TY - JOUR
T1 - 基于代理模型的高效全局低音爆优化设计方法
AU - Qiao, Jianling
AU - Han, Zhonghua
AU - Song, Wenping
N1 - Publisher Copyright:
© 2018, Press of Chinese Journal of Aeronautics. All right reserved.
PY - 2018/5/25
Y1 - 2018/5/25
N2 - It is of great significance to develop efficient numerical optimization methods for low boom design of future supersonic transport aircrafts. To this end, researchers have developed the methods of combining sonic boom prediction with Genetic Algorithm (GA), gradient-based optimization using an Adjoint approach, etc. However, GA has suffered from the prohibitive computational cost for high-dimensional design optimization, and gradient-based optimization can become trapped into a local optimum. This paper proposes to use efficient surrogate-based global optimization towards more effective low sonic boom design. First, the fundamentals of the Whitham theory are introduced, and a comparison of the predicted pressure signals with experimental data shows that the theory is efficient and reasonably accurate for preliminary design of a supersonic transport aircraft. Second, the framework of Surrogate-Based Optimization (SBO) is introduced, including the key elements such as design of experiments, surrogate modeling, infill-sampling criteria and convergence criteria, etc. Third, the proposed methodology of low sonic boom design optimization using SBO is verified by a benchmark sonic boom model of the NASA stepped cone. The comparative study shows that the efficiency of the proposed method is two-orders higher than that of GA, and the optimization results are apparently better than that obtained by the gradient-based method. Finally, a wing-body configuration (69° sweepback delta wing body) taken from the first sonic boom prediction workshop of AIAA is optimized by using the proposed method, and 27.4% reduction of overpressure of the far-field N-wave is achieved. This test demonstrates the great potential of applying the surrogate-based optimization to low boom design of more complex configurations.
AB - It is of great significance to develop efficient numerical optimization methods for low boom design of future supersonic transport aircrafts. To this end, researchers have developed the methods of combining sonic boom prediction with Genetic Algorithm (GA), gradient-based optimization using an Adjoint approach, etc. However, GA has suffered from the prohibitive computational cost for high-dimensional design optimization, and gradient-based optimization can become trapped into a local optimum. This paper proposes to use efficient surrogate-based global optimization towards more effective low sonic boom design. First, the fundamentals of the Whitham theory are introduced, and a comparison of the predicted pressure signals with experimental data shows that the theory is efficient and reasonably accurate for preliminary design of a supersonic transport aircraft. Second, the framework of Surrogate-Based Optimization (SBO) is introduced, including the key elements such as design of experiments, surrogate modeling, infill-sampling criteria and convergence criteria, etc. Third, the proposed methodology of low sonic boom design optimization using SBO is verified by a benchmark sonic boom model of the NASA stepped cone. The comparative study shows that the efficiency of the proposed method is two-orders higher than that of GA, and the optimization results are apparently better than that obtained by the gradient-based method. Finally, a wing-body configuration (69° sweepback delta wing body) taken from the first sonic boom prediction workshop of AIAA is optimized by using the proposed method, and 27.4% reduction of overpressure of the far-field N-wave is achieved. This test demonstrates the great potential of applying the surrogate-based optimization to low boom design of more complex configurations.
KW - Design optimization
KW - Efficient global optimization
KW - Sonic boom
KW - Supersonic transport
KW - Surrogate model
UR - http://www.scopus.com/inward/record.url?scp=85052712534&partnerID=8YFLogxK
U2 - 10.7527/S1000-6893.2017.21736
DO - 10.7527/S1000-6893.2017.21736
M3 - 文章
AN - SCOPUS:85052712534
SN - 1000-6893
VL - 39
JO - Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica
JF - Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica
IS - 5
M1 - 121736
ER -