双椭圆截面再入飞行器的气动计算及布局优化设计  

Aerodynamics prediction and configuration optimizati on for reentry vehicle with double-ellipse cross-section

作　　者：唐伟[1] 高晓成[1] 李为吉[2] 张鲁民[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000 [2]西北工业大学,西安710072

出　　处：《空气动力学学报》2004年第2期171-174,共4页Acta Aerodynamica Sinica

基　　金：国家自然科学基金资助项目(批准号10072074).

摘　　要：双椭圆截面飞行器较圆截面回转体外形具有更好的刚性、更轻的重量、更大的容积和更高的配平升阻比。本文首先发展了一套可以计算该类飞行器纵横向气动力的工程计算方法,并利用N S方程数值模拟方法进行了验证。其次,对此类飞行器的气动布局进行了优化设计,并利用相同的优化模型对圆截面外形进行了计算。最后,对双椭圆截面优化外形和圆截面优化外形的气动特性进行了比较。Traditionally reentry vehicles are designed to be axial symmetric, whereas vehicle with double-ellipse cross-section has a better rigidity, bigger volume, higher trimming lift and lift-to-drag ratio. Firstly, through the introduction of equivalent cone and equivalent cross-section, an engineering method based on Embedded Newtonian Flow Theory was presented to predict the aerodynamic characteristics of this vehicle during hypersonic reentry flight. The comparison of the results with that of N-S equation numerical simulation shows that the accuracy of the presented method is sufficient for the conceptual design, and the correctness and effectiveness of the vehicle for higher trimming lift and lift-to-drag ratio together with the optimization for circle cross-section vehicle under the same constraints of equal length and base area. The optimum results shows that the vehicle with double-ellipse cross-section has high lift and lift-to-drag ratio than the vehicle with circle cross-section as the angle of attack is higher than 7 degree. Finally, the comparison of lift-to-drag ratio and mass center displacement needed for trimming condition were investigated. The stability of the vehicle with double-ellipse cross-section is higher than circle one, easer for the design of mass distribution, and is beneficial for the rolling control. The work indicates that the reentry vehicle with double-cross-section is one of the feasible choices for hypersonic maneuver, and needs to be investigated further in the future.

关 键 词：双椭圆截面 再入飞行器 气动特性 计算 布局 优化设计 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]