A SHA-Based Method for Lifetime Prediction of Spacecraft ACS Missions

A life prediction and spacecraft technology, applied in the direction of instruments, simulators, control/regulation systems, etc., can solve problems such as mission life termination, system performance degradation, and inability to reflect dynamic interaction between components and systems, so as to overcome difficulties in obtaining and avoiding The effect of incomplete information

Active Publication Date: 2020-07-24
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

For a system composed of multiple components, the sudden functional failure of the component will lead to the sudden functional failure of the system, the performance degradation of the component will lead to the performance degradation of the system, and the functional failure and performance degradation of the system will lead to the termination of the mission life
Traditional prediction methods consider a single perspective and cannot reflect the dynamic interaction between components and systems, so it is difficult to obtain accurate system mission life prediction results

Method used

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  • A SHA-Based Method for Lifetime Prediction of Spacecraft ACS Missions
  • A SHA-Based Method for Lifetime Prediction of Spacecraft ACS Missions
  • A SHA-Based Method for Lifetime Prediction of Spacecraft ACS Missions

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Embodiment Construction

[0023] The technical solution of the invention will be described in detail below in conjunction with the accompanying drawings.

[0024] figure 1 The shown mission life prediction method for spacecraft attitude control system based on stochastic hybrid automata is implemented by a system including: SHA module, on-orbit environment temperature prediction module, similarity module, calculation & statistical analysis module. The similarity module processes the information of the historical spacecraft through the similarity algorithm to obtain the component on-orbit reliability model of the current spacecraft; establishes the component SHA according to the component performance degradation model and the component reliability model obtained in the previous module, and then combines DFT to obtain the The subsystem SHA consists of the SHA module, which is used to simulate the random mixed movement of the spacecraft subsystems in orbit; according to the historical time series of the t...

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Abstract

The invention discloses an SHA-based spacecraft ACS mission life prediction method and belongs to the technical field of spacecraft attitude control. The method carries out life prediction based on astochastic hybrid automaton, and simulates stochastic hybrid motion of a spacecraft ACS during in-orbit operation, and the lift predication result is not only based on system reliability, but also takes constraint of system performance degradation on life into consideration, so that the limitation that a traditional life prediction method can only predict the life from the perspective of reliability is overcome, and the predicted result is more in line with requirements of space missions.

Description

technical field [0001] The invention discloses an SHA (Stochastic Hybrid Automaton, random hybrid automaton) spacecraft ACS (ACS, attitude control system) mission life prediction method, which belongs to the technical field of spacecraft attitude control. Background technique [0002] Stochastic Hybrid System (SHS) theory can describe a complex system composed of continuous (or discrete) time variables, discrete event variables and random factors. It is an emerging technology in the field of reliability and control in recent years. Stochastic Hybrid Automata is the most classic model in the method of analyzing SHS. SHA uses discrete state transition diagrams to reflect the various states that exist in the system during actual operation, and considers deterministic transitions between states (such as external input) and non-deterministic transitions (such as random faults); described by stochastic differential equations Changes in performance parameters; unify continuous and...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B17/02
CPCG05B17/02
Inventor 程月华蒋亮姜斌陆宁云汪志军
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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