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Diagnostic determination method for spacecraft control system under influence of noise

A technology for controlling systems and determining methods, applied in the directions of instruments, electrical testing/monitoring, and special data processing applications, which can solve problems such as difficult diagnosability determination

Active Publication Date: 2015-04-29
BEIJING INST OF CONTROL ENG
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  • Abstract
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Problems solved by technology

However, this method is difficult to generalize and apply to the diagnosable determination of faults in dynamic systems such as spacecraft control systems and actuators

Method used

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  • Diagnostic determination method for spacecraft control system under influence of noise
  • Diagnostic determination method for spacecraft control system under influence of noise
  • Diagnostic determination method for spacecraft control system under influence of noise

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Embodiment

[0094] The spacecraft control system composed of an infrared earth sensor and a gyroscope is an example. The infrared earth sensor and gyroscope are used to measure the attitude angle and angular rate of the spacecraft respectively, and the combined use of the two can achieve high-precision combined attitude determination.

[0095] To simplify the problem description, only the discrete state space model of the y-axis of the spacecraft control system is given here:

[0096] θ ( k + 1 ) d y ( k ...

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Abstract

The invention provides a diagnostic determination method for a spacecraft control system under influence of noise. First, a multivariate probability distribution statistic model of the spacecraft control system is built through a standard model and an equivalent space method; then a detectability index is obtained; and fault detectability is determined; finally, an isolability index is obtained, and the fault isolability is determined. According to the diagnostic determination method, influence of process noise, observation noise and other interference factors on diagnostic performance are fully taken into consideration, fault diagnosis algorithms are not required to be designed, and the fault detectability and the isolability can be determined according to system information including kinetics, kinematics, a controller model and the like of the spacecraft control system and the configuration and installation condition of a sensor and an actuator, the fault diagnosis process of the spacecraft control system is simplified, meanwhile, a theoretical basis can be provided for design of a diagnosis algorithm, the design method of the spacecraft control system is optimized, and the controllability of the spacecraft control system is improved.

Description

technical field [0001] The invention relates to a method for determining the diagnosability of a spacecraft control system under the influence of noise, belonging to the field of spacecraft control. Background technique [0002] The control system is an important subsystem to realize the orbit and attitude control of the spacecraft and the drive of various components (such as solar wings, space-borne antennas, etc.). With the development of aerospace technology, the structure and function requirements of the spacecraft control system are becoming more and more complex. For the expensive spacecraft control system, high reliability is the most basic requirement. The function is reduced or lost, and in severe cases, it may even cause catastrophic accidents and huge economic losses. At present, the high reliability of the spacecraft control system is generally guaranteed by the high reliability and redundancy of software / hardware. However, due to objective factors such as the ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B23/02G06F19/00
CPCG05B23/02G16Z99/00
Inventor 王大轶李文博刘成瑞邢琰何英姿
Owner BEIJING INST OF CONTROL ENG
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