Aerodynamic optimization and evaluation for the three-dimensional afterbody/nozzle integrated configuration of hypersonic vehicles  

作　　者：GAO TaiYuan CUI Kai WANG XiuPing HU ShouChao YANG GuoWei REN Liang 

机构地区：[1]Key Laboratory of High Temperature Gas Dynamics,Institute of Mechanics,Chinese Academy of Science,Beijing 100190,China [2]China Petroleum Pipeline Offshore Engineering,Langfang 065000,China

出　　处：《Chinese Science Bulletin》2012年第8期849-857,共9页

基　　金：supported by the National Natural Science Foundation of China (90916013)

摘　　要：The optimization of 2D expansion lines and key parameters of three-dimensional configurations was carried out under simulated conditions of Mach 6.5 and a flight altitude of 25 km for an integrated configuration of the afterbody/nozzle of a hypersonic vehicle.First,the cubic B-spline method was applied to parameterize the expansion lines of the upper expansion ramp.The optimization procedure was established based on computational fluid dynamics and the sequential quadratic programming method.The local mesh reconstruction technique was applied to improve computational efficiency.A three-dimensional integrated configuration afterbody/nozzle was designed based on the two-dimensional optimized expansion lines.The influence rules incorporated certain key design parameters affecting the lift and thrust performance of the configuration,such as the ratio of the lengths of the lower expansion ramp to the afterbody (l/L),the dip angle of the lower expansion ramp ω,and the ratio of exit height to the length of afterbody (H/L).Under these conditions,we found that the integrated configuration has optimal performance when l/L=1/6,H/L=0.35 and =10°.We also showed that the presence of a side-board promotes lift and thrust performance,and effectively prevents the leakage of high pressure gas.The optimization of 2D expansion lines and key parameters of threedimensional configurations was carried out under simulated conditions of Mach 6.5 and a flight altitude of 25 km for an integrated configuration of the afterbody/nozzle of a hypersonic vehi cle. First, the cubic Bspline method was applied to parameterize the expansion lines of the upper expansion ramp. The optimiza tion procedure was established based on computational fluid dynamics and the sequential quadratic programming method. The local mesh reconstruction technique was applied to improve computational efficiency. A threedimensional integrated configura tion afterbody/uozzle was designed based on the twodimensional optimized expansion lines. The influence rules incorporated certain key design parameters affecting the lift and thrust performance of the configuration, such as the ratio of the lengths of the lower expansion ramp to the afterbody （l/L）, the dip angle of the lower expansion ramp to, and the ratio of exit height to the length of afterbody （H/L）. Under these conditions, we found that the integrated configuration has optimal performance when llL=l/6, H/L=0.35 and co=10°. We also showed that the presence of a sideboard promotes lift and thrust performance, and effectively prevents the leakage of high pressure gas.

关 键 词：气动优化设计 高超声速飞行器 综合配置 尾部 三维 喷嘴 序列二次规划法 计算流体动力学 

分 类 号：TP316.8[自动化与计算机技术—计算机软件与理论] V224[自动化与计算机技术—计算机科学与技术]