Iterative reentry guidance method with terminal heading angle and time constraints

TY - JOUR

T1 - Iterative reentry guidance method with terminal heading angle and time constraints

AU - Han, Wanru

AU - Liu, Junhui

AU - Shan, Jiayuan

AU - Wang, Jianan

N1 - Publisher Copyright: © 2026, Chinese Institute of Electronics. All rights reserved.

PY - 2026/3/6

Y1 - 2026/3/6

N2 - An iterative reentry guidance method based on angle of attack profile correction and bank reversals search is proposed to meet constraints on the time and heading angle of the mid-terminal shift in hypersonic vehicle. To address the time and range constraints of the gliding phase, a dual-parameter drag acceleration profile with corridor-boundary interpolation is designed in the longitudinal-plane. The heading angle constraint is transformed into a nonlinear optimization problem of the lateral-plane bank angle reversal point, and a bank angle reversal search strategy based on simulated annealing-sequential quadratic programming (SA-SQP) hybrid optimization is developed. Furthermore, in order to reduce the coupling interference error between longitudinal and lateral guidance, a predictor-corrector method with real-time correction of the angle of attack profile is proposed to improve the guidance accuracy. Numerical simulation experiments verify that the algorithm can satisfy the constraints of flight time, range, heading angle, etc., and has high guidance accuracy and strong mission adaptability. Monte Carlo simulations further validate the adaptability and robustness of the method against initial state deviations and process disturbances.

AB - An iterative reentry guidance method based on angle of attack profile correction and bank reversals search is proposed to meet constraints on the time and heading angle of the mid-terminal shift in hypersonic vehicle. To address the time and range constraints of the gliding phase, a dual-parameter drag acceleration profile with corridor-boundary interpolation is designed in the longitudinal-plane. The heading angle constraint is transformed into a nonlinear optimization problem of the lateral-plane bank angle reversal point, and a bank angle reversal search strategy based on simulated annealing-sequential quadratic programming (SA-SQP) hybrid optimization is developed. Furthermore, in order to reduce the coupling interference error between longitudinal and lateral guidance, a predictor-corrector method with real-time correction of the angle of attack profile is proposed to improve the guidance accuracy. Numerical simulation experiments verify that the algorithm can satisfy the constraints of flight time, range, heading angle, etc., and has high guidance accuracy and strong mission adaptability. Monte Carlo simulations further validate the adaptability and robustness of the method against initial state deviations and process disturbances.

KW - angle of attack profile correction

KW - lateral guidance

KW - multi-constraint guidance

KW - reentry guidance

UR - https://www.scopus.com/pages/publications/105032742808

U2 - 10.12305/j.issn.1001-506X.2026.02.24

DO - 10.12305/j.issn.1001-506X.2026.02.24

M3 - Article

AN - SCOPUS:105032742808

SN - 1001-506X

VL - 48

SP - 638

EP - 651

JO - Xi Tong Gong Cheng Yu Dian Zi Ji Shu/Systems Engineering and Electronics

JF - Xi Tong Gong Cheng Yu Dian Zi Ji Shu/Systems Engineering and Electronics

IS - 2

ER -