TY - GEN
T1 - Surrogate-Assisted Optimization of Hypersonic Gliding Vehicle for Range Extension in Re-entry Flight
AU - Song, Yixing
AU - Shi, Renhe
AU - Tai, Xinhui
N1 - Publisher Copyright:
© The Chinese Mechanical Engineering Society 2026.
PY - 2026
Y1 - 2026
N2 - To increase the range of re-entry flight and improve the performance of hypersonic gliding vehicle (HGV), a surrogate-assisted multidisciplinary design optimization (MDO) framework is developed in this paper. First, the HGV multidisciplinary optimization problem is defined to increase the range of re-entry flight subject to the constraints of overload, heat flux, aerodynamic pressure, and plot ratio. Then the parameterized geometry model is established based on the free form deformation method to effectively change the shape of HGV. The panel method is used to calculate the aerodynamic force and heat flux, where the heat flux in the stagnation region is obtained by the Detra-Kemp-Riddell formula. And the re-entry flight model is established considering the effect of oblateness perturbation and rotational angular velocity of Earth. Finally, the multidisciplinary optimization problem is efficiently solved by Kriging assisted constrained differential evolution (KRG-CDE) algorithm. After optimization, the flight range is increased by 34% while the heat flux in the stagnation region is decreased by 22%. Moreover, the optimization cost of KRG-CDE is reduced by 64% compared with that of the conventional differential algorithm, which illustrates the practicability and effectiveness of the proposed surrogate-assisted MDO framework.
AB - To increase the range of re-entry flight and improve the performance of hypersonic gliding vehicle (HGV), a surrogate-assisted multidisciplinary design optimization (MDO) framework is developed in this paper. First, the HGV multidisciplinary optimization problem is defined to increase the range of re-entry flight subject to the constraints of overload, heat flux, aerodynamic pressure, and plot ratio. Then the parameterized geometry model is established based on the free form deformation method to effectively change the shape of HGV. The panel method is used to calculate the aerodynamic force and heat flux, where the heat flux in the stagnation region is obtained by the Detra-Kemp-Riddell formula. And the re-entry flight model is established considering the effect of oblateness perturbation and rotational angular velocity of Earth. Finally, the multidisciplinary optimization problem is efficiently solved by Kriging assisted constrained differential evolution (KRG-CDE) algorithm. After optimization, the flight range is increased by 34% while the heat flux in the stagnation region is decreased by 22%. Moreover, the optimization cost of KRG-CDE is reduced by 64% compared with that of the conventional differential algorithm, which illustrates the practicability and effectiveness of the proposed surrogate-assisted MDO framework.
KW - Hypersonic gliding vehicle
KW - Multidisciplinary design optimization
KW - Re-entry flight optimization
KW - Surrogate-assisted optimization
UR - https://www.scopus.com/pages/publications/105041214279
U2 - 10.1007/978-981-95-7342-4_35
DO - 10.1007/978-981-95-7342-4_35
M3 - Conference contribution
AN - SCOPUS:105041214279
SN - 9789819573417
T3 - Mechanisms and Machine Science
SP - 509
EP - 525
BT - Advances in Mechanical Design - Proceedings of the 2025 International Conference on Mechanical Design ICMD 2025
A2 - Tan, Jianrong
A2 - Liu, Zhenyu
A2 - Hu, Weifei
PB - Springer Science and Business Media B.V.
T2 - International Conference on Mechanical Design, ICMD 2025
Y2 - 9 May 2025 through 11 May 2025
ER -