摘要
为了使固体微型推力器阵列应用于微型卫星控制,须要解决推力器的布局设计以及推力器阵列设计问题。提出了一种以正六边形为基元的推力器阵列方法,研究了推力器阵列的特点及规律,进行了应用分析;研究了推力器阵列的最优布局方式,设计了一种基于解耦控制的推力器布局设计,分析了该布局下的冲量和冲量矩的包络面。以正六边形为基元的推力器阵列方式能够满足微型卫星姿轨控的需要,推力器分布规律性强,利于分配算法设计;采用正六面体方式的布局设计,其冲量和冲量矩包络面亦为正六面体。
In order to make solid propellant micro-thruster array more practical, a study of thruster lay- out and thruster array configuration design is required. A layout based on regular hexagon is designed and the characteristics and rules of the layout are studied. Thruster configuration based on decoupling control is designed and impulse and impulse moment envelope are studied. The layout with regular hexa gon as primitives can meet the spacecraft attitude and orbit control requirements, easily get the rules, and is favorable for allocation algorithm design. The impulse and the impulse moment envelope based on the hexahedral configuration are hexahedral as well.
出处
《航天器工程》
2012年第6期74-79,共6页
Spacecraft Engineering
关键词
微型卫星
固体微型推力器阵列
推力器阵列
布局设计
包络面
micro satellite
solid propellant micro-thruster array~ thruster array
configuration design
envelope
