乘波飞行器低马赫数飞行状态下的气动性能研究  

Research on Aerodynamic Characteristics of Waverider-Based Vehicles Flying at Low-Mach States

作　　者：李维东[1] 丁海河[1] 王发民[1] 

机构地区：[1]中国科学院力学研究所高温气湾动力学重点实验室,北京100190

出　　处：《宇航学报》2010年第5期1283-1288,共6页Journal of Astronautics

基　　金：国家自然科学基金项目(10772186)

摘　　要：乘波飞行器在低马赫数飞行状态下的气动性能是近空间飞行器设计和研究人员关心的问题之一。本文以M=3,设计飞行高度H=15 km为设计点,最大升阻比为优化目标,并通过满足一定的有效载荷容积,气动热防护和气动操纵的要求进行了工程化设计后得到的锥导乘波体为研究对象,借助数值模拟和风洞实验技术相结合的研究手段对乘波飞行器在跨声速和超声速飞行阶段的气动性能进行了探讨。研究结果表明,乘波飞行器在该飞行阶段的气动性能与前缘所处的气动状态密切相关。Aerodynamic characteristics of waveriders flying at low Mach states is one of common concerned problems for hypersonic vehicle designers.By taking a cone-derived waverider as the research object,designed for flight Mach of 3 and height of 15 km above sea level and optimized for maximum lift-to-drag ratio and to meet the requirements for payload volume,aerothermal protection and fly control and locally modified for engineering,the transonic and supersonic aerodynamics of waveriders are discussed in combination with computational fluid dynamics and wind tunnel experimental techniques in this paper.Research results indicate that aerodynamic characteristics of waveriders-based vehicles flying at this speed range strongly depend on aerodynamic states of the leading edge region of vehicles.

关 键 词：乘波飞行器 升阻比 气动性能 

分 类 号：V211.5[航空宇航科学与技术—航空宇航推进理论与工程]