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首页> 外文期刊>Journal of guidance, control, and dynamics >Recovering Linear Controllability of an Underactuated Spacecraft by Exploiting Solar Radiation Pressure
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Recovering Linear Controllability of an Underactuated Spacecraft by Exploiting Solar Radiation Pressure

机译：利用太阳辐射压力恢复欠驱动航天器的线性可控性

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摘要

This paper describes a method for recovering linear controllability for the attitude of an underactuated spacecraft by accounting for the effects of solar radiation pressure in the spacecraft attitude model. The developments are based on a spacecraft model that has at least two functional reaction wheels. A solar radiation pressure torque model that is a function of spacecraft attitude is incorporated and, under suitable assumptions, can be simplified for spacecraft with body symmetry. Conditions are given under which a symmetric-body spacecraft will experience zero solar radiation pressure torque. The stability of the underactuated spacecraft model is discussed, and necessary and sufficient conditions are given for linear controllability to be regained when solar radiation pressure torques are included in the spacecraft attitude model. With linear controllability restored, conventional controllers can be designed for under-actuated spacecraft Controllability of a cuboid spacecraft under the influence of solar radiation pressure is then analyzed. Nonlinear simulations illustrate this novel approach to recover pointing by controlling two functioning reaction wheels while two other wheels undergo subsequent failures.
机译：本文介绍了一种通过考虑航天器姿态模型中太阳辐射压力的影响来恢复欠驱动航天器姿态的线性可控制性的方法。这些开发基于具有至少两个功能反作用轮的航天器模型。引入了与航天器姿态有关的太阳辐射压力转矩模型，在适当的假设下，可以简化具有身体对称性的航天器的模型。给出了对称物体航天器将经历零太阳辐射压力扭矩的条件。讨论了欠驱动航天器模型的稳定性，并给出了在航天器姿态模型中包括太阳辐射压力转矩时要恢复线性可控性的必要和充分条件。恢复线性可控性后，可以为欠驱动航天器设计常规控制器，然后分析太阳辐射压力影响下的长方体航天器的可控性。非线性仿真说明了这种新颖的方法，可以通过控制两个正常工作的反作用轮来恢复指向，而另外两个反作用轮则随后发生故障。

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