箭载中层大气三维流场探测理论问题研究

We are confronted by five problems, i.e., ‘calibrating under a black box of physics for flow over a sphere’, ‘error resulting from the detached flow’, ‘the displacement effects of the sheared flow’, ‘the cost effects rating’, and ‘the lack of theoretical basis’, when idea of the multiple-hole probe (MHP) is adopted by the rocket-borne 3D wind sounding in the Middle atmosphere. For these reasons, theory study on the sphere MHP as the rocket-borne 3D wind-sounding load is suggested here. Firstly, the parameterized theoretical model for the sheared supersonic compressible-flow over a sphere should be developed following the parameterized shock position model and the parameterized detached flow model, that both are created with the output data of the directed numerical simulation (DNS) to the case of flow over a sphere. Secondly, an regularized inversion scheme should be developed for those model parameters after its reduction for the boundary integral relations between the free flow and the distribution of the surface pressure over the sphere. Thirdly, a regularized inversion scheme for solution of the free flow conditions should be developed after the newly developed 3D Hilbert transform formulae over a ball and its high accuracy quadrature schemes. Lastly, the new technology for the synchronously measuring of the 3D flow and its vortices vector field is then created, which is shown as the result of theory innovation for 3D wind-sounding in the Middle atmosphere. Theoretical innovation for rocket-borne wind-sounding MHP will take great chance to developments of this new technology, once problems restricting its capabilities are solved. It is believed that development of this new technology will play an important role for studies on the instability of gravity waves in Middle atmosphere, and can be used to develop the key instruments for inspection of the transition conditions for those waves.

针对传统多孔探针流场测量原理在箭载中层大气三维流场探测应用中会面临“黑盒测试”、“分离流误差”、“非均匀流场位移效应”、“标定成本”和“理论缺位”等问题，提出开展可用于超音速非均匀可压缩流体的球面绕流探测理论研究。发展超音速非均匀可压缩流体球面绕流激波位置参数化方案和流面分离位置参数化方案，并对参数化模型进行验证，构建参数化超音速非均匀可压缩流体球面绕流理论模型；建立球型多孔探针绕流理论模型参数反演计算方案，着重解决基于绕流理论模型的球面压力分布与自由流之间的边界积分关系问题，并在此基础上发展相应的模型参数反演计算方案；研究中层大气三维流场和涡度矢量场同步测量新方法，建立适用于箭载的球形探针三维流场测量模型和误差模型，箭载球形探针涡度场同步测量模型及其误差模型。实现箭载中层大气流场探测方法理论创新，为中层大气重力波稳定性理论观测验证，重力波转捩条件观测检验提供技术支撑。

为适应当前中层大气科学前沿问题研究对原位探测新技术的需求，提出研究箭载中层大气三维流场测量相关技术，探索三维流场和湍涡同步测量的可行性，为中层大气重力波稳定性理论观测验证， 重力波转捩条件观测检验提供技术支撑,为以微波临边扫描技术(microwave limb sounding, MLS)为代表的天基中层大气卫星遥感技术观测对比和定标提供技术支撑。.项目主要围绕任务书要求的内容开展研究，取得了如下成果: 基于球面绕流理论开展了超音速非均匀可压缩流体的探测方法理论研究。采用计算流体方法给出了研究所需的控制方程、网格划分方法和湍流模型，开展了不同形制多孔探针在不同速度和攻角的数值计算仿真，建立了218个工况数值样本库。针对多孔探针绕流场中的激波位置点、边界层稳定影响机制、转捩问题，建立了超音速非均匀可压缩流体球面绕流激波位置参数化方程、表面压强参数化方程，并对参数化方程进行数值验证。提出了球型多孔探针绕流理论模型参数反演计算方法，着重研究了球面压力分布与来流失量之间的关系问题，建立了三维流场测量新方法。结合中层大气应用环境，研究了箭载中层大气三维流场和涡度场同步测量方法，建立了适用于箭载的球形探针三维流场测量校准模型和误差模型、箭载球形探针涡度同步测量模型及其误差模型。分析比较了不同结构探针的优缺点及其结构参数对探针测量误差的影响，通过数值仿真得到最优探针头部结构。开展了半球形七孔探针新校准方法研究，建立了探针孔压和流场参数关联关系，给出了压-速参数化方程，并提出了参数反演方法，通过数值模拟和风洞实验对半球形七孔探针进行了校准比较，验证了有效性。设计研制了三坐标多向可旋转风洞测量系统，解决了探针风洞校准实验手段问题。.本研究完成了全部任务书内容，为中层大气重力波稳定性理论观测验证，重力波转捩条件观测检验提供了技术支撑。