Purpose

This paper aims to study the attitude control problem with mutating orbital rate and actuator fading.

Design/methodology/approach

To avoid malicious physical attacks and hide itself, the spacecraft may irregularly switch its orbit altitude within a specific range, which will bring about variations in orbital rate, thereby causing mutations in the attitude dynamics model. The actuator faults will also cause changes in system dynamics. Both factors affect the control performance. First, this paper determines the potential switching orbits. Then under different conditions, design controllers that can accommodate actuator faults according to the statistical law of actuator fading.

Findings

This paper, to the best of the authors’ knowledge, for the first time, introduces the Markovian jump framework to model the possible unexpected mutating of orbital rate and actuator fading of spacecraft and then designs a novel control policy to solve the attitude control problem.

Practical implications

This paper also provides the algorithm design processes in detail. A comparative numerical simulation is given to verify the effectiveness of the proposed algorithm.

Originality/value

This is an early solution for spacecraft attitude control with dynamics model mutations.

中文翻译：

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马尔可夫跳跃框架下具有变异轨道速率和执行器衰减的航天器姿态控制

目的

本文旨在研究具有变异轨道速率和致动器衰落的姿态控制问题。

设计/方法/方法

为了避免恶意物理攻击和隐藏自身，航天器可能会在特定范围内不规则地切换轨道高度，这会带来轨道速率的变化，从而导致姿态动力学模型的突变。执行器故障也会引起系统动态的变化。这两个因素都会影响控制性能。首先，本文确定了潜在的转换轨道。然后在不同的条件下，根据执行器衰落的统计规律设计出能够适应执行器故障的控制器。

发现

本文据作者所知，首次引入马尔可夫跳跃框架来模拟可能的轨道速率意外突变和航天器执行器衰落，然后设计一种新的控制策略来解决姿态控制问题。

实际影响

本文还详细提供了算法设计过程。通过数值仿真对比验证了所提算法的有效性。

原创性/价值

这是具有动力学模型突变的航天器姿态控制的早期解决方案。