双自旋人造卫星的姿态动力学方程和稳定性研究

把卫星视为刚体和半刚体研究其自旋稳定性虽然简单可行,但必须使自旋轴成为最大惯量主轴.而要把完成各种使命的卫星都设计成短粗状是不现实的,因此双自旋卫星的设想便应运而生.空间环境存在着许多不确定因素,由于姿态失稳而导致的事故也时有发生.本文在把卫星作为刚体和半刚体研究其自旋稳定性的基础上,考虑到耗能器在稳定性研究中的作用,建立了一个不失一般性的模型,推导了双自旋卫星的姿态动力学方程,并探讨了它的姿态稳定性的实现条件.即当阻尼器参数确定后,双自旋卫星姿态稳定取决于平台和转子的标称角速度。这一结果对进一步研究各种形状的卫星类航天器具有普遍意义.

Dynamic attitude equations and stability study of dual spinning satellites

Artificial satellites play a great role in many areas, such as national defense,communication,weather and remote sensing. It is important to design the perfect orbit according to a satellite's unique mission.There are many uncertain factors in space that will disturb its attitude such as flat rate of the earth and difference of gravitation field,influence of universal gravitation of the earth and the moon,change of atmosphere aerodynamics and light pressure of the sun.Many accidents result from instability of satellites. Therefore, it is important to study its orientability and stability in order to influence its working accuracy and service life. Based on stability study of dual spinning satellites regarded as rigid bodies or quasi rigid bodies and consideration of the role of the damper,a general model is established,and its dynamic attitude equations are deduced,and the necessary conditions for their attitude stability are obtained.After damper parameter is given,the stability of dual spinning satellites will lie on angular velocity of the flat floor and rotor.The results are useful to further studying various shapes of spacecrafts.