To use the data after separation of satellite and rocket in the process of calculating orbit, a correction method is proposed.
为了使航天测控中星箭分离后得到的数据能够在定轨时获得应用，提出了一种修正方法。
It is shown that the radial shock of the satellite-rocket separation interface increases with the increase of the pre-tightening force of clamp band.
分析结果表明，分离面径向冲击随着包带预紧力增加而增大；
The shock induced by satellite-rocket separation is one of the severe mechanical environments that the spacecraft has to experience.
星箭分离冲击是航天器所经历的较为严酷的力学环境之一。
应用推荐