chart of the fault discrimination method of the gyro dual inertial group. Such as figure 1 As shown, the present invention provides a method for discriminating faults under the configuration of the gyro dual-five meter, the dual inertial group includes a first inertial group and a second inertial group, and the first inertial group and the second inertial group Each includes five Wx, Wy, Wz, Ws, Wt, wherei...

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Abstract

The invention relates to a fault discrimination method under gyroscope double five-meter configuration. The method comprises the following steps: S1, respectively carrying out fault meter consistency detection in a first inertial unit and a second inertial unit, and executing fault meter isolation operation; S2, judging whether the first inertial unit and the second inertial unit have the inertial unit of which the gyroscope has a second-degree fault or not; and S3, if the inertial unit with the gyroscope having the second-degree fault exists, executing a gyroscope fault judging and positioning method between the inertial units, and detecting whether the corresponding orthogonal table of the inertial unit with the gyroscope having the second-degree fault has a fault or not. According to the invention, redundant information can be effectively utilized, the requirement for reliable work under the condition of second-degree and higher-degree single-meter-level faults is met, the faults are detected to the maximum extent, and meanwhile misjudgment and missed judgment are avoided.

Description

technical field [0001] The invention relates to the technical field of inertial navigation, in particular to a method for discriminating faults under the configuration of gyro dual-five meters. Background technique [0002] In order to improve the reliability of the strapdown inertial group, the current effective way is to use the redundant technology. Manned launch vehicles need to meet higher reliability and safety requirements, so the redundancy scheme covers a higher degree of failure than other models, and it is necessary to ensure that the inertial set can work reliably under the condition of two or more failures. [0003] The existing inertial group navigation cannot meet the requirements of reliable work in the case of second-degree and above single-meter-level faults, and cannot effectively use redundant information. The adaptability to faults is limited, and the probability of system misjudgment and missed judgment Big. Contents of the invention [0004] The ma...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C25/00G01C21/16G01C21/20
CPCG01C25/005G01C21/16G01C21/20
Inventor 柴嘉薪施国兴
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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