Method for determining reconfigurable envelope of limited system of recoverable state domain

Abstract

The invention discloses a method for determining a reconfigurable envelope of a limited system of a recoverable state domain, and belongs to the technical field of space. According to the invention, theoretical analysis and simulation verification are carried out, under the constraint conditions of time and energy, the maximum reconfigurable envelope of the spacecraft system is given, quantitativeanalysis of reconfigurability of a limited system is achieved, the method can be used for optimizing configuration of the spacecraft system and a fault-tolerant control algorithm, on-orbit monitoringof the health state of the spacecraft system and autonomous processing of faults are achieved, and the autonomous reconfiguration capacity of the spacecraft system is improved. Compared with an existing method, the method has the advantages that the spacecraft system reconfigurability envelope is solved through adoption of the fine integral algorithm, and the method is high in precision, small incalculated amount, easy to implement and the like and has enough flexibility and applicability in practical application.

Description

technical field [0001] The invention relates to a method for determining the reconfigurability envelope of a restricted system in a recoverable state domain, and belongs to the field of space technology. Background technique [0002] The maximum reconfiguration potential of a spacecraft under limited resources is a matter of great concern to engineers and technicians. In the actual operation process, the spacecraft is affected by multiple constraints, the most representative of which are energy and time constraints. Due to the severely limited power generation capacity and propellant carrying capacity of solar panels, energy consumption constraints are a key factor affecting the reconfigurability of spacecraft systems. In addition, many specific tasks need to be completed within a specified time. After a system failure, in order to continue to complete such predetermined tasks, the system must be reconfigured within a certain time window. The smaller the window, the more ti...

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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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