TY - GEN
T1 - Firing Data Design for the Midcourse Interceptor with Complex Flight Program
AU - Zhang, Zhao
AU - Gao, Changsheng
AU - Jing, Wuxing
AU - Chen, Erkang
N1 - Publisher Copyright:
© 2018 IEEE.
PY - 2018/9/18
Y1 - 2018/9/18
N2 - A rapid design algorithm is proposed to determine the firing data of a four-stage midcourse interceptor covering height from 400 km to 3000 km, taking flight time, mobile launcher and landing positions of engine debris as constraints. Firstly, the necessity of numerical trajectory is analyzed in the case of complex flight program. Then, a novel design scheme is proposed and divided into two parts, namely, predesign and designing. In predesign phase, the step size of firing data is determined on the sensitivity of trajectory to firing data, resulting from uniform design and first-order difference quotient. Afterwards, the ascent trajectories of interceptor are calculated ergodic to establish state table and boundary table with the division of killing zone. During designing phase, the existence of solution to the mission is analyzed by boundary table and average energy method firstly. Then, initial guesses of firing data can be obtained from online table, which is formed by calculating trajectories ergodic according to boundary table. Finally, these initial guesses can be refined by Levenberg-Marquardt method for more accurate performance. Simulation results verify effectiveness of the proposed design algorithm.
AB - A rapid design algorithm is proposed to determine the firing data of a four-stage midcourse interceptor covering height from 400 km to 3000 km, taking flight time, mobile launcher and landing positions of engine debris as constraints. Firstly, the necessity of numerical trajectory is analyzed in the case of complex flight program. Then, a novel design scheme is proposed and divided into two parts, namely, predesign and designing. In predesign phase, the step size of firing data is determined on the sensitivity of trajectory to firing data, resulting from uniform design and first-order difference quotient. Afterwards, the ascent trajectories of interceptor are calculated ergodic to establish state table and boundary table with the division of killing zone. During designing phase, the existence of solution to the mission is analyzed by boundary table and average energy method firstly. Then, initial guesses of firing data can be obtained from online table, which is formed by calculating trajectories ergodic according to boundary table. Finally, these initial guesses can be refined by Levenberg-Marquardt method for more accurate performance. Simulation results verify effectiveness of the proposed design algorithm.
KW - Levenberg-Marquardt method
KW - firing data
KW - firing table
KW - midcourse interceptor
KW - uniform design
UR - https://www.scopus.com/pages/publications/85055575142
U2 - 10.1109/ICMAE.2018.8467690
DO - 10.1109/ICMAE.2018.8467690
M3 - 会议稿件
AN - SCOPUS:85055575142
T3 - Proceedings of 2018 9th International Conference on Mechanical and Aerospace Engineering, ICMAE 2018
SP - 190
EP - 198
BT - Proceedings of 2018 9th International Conference on Mechanical and Aerospace Engineering, ICMAE 2018
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 9th International Conference on Mechanical and Aerospace Engineering, ICMAE 2018
Y2 - 10 July 2018 through 13 July 2018
ER -