新一代远程机动飞行器关键气动问题基础研究

Now the strategic flight vehicles are changing from ballistic reentry vehicles to long-distance maneuvering vehicles flying in the atmosphere, we are facing some basic scientific problems on hypersonic aerodynamics that have not met before and have not been solved theoretically. Based on the problems in HTV-2 test flight and our country met this years, our research will focus on waverider configuration of long-distance maneuvering vehicles, accurate aerodynamic measurement and flight stability. For waverider configuration of long-distance maneuvering vehicles, the fictitious-body of waverider will be generated according to engineering constraint conditions, and then the leading edge will be blunted at different region based on different heat load. The leading edge can be adjusted to control the pressure center, and we can change the pressure distribution of upper surface and lower surface to improve lateral stability. Furthermore, the force balance and related experimental technique for high Mach number and low Reynolds number shock tunnel will be developed , semiconductor sensitive elements will be used to increase sensitivity and the superposition of piezoelectric crystal can improve the accuracy of axial force. At last, a new aerodynamic model will be established for the study of dynamic characteristics of flight vehicles. We will emphatically analyze the coupling characteristics of pitching moment and rolling moment. It could provide scientific basis for performance evaluation of long-distance maneuvering vehicles and would provide a new method for aerodynamic configuration design, aerodynamic measurement and flight control.

面对战略飞行器由再入弹道式飞行到大气层内高机动远程滑翔转变，存在以前在工程上没有遇到、理论上没有解决的高超声速空气动力学基础科学问题。针对HTV-2飞行试验中暴露出来的问题，以及我国在该类飞行器研制中遇到的问题，着重研究远程机动飞行器乘波布局、气动力精确测量和飞行稳定性等基础科学问题。根据工程约束构造生成乘波体的"虚拟体"，依据不同热载荷，进行不同区域前缘钝化；调整前缘线控制纵向压心位置，上下表面压力分布改善横向稳定性。研究高马赫数低雷诺数激波风洞来流模拟技术；通过半导体敏感元件提高灵敏度，压电晶体叠加提高轴向力精度，研制适用于高升阻比复杂布局的激波风洞测力天平和相应的实验技术。通过建立新的飞行力学模型，研究飞行器动态特性，重点分析俯仰力矩和滚转力矩等的耦合特性和提高偏航力矩的模拟精度。为远程机动飞行器飞行性能决策提供科学依据；为飞行器气动布局设计、气动力测量和飞行控制提供新概念新方法。

针对助推滑翔飞行器面临的工程科学问题，开展了乘波布局工程化设计、静稳定性设计途径、复杂布局动态耦合特性和中低雷诺数风洞试验等基础研究。在工程化设计方面，提出了“虚拟体”和强粘性干扰修型两种原始乘波体生成途径；前缘线钝化上采取了根据不同区域热载荷进行不同途径的前缘钝化，缓解了升阻比和热防护之间的矛盾。研究了乘波布局表面压力分布与静稳定性的关系，提出了能够实现乘波布局静稳定性的相关理论和技术途径。为了满足长航时的热防护需要，研究了依靠较少的舵面实现飞行包线内气动操纵需求的舵面设计方法，以及利用横向控制偏离判据(LCDP)，评估横航向的耦合特性。对于非对称复杂布局动态特性物理问题，提出了粘性修正当地流活塞理论（VLPT）和基于参数敏感性的自适应采样代理-降阶非定常气动力模型。在JF-10高焓风洞中开展了中低雷诺数风洞测力实验。