空气动力学学报2026，Vol.44Issue(5)：78-87,10.DOI:10.7638/kqdlxxb-2025.0096
基于离散伴随方程的飞行器机动点气动优化设计研究
Aerodynamic optimization design of aircraft at maneuver points based on discrete adjoint equations
陈其盛 1张伟 1邓俊 2刘刚 1陈宪 1章胜1
作者信息
- 1. 中国空气动力研究与发展中心 空天技术研究所,绵阳 621000
- 2. 中国空气动力研究与发展中心 空天技术研究所,绵阳 621000||西北工业大学 航空学院,西安 710072
- 折叠
摘要
Abstract
Modern supersonic aircraft with low aspect ratio must achieve favorable subsonic and supersonic cruise efficiency and high maneuverability.However,conventional aerodynamic optimization has primarily focused on cruise lift-to-drag characteristics,with limited attention paid to maneuverability at high angles of attack,yielding designs that fail to satisfy practical engineering requirements.To address this gap,a discrete adjoint aerodynamic optimization design method based on an upwind scheme is developed.A high-fidelity adjoint-gradient optimization framework is established based on the free form deformation(FFD)method and the sequential quadratic programming(SQP)algorithm.This framework is applied to the maneuverability optimization of a low-aspect-ratio wing at high angles of attack under supersonic conditions,and the resulting configurations are evaluated for both cruise aerodynamic performance and overload characteristics across subsonic and supersonic flight regimes.The results indicate that the optimized configuration achieves an increase in normal overload of approximately 0.1 g at Ma=0.9 and 0.27 g at Ma=1.5.The maneuverability of the aircraft is improved under transonic and supersonic conditions,while the cruise lift-to-drag characteristics are essentially preserved.These findings demonstrate the applicability of the proposed method to complex engineering problems and provide valuable guidance for practical design applications.关键词
超声速飞行器/气动优化设计/机动飞行性能/离散伴随方法/压力分布Key words
supersonic aircraft/aerodynamic optimization design/maneuvering flight performance/discrete adjoint method/pressure distribution分类
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陈其盛,张伟,邓俊,刘刚,陈宪,章胜..基于离散伴随方程的飞行器机动点气动优化设计研究[J].空气动力学学报,2026,44(5):78-87,10.
