摘要
The tethered satellite system has a great potential and one of its very useful applications is momentum transfer. Raising a payload by deploying it upward from an orbitor on a long tether and then releasing it represents a rather important possible application with significant fael economy. This paper presents a dynamic model set up for a two body tethered satellite system and two control laws of deployment used to simulate the deployment of the system, gives calculation formulas for six orbital elements of two sub satellites and discusses calculation examples.
ＣａｌｃｕｌａｔｉｏｎｏｆＯｒｂｉｔａｌＥｌｅｍｅｎｔｓｆｏｒＲｅｌｅａｓｅｄＴｅｔｈｅｒｅｄＳａｔｅｌｉｔｅＣＵＩＮａｉｇａｎｇ（崔乃刚）ＬＩＵＤｕｎ（刘暾）ＬＩＵＹｕｈｕａ（刘育华）ＱＩＮａｉｍｉｎｇ（齐乃明）（ＡｓｔｒｏｎａｕｔｉｃｓＳｃｈｏｏ...
