我国载人航天器飞行轨道设计  

Orbit Design of China Manned Spacecraft

作　　者：汤溢 商帅 陈伟跃 张亚锋 张治国 TANG Yi;SHANG Shuai;CHEN Weiyue;ZHANG Yafeng;ZHANG Zhiguo(Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《航天器工程》2022年第6期54-61,共8页Spacecraft Engineering

基　　金：中国载人航天工程。

摘　　要：我国载人航天器轨道设计从无到有,已形成了完整的体系,包括初始轨道设计、运行轨道设计、返回轨道设计、交会对接轨道设计和离轨轨道设计等。在载人航天工程初期,轨道设计与工程各大系统及航天器自身约束条件相互耦合,共同确定了载人航天工程基本方案。随着交会对接、空间站建造等工程任务发展,轨道设计适应新的任务需求,采用新的算法,优化轨道控制精度、推进剂消耗等指标,充分利用航天器自主轨道控制能力,提升整个工程任务的效率和技术先进性。Orbit design of China manned spacecraft, including initial, operational, returning, rendezvous and docking, and de-orbiting design, etc., has developed a complete system from nothing. At the beginning of the manned space program, all the constraints of orbit design, major systems of the program and the spacecraft itself are inter-couple, and the basic plan of manned space program is determined based on the constraints. With the development of rendezvous and docking, space station construction and so on, orbit design adapts to new requirements. New algorithms are adopted, and orbit control accuracy and propellant consumption are optimized. Spacecraft autonomous orbit control capability is fully utilized in order to improve the efficiency and technical sophistication of the program.

关 键 词：载人航天器 轨道设计 任务需求 自主轨道控制 

分 类 号：V529.1[航空宇航科学与技术—人机与环境工程]