摘要
针对由有效载荷、太阳帆和4个控制叶片所组成的太阳帆航天器系统,从物理模型出发,利用欧拉方程建立了姿态动力学模型,并通过数值仿真对太阳帆航天器基于控制叶片的对日定向性能进行了研究。研究结果表明,在行星际飞行中太阳帆航天器可以通过使控制叶片保持偏置来保持姿态稳定。
A solar sail spacecraft which is composed of four parts-sail film, structural booms, and payload mass, control vanes was studied. Dynamic model of the solar sail spacecraft was established using the Euler equation. Then, the nonlinear rotation system was run through a series of simulations to characterize the behavior of passive attitude control using control vanes and determine the effectiveness of attitude controlling. Results of simulations showed that the solar sail spacecraft could be stable in the present of passive control by control vanes in the future deep space exploration mission.
出处
《飞行力学》
CSCD
北大核心
2008年第5期47-50,共4页
Flight Dynamics
基金
国家863计划资助项目(2005AA737071)
关键词
动力学建模
姿态控制
太阳帆航天器
控制叶片
dynamics modeling
attitude control
solar sail spacecraft
control vane
