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Assembled kinetic impactor for deflecting asteroids by combining the spacecraft with the launch vehicle upper stage
Icarus ( IF 3.2 ) Pub Date : 2021-06-24 , DOI: 10.1016/j.icarus.2021.114596
Yirui Wang , Mingtao Li , Zizheng Gong , Jianming Wang , Chuankui Wang , Binghong Zhou

Asteroid impacts pose a major threat to all life on Earth. Deflecting an asteroid on an impact trajectory is critical to mitigating this threat. A kinetic impactor remains the most feasible asteroid deflection method. However, due to launch capability constraints, an impactor with a limited mass can only minimally change the velocity of an asteroid. To improve the deflection efficiency of the kinetic impactor strategy, this paper proposes the Assembled Kinetic Impactor (AKI), which combines the spacecraft with the launch vehicle upper stage. After the launch vehicle upper stage sends the spacecraft into an Earth-escaping trajectory, the spacecraft-rocket separation is not performed, and the spacecraft controls the AKI to impact the asteroid. By retaining the mass of the launch vehicle upper stage, the mass of the impactor is increased, thereby enhancing the deflection efficiency. According to the technical data of the Long March 5 (CZ-5) launch vehicle, missions to deflect Bennu are designed to demonstrate the power of the AKI concept. Simulation results of the AKI compared with the Classical Kinetic Impactor (CKI, with spacecraft-rocket separation) show that the addition of the mass of the upper stage increases the deflection distance by >3 times. To achieve a given deflection distance, the addition of the upper stage mass reduces the number of launches to 1/3 that of the number of CKI launches. The AKI concept makes it possible to deflect large Bennu-like asteroids with a nuclear-free technique with a 10-year launch lead time. Additionally, with a single CZ-5, the deflection distance of a 140-m-diameter asteroid with a 10-year launch lead time increases from less than 1 to more than 1 Earth radius, representing an improvement in the reliability and efficiency of asteroid deflection missions.



中文翻译:

通过将航天器与运载火箭上级相结合,用于偏转小行星的组装动力撞击器

小行星撞击对地球上的所有生命构成重大威胁。在撞击轨迹上偏转小行星对于减轻这种威胁至关重要。动力撞击器仍然是最可行的小行星偏转方法。然而,由于发射能力的限制,质量有限的撞击器只能最低限度地改变小行星的速度。为提高动力冲击器策略的偏转效率,本文提出了组合动力冲击器(AKI),将航天器与运载火箭上级相结合。运载火箭上级将飞船送入逃离地球的轨迹后,不进行飞船-火箭分离,飞船控制AKI撞击小行星。通过保留运载火箭上级的质量,增加了撞击器的质量,从而提高偏转效率。根据长征五号(CZ-5)运载火箭的技术数据,本努偏转任务旨在展示AKI概念的威力。AKI 与经典动力学撞击器(CKI,航天器-火箭分离)相比的模拟结果表明,增加上级质量使偏转距离增加了 >3 倍。为了实现给定的偏转距离,增加上级质量将发射次数减少到 CKI 发射次数的 1/3。AKI 概念使得使用无核技术偏转大型 Bennu 类小行星成为可能,发射周期为 10 年。此外,使用单个 CZ-5,

更新日期:2021-06-29
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