Orbit design for the Laser Interferometer Space Antenna (LISA)
Orbit design for the Laser Interferometer Space Antenna (LISA)
复制标题
激光干涉仪空间天线（LISA）的轨道设计
DOI：
10.1007/s11433-010-0100-7
复制
发表时间：
2010-01-01
影响因子：
6.4
通讯作者：
Luo YongJie
中科院分区：
文献类型：
--
作者：
Xia Yan;Li GuangYu;Luo YongJie
激光干涉仪空间天线（丽莎）是欧空局-美国航天局的一项联合使命，通过在三个航天器之间使用精确的激光干涉测量法，探测0.1兆赫至1赫兹频率范围内的低频引力波，这些航天器将于2018年左右发射，一年后到达其绕太阳的运行轨道。为了成功运行，三个航天器的星座具有极高的稳定性至关重要。在对2015年某次发射的运行轨道进行研究的基础上，设计了2019-03-01开始历元的运行轨道，并介绍了轨道设计和优化方法。设计了卫星从地球转移到运行轨道的轨道，包括发射段和分离段，并分析了这两个轨道段的能量需求与飞行时间的关系。最后给出了一个轨道设计实例。
The Laser Interferometer Space Antenna (LISA) is a joint ESA-NASA mission for detecting low-frequency gravitational waves in the frequency range from 0.1 mHz to 1 Hz, by using accurate laser interferometry between three spacecrafts, which will be launched around 2018 and one year later reach their operational orbits around the Sun. In order to operate successfully, it is crucial for the constellation of the three spacecrafts to have extremely high stability. Based on the study of operational orbits for a 2015 launch, we design the operational orbits of beginning epoch on 2019-03-01, and introduce the method of orbit design and optimization. We design the orbits of the transfer from Earth to the operational orbits, including launch phase and separation phase; furthermore, the relationship between energy requirement and flight time of these two orbit phases is investigated. Finally, an example of the whole orbit design is presented.