侧向喷流干扰工程估算模型研究  

A study for engineering prediction model of jet disturbance

作　　者：唐伟[1] 张勇[1] 李为吉[1] 张鲁民[2] 

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

出　　处：《流体力学实验与测量》2003年第3期88-92,共5页Experiments and Measurements in Fluid Mechanics

基　　金：国家自然科学基金(10072074)

摘　　要：喷流的直接力控制适用于全速域和全空域,具有响应快、效率高等特点,是控制飞行器飞行的有效手段之一。喷流与飞行器流场的相互干扰十分复杂,准确地获得喷流干扰气动力非常困难。笔者调研了国内外大量的喷流实验和局部凸起物干扰的分离流动实验,利用二维平板及轴对称凸起物绕流的分离特性,初步建立了计算喷流干扰的工程模型。该模型可计算喷流穿透高度、分离区长度、二维分离区边界、分离区平台压力系数,并可对分离特性进行三维修正。利用这一模型,笔者进行了某飞行器的超声速喷流的气动干扰特性计算,并与数值计算结果进行了比较。The jet control system is one of the possible and effective approaches for the vehicle maneuvering because it can be applied to overall speed and attitude range, with quick respond and high effectiveness. The interference induced by the jet is extremely complicated, thus it is very difficult to obtain the effective jet control ability exactly. A primary engineering prediction model for jet interference aerodynamics is established with the help of detail analyses of the experimental results for the separation flow field of 2-D flat and axial-symmetric vehicle. The jet penetration height, the separation distance, the separation boundary and the pressure coefficient within the separation region are estimated, and the 3-D correction is also adopted. The prediction results are presented and validated by a numerical simulation result.

关 键 词：侧向喷流干扰 直接力控制 飞行器控制 工程计算 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计] V448