CAJ | 학술논문

根据“上帝之杖”弹道式再入动能打击假想，利用自适应伪谱法分别研究有限推力制动和连续小推力制动作用下动能弹所能达到的最大再入倾角，分析过渡段实现动能弹垂直再入的可行性。通过计算发现，在再入倾角接近垂直的情况下，无论采用哪种制动方式，随着动能弹质量的增加，燃料消耗量急剧增加，动能弹与燃料质量比达到1：9；采用有限推力制动时，能够在较短时间内以接近垂直的倾角再入，但再入速度较低，约3.5 km/s；而采用连续小推力作用时，再入倾角接近垂直，再入速度较高，约7 km/s，但发动机工作时间长，过渡段飞行时间超过1 h。
근거“상제지장”탄도식재입동능타격가상，이용자괄응위보법분별연구유한추력제동화련속소추력제동작용하동능탄소능체도적최대재입경각，분석과도단실현동능탄수직재입적가행성。통과계산발현，재재입경각접근수직적정황하，무론채용나충제동방식，수착동능탄질량적증가，연료소모량급극증가，동능탄여연료질량비체도1：9；채용유한추력제동시，능구재교단시간내이접근수직적경각재입，단재입속도교저，약3.5 km/s；이채용련속소추력작용시，재입경각접근수직，재입속도교고，약7 km/s，단발동궤공작시간장，과도단비행시간초과1 h。
Referring to the supposition of ballistic reentry for kinetic energy attacking named as “God’s Rod”, the max reentry angle of payload controlled by limit thrust and continuous low-thrust was researched using adaptive pseudo-spectral method, and the feasibility for perpendicular reentry of payload was analyzed. The result illuminated that whatever de-orbit model was used to ensure the reentry angle of payload close to vertical, the consumption of fuel increased sharply with the payload mass, the mass ratio of payload to fuel attained 1:9. When a limit thrust was used for de-orbit, the reentry angle could get close to perpendicular in a short time, but the velocity was only 3.5 km/s. However, when the continuous low-thrust was used, the reentry angle could be close to vertical with a higher velocity about 7 km/s, but the work time of engine exceeded 1 hour.