A data validity identification method for spacecraft control system

A data validity and control system technology, applied in the general control system, control/regulation system, test/monitoring control system, etc., can solve the threat to the safety of the entire star structure and energy security, the long-term effect of wrong data, and the inability to satisfy users Requirements and other issues, to achieve the effect of ensuring closed-loop performance indicators, strong versatility, and practical methods

Active Publication Date: 2021-07-13
BEIJING INST OF CONTROL ENG
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

The unreasonable introduction of invalid, erroneous, and illegal data may lead to a decline in control performance, fail to meet user needs, and cause load work interruption. The long-term effect of erroneous data may even lead to control divergence, which threatens the structural safety and energy security of the entire star.

Method used

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  • A data validity identification method for spacecraft control system
  • A data validity identification method for spacecraft control system

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Embodiment

[0037] Taking a typical spacecraft control system as an example, it is assumed that the spacecraft control system is configured with 2 star sensors, 3 front-mounted gyroscopes + 1 oblique-mounted gyroscope, and 4 momentum wheels in a pyramid configuration. The star sensor and gyroscope are used as the attitude measurement sensor, and the momentum wheel is used as the attitude control actuator. The orbit calculation method on the satellite adopts the analytical orbit fitting method based on the 6-element number of the orbit. External system time calibration includes whole satellite time system time calibration, GPS / GNSS receiver time calibration, payload clock time calibration, ground time calibration, etc. Set the measurement data of star sensor B to slowly drift, and according to the present invention, the data validity of the spacecraft control system is identified, and the steps are as follows:

[0038] (1) According to the data usage sequence of the control system, first ...

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Abstract

The invention belongs to the technical field of stable operation of a spacecraft control system, and relates to a data validity identification method of a spacecraft control system. The data validity identification design method of the spacecraft control system provided by the present invention can effectively identify and eliminate erroneous data, including the validity identification of the sensor measurement data, the validity identification of the actuator measurement data, and the ground injection orbit data. Validity identification, the validity identification of external system timing data, avoiding the introduction of error information into control calculations, ensuring the stable operation of spacecraft in orbit, ensuring closed-loop performance indicators, and providing stable and reliable operating conditions for payloads; the invention proposes The data validity judgment design method is intended to eliminate unexpected data and ensure the stable operation of the control system in real time. It is an important protection mechanism that must be possessed when the system has fault diagnosis and fault tolerance capabilities; The data characteristics are targeted, and at the same time, it reflects the ability of multi-source information fusion. The designed data validity identification method has good abstraction, strong versatility, and can avoid misjudgment and missed judgment.

Description

technical field [0001] The invention belongs to the technical field of stable operation of a spacecraft control system, and relates to a data validity identification method of a spacecraft control system. From the perspective of the stable operation of the spacecraft control system, this method proposes the basic design method and specific judgment criteria for the data validity judgment, including the validity recognition of the sensor measurement data, the validity recognition of the actuator measurement data, and the ground Injecting track data for validity identification and external system timing data for validity identification, the purpose is to ensure that there are effective means to prevent outliers, illegal data, wrong information, etc. from entering the system, affecting stable operation, and even causing safety risks. Background technique [0002] The spacecraft control system undertakes the attitude control and orbit control tasks of various high and low orbit ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B23/02
CPCG05B23/0221
Inventor 王淑一刘潇翔蒋庆华张万利刘羽白石恒苏晏
Owner BEIJING INST OF CONTROL ENG
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