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A Reconfigurability Envelope Determination Method for Constrained Systems in Restorable State Domain

A technology for restoring the state and determining the method, applied in the space field, it can solve the problems of not fully considering the time, large amount of calculation, difficult to achieve on-orbit, etc.

Active Publication Date: 2020-10-23
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

[0003] At present, the most common method for determining the reconfigurability envelope based on the controllable Graham matrix mainly has the following two shortcomings: 1) The impact of energy constraints on system reconfigurability is only considered in the form of a constant threshold, and there is no Fully consider other constraints such as time; 2) In the process of calculating the reconfigurable envelope, the Lyapunov equation needs to be solved, and there is a singularity problem, and the amount of calculation is large, so it is difficult to realize on-orbit

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  • A Reconfigurability Envelope Determination Method for Constrained Systems in Restorable State Domain
  • A Reconfigurability Envelope Determination Method for Constrained Systems in Restorable State Domain
  • A Reconfigurability Envelope Determination Method for Constrained Systems in Restorable State Domain

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Embodiment Construction

[0023] The present invention will be further explained and described below in conjunction with specific embodiments.

[0024] A method for determining the reconfigurability envelope of a restricted system with a restorable state domain includes the following steps:

[0025] S1. Establish a spacecraft system state space model with limited energy and time in the event of a spacecraft actuator failure;

[0026] S2, based on the state space model, mission requirements and safety requirements, set the minimum state envelope that the spacecraft can recover;

[0027] S3, based on the state space model, task requirements and safety requirements, determine the given energy E by solving the differential Lyapunov equation * With time constraints mis The reconfigurability envelope of the next system;

[0028] S4, by comparing the system reconfigurability envelope obtained by S3 with the minimum state envelope set by S2, determine whether the system is reconfigurable; if the system is not reconfigur...

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Abstract

A method for determining the reconfigurability envelope of a constrained system in a recoverable state domain belongs to the field of space technology. Through theoretical analysis and simulation verification, the present invention can give the maximum reconfigurability envelope of the spacecraft system under the constraint conditions of time and energy, realize the quantitative analysis of reconfigurability for the limited system, and can be used for optimization The spacecraft system configuration and fault-tolerant control algorithm realize the on-orbit monitoring of the health status of the spacecraft system and the autonomous processing of faults, and improve the autonomous reconfiguration capability of the spacecraft system. Compared with the existing methods, the patent of the present invention uses the fine integral algorithm to solve the reconfigurability envelope of the spacecraft system, which has the advantages of high precision, small amount of calculation, and easy implementation, and has sufficient flexibility and flexibility in practical applications. applicability.

Description

Technical field [0001] The invention relates to a method for determining the reconfigurability envelope of a restricted system of a recoverable state domain, and belongs to the field of space technology. Background technique [0002] The maximum reconstruction potential of a spacecraft with limited resources is a problem that engineers and technicians are very concerned about. In the actual operation process, the spacecraft is affected by multiple constraints, the most representative of which is the energy and time constraints. As the power generation capacity of solar panels and the carrying capacity of propellants are severely limited, energy consumption constraints are a key factor affecting the reconfiguration of spacecraft systems. In addition, many specific tasks need to be completed within the specified time. After the system fails, in order to continue to complete such tasks, the system must be rebuilt within a certain time window. The smaller the window, the time redund...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G99/00
CPCB64G99/00
Inventor 王大轶屠园园李文博刘成瑞张香燕赵小宇林海淼
Owner BEIJING INST OF SPACECRAFT SYST ENG
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