近空间高超声速高升阻比布局飞行器动稳定性研究

项目名称： 近空间高超声速高升阻比布局飞行器动稳定性研究

项目编号： No.91216205

项目类型： 重大研究计划

立项/批准年度： 2013

项目学科： 数理科学和化学

项目作者： 王发民

作者单位： 中国科学院力学研究所

项目金额： 350万元

中文摘要： 目前我们面临着由空间快速再入到大气层中长航时高超声速飞行的转变，气动布局也由大钝头低升阻比布局转化为高升阻比复杂布局，目前国内对这类布局的动稳定性研究还未开展起来。针对近空间高超声速长航时大机动飞行面临的工程科学问题，开展该飞行条件下大梯度墒层、强粘性干扰和激波/边界层干扰等复杂流动现象的基础研究，以此为依据，建立一种相适应的基于CFD的非定常气动力工程模型，同时在CFD/RBD耦合系统的基础上，开展气动力降阶方法研究。通过上述两种途径，建立满足宽速域、宽空域高升阻比复杂外形工程需求的高效非定常气动力工程计算理论体系和软件平台。利用上述理论和计算平台，开展耦合系统失稳敏感性分析。进而结合控制系统和气动操纵，开展闭环耦合系统的失稳敏感性研究。针对典型高升阻比外形，开展激波风洞自由飞实验，对上述理论进行验证。

中文关键词： 高超声速；乘波体；稳定性；动稳定性；非定常气动力

英文摘要： The hypersonic applications are turning from rapid space re-entry into long-endurance hypersonic cruise in atmosphere. The corresponding aerodynamic layout is also turning from large blunt-head configurations with low lift-to-drag ratio into configurations with high lift-to-drag ratio. However, the research on the dynamic stability of this type of configuration has not been started yet. In order to full fill the needs of analyses for near-space long-endurance high maneuver hypersonic flight, the project is about to build appropriate CFD- based engineering unsteady aerodynamic model and Reduced-Order-Model basing on the researches on the hypersonic flow characters of large gradient of moisture layer, strong adhesive interference, and shock / boundary layer interference. With the new unsteady aerodynamic models, an efficient unsteady aerodynamic prediction system will be built. coupled with 6 DOF rigid body dynamic equations, the departure susceptibility criteria will be analyzed. coupling with control system and aerodynamic control surfaces, the departure susceptibility criteria of the closed-loop system will be studied. Shock tunnel freeflight test will be performed in order to verify the numerical analyses.

英文关键词： hypersonic；waverider；stability；dynamic stability；unsteady aerodynamics