利用并联氙气瓶温差补偿航天器质心偏移的可行性研究

在以往航天器研制中,一般通过增加配重的方式对航天器质心偏移进行补偿.这种质心补偿方式占用了运载火箭承载能力资源,降低了航天器的有效承载能力.针对常规质心补偿方式的弱点,利用电推进航天器上氙气高密度填充的特点,提出了一种通过氙气瓶温度控制对航天器质心偏移进行补偿的方法,减少了航天器配重的使用需求.氙气瓶温差对航天器质心偏...

Feasibility study of spacecraft gravity center offset compensation by intentional xenon temperature control

The gravity center offset of spacecraft was generally compensated by adding some balancing weight. The balancing weight was not able to provide other support for spacecraft mission, thus it reduced the loading efficiency of spacecraft. For the spacecraft equipped with high density gas cylinders, e.g. xenon, a new method was raised to compensate the offset of gravity center of spacecraft by the intentional temperature control of xenon cylinders, so as to reduce the use of balancing weight. The gravity center offset compensation ability influenced by the temperature control of xenon cylinders was positively related to xenon mass ratio and xenon cylinders′ centroid spacing. Under the condition of application for spacecraft, the gravity center offset with magnitude order of tens of millimeters can be compensated by the temperature control of xenon cylinders and the minimum compensation error was approximately 2mm. References for gravity center compensation of electric propulsion spacecraft can be provided.