The invention discloses a design method and device for a tail-stage in-orbit of a solid carrier rocket. The method comprises the steps of obtaining a space test requirement of a test load of rail leaving; determining the mounting position of a test load according to space test requirements; the final stage of the solid carrier rocket is used as a carrying platform of a test load, and after the final stage is separated from a main satellite, the residual propellant of the final stage provides energy for the final stage and the test load during in-orbit operation. Therefore, after the main satellite is separated from the final stage, the space test can be carried out by continuing to remain on the orbit to carry the small satellite, so that more space test opportunities are provided, the test cost of the small satellite is greatly reduced, and the utilization rate of the final stage of the carrier rocket is improved.
本发明公开一种固体运载火箭留轨末级设计方法及装置。通过获取留轨的试验载荷的空间试验要求;根据空间试验要求,确定试验载荷的安装位置;将固体运载火箭的末级作为试验载荷的搭载平台,末级与主卫星脱离后,末级的剩余推进剂为末级以及试验载荷留轨运行时提供能量。如此,可在主卫星与末级分离后,继续留轨搭载小卫星能够开展空间试验,从而提供更多空间试验机会,大大降低小卫星的试验成本,提高运载火箭末级的利用率。
Solid carrier rocket in-orbit final-stage design method and solid carrier rocket in-orbit final-stage design device
一种固体运载火箭留轨末级设计方法及装置
2023-08-18
Patent
Electronic Resource
Chinese
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