组合式航天器概念及构型变换最优脉冲控制  

Conceptual Design of Assembling Spacecraft and Optimal Impulse Control on Reconfiguration

作　　者：田爱平[1] 宝音贺西[2] 李俊峰[2] 

机构地区：[1]海军航空工程学院飞行器工程系,烟台264001 [2]清华大学航天航空学院,北京100084

出　　处：《航天控制》2013年第2期62-68,共7页Aerospace Control

摘　　要：为应对多种多样的不确定性对传统航天器的挑战,提出了一种更具灵活性、可靠性的组合式航天器概念。从模块化设计、标准化接口、运行模式、空间任务构型方面对此航天器概念进行描述。它在可维护性、规模可缩放性、可重构性等性能显著增强,特别是具有根据空间任务的不同而进行构型变换的能力。并从相对运动动力学方程出发,本文针对组合式航天器空间任务构型变换,设计了给定机动时间的、以燃料消耗最少为目标的最优脉冲控制方法,生成最优脉冲序列。仿真结果表明,最优脉冲控制方法是实现组合式航天器构型变换的一种有效途径。To deal with the challenge of the vast and diverse uncertainty to traditional spacecraft system, a new spacecraft concept nameed the assembling spacecraft, which has more reliability and more flexibility, is proposed. The assembling spacecraft concept is mainly described by modularization design, standard interface, running model and space mission configurations. The maintainability, scalability and reconfigurability are the essential manifestations of new-style spacecraft system flexibility. Especially, the reconfigurability is prerequisite, which guarantees to perform all kinds of complex space missions for the assembling spacecraft system. Based on the dynamic equations of relative motion, the optimal impulse control method is devised to find out the impulse sequence which requires the smallest total fuel consumption within specified maneuver duration. The simulation indicates that the optimal impulse control method is an effective approach to achieve the reconfiguration of the assembling spacecraft.

关 键 词：组合式航天器 构型变换 最优脉冲控制 线性规划 

分 类 号：V41[航空宇航科学与技术—航空宇航推进理论与工程]