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METHOD OF LIGHT-SAIL SPACECRAFT REORIENTATION AND THRUST CONTROL

机译：轻型航天器改向和推力控制的方法

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1. The method of adjusting and controlling the thrust of rotating spacecraft with solar sail,1. Change the orientation of spacecraft with solar sail by changing the rotation parameters of spacecraft;DifferBy means of time, the initial stable rotation of the spacecraft and the thrust vector of the solar sail change in the direction of the required angle lossWhen adjusting the direction of the instantaneous rotation axis to the required relative starting angle positionThe reason for the loss of stability is that the ratio of the three main moments of inertia of the spacecraft to the three main moments of inertia of the solar sail has a controllable change. Oblique axis(a) An axis matching the basic stable rotation axis of the spacecraft;And in order to lose the stability of the instantaneous rotation axisThe initial stable rotation time and control of spacecraft make the mean moment of inertia between the three main moments of inertia become a stable starting point.A / when the spacecraft is reoriented to the desired angle to restore stability, the specified primary moment of inertia again reaches the maximum of the three values. Main moment of inertiaMoreover, the change of the moment of inertia is realized by adjusting the mass of the instrument to adapt to the corresponding radial axis;
机译：1.用太阳帆调节和控制旋转航天器推力的方法，1。通过更改航天器的旋转参数来更改带有太阳帆的航天器的方向;通过时间的不同，航天器的初始稳定旋转和太阳帆的推力矢量会在所需角度损失的方向上发生变化。瞬时旋转轴到所需的相对起始角度位置的原因失去稳定性的原因是，航天器的三个主要惯性矩与太阳帆的三个主要惯性矩之比具有可控的变化。倾斜轴（a）与航天器基本稳定旋转轴匹配的轴;并且为了失去瞬时旋转轴的稳定性初始稳定旋转时间和航天器的控制使三个主要惯性矩之间的平均惯性矩当航天器重新定向到所需角度以恢复稳定性时，指定的主惯性矩再次达到三个值中的最大值。主惯性矩此外，通过调节仪器的质量以适应相应的径向轴，可以实现惯性矩的变化。

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