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The Coupled Orbit-Attitude Dynamics and Control of Electric Sail in Displaced Solar Orbits

机译:位移太阳轨道中电帆的轨道-姿态耦合动力学和控制

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摘要

Displaced solar orbits for spacecraft propelled by electric sails are investigated. Since the propulsive thrust is induced by the sail attitude, the orbital and attitude dynamics of electric-sail-based spacecraft are coupled and required to be investigated together. However, the coupled dynamics and control of electric sails have not been discussed in most published literatures. In this paper, the equilibrium point of the coupled dynamical system in displaced orbit is obtained, and its stability is analyzed through a linearization. The results of stability analysis show that only some of the orbits are marginally stable. For unstable displaced orbits, linear quadratic regulator is employed to control the coupled attitude-orbit system. Numerical simulations show that the proposed strategy can control the coupled system and a small torque can stabilize both the attitude and orbit. In order to generate the control force and torque, the voltage distribution problem is studied in an optimal framework. The numerical results show that the control force and torque of electric sail can be realized by adjusting the voltage distribution of charged tethers.
机译:研究了由电动帆推动的航天器的位移太阳轨道。由于推进力是由航行姿态引起的,因此基于电帆的航天器的轨道和姿态动力学是耦合的,需要一起研究。但是,在大多数已发表的文献中尚未讨论电动帆的动力学和控制的耦合。本文获得了在位移轨道上耦合动力系统的平衡点,并通过线性化对其稳定性进行了分析。稳定性分析的结果表明,只有部分轨道是边缘稳定的。对于不稳定的位移轨道,采用线性二次调节器来控制耦合的姿态轨道系统。数值仿真表明,所提出的策略可以控制耦合系统,较小的转矩可以稳定姿态和轨道。为了产生控制力和转矩,在最佳框架下研究了电压分布问题。数值结果表明,通过调节带电绳的电压分布,可以实现电动帆的控制力和转矩。

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  • 来源
    《International journal of aerospace engineering》 |2017年第2期|3812397.1-3812397.12|共12页
  • 作者单位

    Harbin Inst Technol, Dept Aerosp Engn, Harbin 150001, Heilongjiang, Peoples R China;

    Shanghai Satellite Engn Res Inst, Shanghai 200240, Peoples R China;

    Harbin Inst Technol, Dept Aerosp Engn, Harbin 150001, Heilongjiang, Peoples R China;

    Harbin Inst Technol, Dept Aerosp Engn, Harbin 150001, Heilongjiang, Peoples R China;

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