Task constraint-based spacecraft attitude control system on-orbit reconstruction method

Abstract

The invention discloses a task constraint-based spacecraft attitude control system on-orbit reconstruction method and belongs to the technical field of reconstruction of a spacecraft attitude controlsystem. Task constraint conditions are introduced into design of a utility function and a performance index function, iteration control rules of an HJB (Hamilton-Jacobian-Bellman) equation are determined on the basis of the utility function and the performance index function, and a neural network is trained in an ADP (Adaptive Dynamic Programming) framework to conduct fitting of a target functionunder the iteration control rules and then to determine an optimal reconstruction strategy. In the case of faults, the optimal reconstruction strategy ensuring that set tasks can be carried out as successfully as possible is adopted, and task completion capabilities and fault handling capabilities of a spacecraft are improved.

Description

technical field [0001] The invention discloses a mission-constrained spacecraft attitude control system on-orbit reconfiguration method, belonging to the technical field of spacecraft attitude control system reconfiguration. Background technique [0002] Once an in-orbit spacecraft fails, even if it is only a few minutes or ten minutes, it may lead to the failure of the entire mission. Since the spacecraft is far away from the ground, faults are often not handled by ground measurement and control personnel in a timely manner. The spacecraft should have the ability to autonomously reconfigure on-orbit. The current system reconfiguration methods mainly focus on the design of fault-tolerant controllers, and achieve system stability after faults through active fault-tolerant or passive fault-tolerant methods. However, active fault-tolerant or passive fault-tolerant methods do not consider task constraints. The system cannot guarantee that the task execution requirements will be...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the invention of the present invention is to address the deficiencies of the above-mentioned background technology, and to provide a method for on-orbit reconfiguration of the spacecraft attitude control system oriented to mission constraints, which incorporates mission constraints into the design of utility functions and performance index functions. Make optimal reconfiguration decisions to ensure the smooth execution of established tasks as much as possible, and solve the technical problem that the reconfigured control system of existing reconfiguration methods cannot guarantee to meet the requirements of task execution

Images