Zhao-hua+Yi

Based on many co-orbital phenomena in astronomy and astronautics, a dynamical model — co-orbit restricted problem is pointed out. To study the orbit of LISA looks as an example. It is a 2+3 co-orbit restricted problem which can be divided into two parts. First, to discuss the motion of C, the center of mass of 3 spacecraft under the gravitation of the sun and the earth (plus moon) looks as a co-orbit restricted 3-body problem (planar and circular). The analytical result of position variation of C is given. Second, the configuration of 3 spacecraft that constitute an equilateral triangle at origin of time is discussed; it is found that the armlengths of triangle vary sensitively with the inclination angle between the plane defined by 3 spacecraft to the ecliptic plane. The optimal inclination angle is given.
 * A Dynamical Model—Co-orbit Restricted Problem and its Application to Astronomy and Astronautics **
 * Zhaohua Yi 1,2, Guangyu Li 1, **
 * Gerhard Heinzel 3, Oliver Jennrich 4 **
 * 1. Purple Mountain Observatory, CAS **
 * 2. Nanjing University **
 * 3. Max Planck Institute for Gravitational Physics **
 * 4. European Space Research and Technology Center **