可变弯尾飞行器飞行特性研究  

A study on flight performance of a Variable-Bend-Tail Vehicle

作　　者：唐伟[1] 张勇[2] 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,陕西西安710072

出　　处：《空气动力学学报》2003年第2期151-156,共6页Acta Aerodynamica Sinica

基　　金：国家自然科学基金资助项目(项目批准号10072074)。

摘　　要：本文研究了可变弯尾飞行器的机动飞行问题。可变弯尾飞行器具有气动控制独特、机动范围可调等特点,是高超声速飞行器实现机动飞行的有效途径。本文通过气动力工程计算与飞行器六自由度弹道的耦合计算,研究了此类飞行器在再入过程中的机动控制和飞行稳定性。The problems of maneuvering flight performance for a VariableBendTail Vehicle are investigated. VariableBendTail Vehicle is one of the useful approaches for supersonic and hypersonic maneuver, because of its unique control mechanism and adjustable maneuverability. The aerodynamic joint hinge moment generated by its bend tail is one of the most challenging problem. Through the analysis and the optimization, an optimum configuration of VariableBendTail Vehicle was obtained which has an acceptable hinge moment and a high lifttodrag ratio during the wide range of trimming flight conditions. Using a coupling technique of aerodynamics engineering prediction method and numerical simulation of 6D ballistic trajectory, the flight performance of this vehicle under the given bendtail disciplinarian, the flight stability,the joint moment characteristics and the effects of side wind are studied. 

关 键 词：可变弯尾飞行器 飞行特性 机动飞行 气动控制 再入过程 

分 类 号：V212[航空宇航科学与技术—航空宇航推进理论与工程]