The invention discloses a near-earth asteroid kinetic energy impact task orbit design method with an optimal deflection effect, and the method comprises the following steps: S1, selecting initial parameters of a spacecraft, including starting and arrival moments of the spacecraft; s2, designing a spacecraft orbit into splicing of three sections, namely a large elliptical earth parking orbit, an earth escape orbit starting from the large elliptical orbit and an interplanetary transfer orbit, and calculating orbit parameters; s3, performing target near-earth asteroid deflection effect evaluation; and S4, traversing all possible departure and arrival moments of the spacecraft, repeating the steps S1 to S3, drawing a contour map of the deflection distance and the departure and arrival moments of the spacecraft, eliminating unreasonable moments, and then determining a spacecraft launching window with the optimal deflection effect. According to the method, the large elliptical earth parking orbit is adopted, and the spacecraft launching window is screened, so that the mass and the relative speed of the spacecraft are relatively high when the spacecraft impacts the asteroid, and the optimal asteroid deflection effect is achieved.
本发明公开一种偏转效果最优的近地小行星动能撞击任务轨道设计方法,包括以下步骤:S1,选择航天器初始参数,包括航天器出发和到达时刻;S2,将航天器轨道设计为大椭圆地球停泊轨道、从大椭圆轨道出发的地球逃逸轨道及行星际转移轨道三段的拼接,并进行轨道参数计算;S3,进行目标近地小行星偏转效果评估;S4,遍历航天器所有可能的出发和到达时刻,重复步骤S1~S3,绘制偏转距离与航天器出发、到达时刻的等高线图,并剔除不合理时刻后从中确定偏转效果最优的航天器发射窗口。本发明通过采用大椭圆地球停泊轨道,并筛选航天器发射窗口,使得航天器在撞击小行星时的质量和相对速度较大,从而取得最优的小行星偏转效果。
Design method of near-earth asteroid kinetic energy impact task orbit with optimal deflection effect
偏转效果最优的近地小行星动能撞击任务轨道设计方法
2022-12-30
Patent
Electronic Resource
Chinese
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