尖化前缘的稀薄气体化学非平衡流动和气动加热相似律研究

以近空间尖前缘高超声速巡航飞行器的研制为背景, 作者在前一阶段采用模型理论分析方法, 陆续研究了沿微钝前缘驻点线的化学非平衡流动和气动加热相似律, 文章是上述研究的综合回顾和深化讨论.稀薄条件下, 驻点附近流动和传热出现一系列与连续流动模型不同的新特征, 超出了经典气动热预测理论的适用范围.作者建立了一个沿驻点线能量传递和转化的广义模型, 并分别推导了具有实际物理意义的边界层外离解非平衡流动判据和边界层内复合非平衡流动判据.基于这些判据构建了预测非平衡流动驻点气动加热的桥函数, 并讨论了稀薄非平衡真实气体流动和气动加热的相似律, 发现新型近空间尖前缘飞行器遭遇的气动热环境不同于传统大钝头航天器再入问题, 传统的天地换算相似准则将会失效.这些理论分析结果可为稀薄非平衡化学反应流及气动加热的实验和计算提供一个标模检验的手段.      

Mechanism of unsteady aerodynamic heating with sudden change in surface temperature

The characteristics and mechanism of unsteady aerodynamic heating of a transient hypersonic boundary layer caused by a sudden change in surface temperature are studied. The complete time history of wall heat flux is presented with both analytical and numerical approaches. With the analytical method, the unsteady compressible boundary layer equation is solved. In the neighborhood of the initial and final steady states, the transient responses can be expressed with a steady-state solution plus a perturbation series. By combining these two solutions, a complete solution in the entire time domain is achieved. In the region in which the analytical approach is applicable, numerical results are in good agreement with the analytical results, showing reliability of the methods. The result shows two distinct features of the unsteady response. In a short period just after a sudden increase in the wall temperature, the direction of the wall heat flux is reverted, and a new inflexion near the wall occurs in the profile of the thermal boundary layer. This is a typical unsteady characteristic. However, these unsteady responses only exist in a very short period in hypersonic flows, meaning that, in a long-term aerodynamic heating process considering only unsteady surface temperature, the unsteady characteristics of the flow can be ignored, and the traditional quasi-steady aerodynamic heating prediction methods are still valid.     

高超声速飞行器前驻点热流数值模拟的物理准则研究

通过建立高超声速飞行器前驻点处沿驻点线的准一维流简化模型,再将头激波后流场分为无粘区和近壁粘性区,然后从N-S方程组出发,利用流场对称性和量级分析方法,最终推导出驻点邻域简化控制方程组,并证明了其流动具有边界层型特征．在此基础上,根据该控制方程组,给出了计算结果应满足的壁面驻点以及沿驻点线的相容关系,成为热流CFD计算准确与否应遵循的物理准则．最后通过算例验证了物理准则作为热流CFD计算可靠性判据的正确性．     

壁温变化非定常气动加热机理研究

研究了高超声速平板边界层因壁温时变引发的非定常气动热环境特征及机理.通过近似解析和数值模拟两种手段,得到了壁面热流随时问变化的完整过程.解析手段求解非定常可压缩边界层方程,将非定常响应表达成稳态解加上摄动级数的形式,在初始和最终稳态邻域分别求解,在适当的位置进行拼接,从而得到整个时间域上的解.在满足解析解假设的区域,数值结果与解析结果吻合较好,证明了所使用方法的可靠性.结果表明,非定常响应有两点显著特征:在壁温突然增加后短时间内,壁面热流方向改变,热边界层剖面在壁面附近出现了另一个拐点,这种新的剖面形状是典型的非定常特征.但是,高超声速情况下此种非定常响应存在的时间却很短,在考虑长时间气动加热的情况下,若只存在壁面温度时变的诱因,可以忽略流动中的非定常过程,当作准定常情况来处理.     

VISCOELASTIC CONSTITUTIVE MODEL RELATED TO DEFORMATION OF INSECT WING UNDER LOADING IN FLAPPING MOTION

Flexible insect wings deform passively under the periodic loading during napping flight. The wing flexibility is considered as one of the specific mechanisms on improving insect flight performance. The constitutive relation of the insect wing material plays a key role on the wing deformation, but has not been clearly understood yet. A viscoelastic constitutive relation model was established based on the stress relaxation experiment of a dragonfly wing (in vitro). This model was examined by the finite element analysis of the dynamic deformation response for a model insect wing under the action of the periodical inertial force in flapping. It is revealed that the viscoelastic constitutive relation is rational to characterize the biomaterial property of insect wings in contrast to the elastic one. The amplitude and form of the passive viscoelastic deformation of the wing is evidently dependent on the viscous parameters in the constitutive relation.     

高超声速分离-再附流动峰值热流的模型理论

具有大尺度分离区的高超声速分离-再附流动中会在再附点后产生极大的热流峰值.通过分析再附点后局部区域的流动和传热特征,提出了斜驻点-三层结构模型理论框架.继而将此理论框架应用于中低Reynolds数的高超声速压缩拐角流动,提出了其再附点局域流动的外缘参数的工程求解方案,给出了对应的峰值热流值,并与数值计算结果做了对比验证.最后,利用该理论研究了分离区的大小和分离时边界层的厚度对峰值热流的影响规律.      

Physical criterion study on forward stagnation point heat flux CFD computations at hypersonic speeds

In order to evaluate uncertainties in computational fluid dynamics （CFD） computations of the stagnation point heat flux, a physical criterion is developed. Based on a quasi-one-dimensional hypothesis along the stagnation line, a new stagnation flow model is applied to obtain the governing equations of the flow near the stagnation point at hypersonic speeds. From the above equations, the compatibility relations are given at the stagnation point and along the stagnation line, which consist of the physical criterion for checking the accuracy in the stagnation point heat flux computations. The verification of the criterion is made with various numerical results.     

高超声速压缩拐角峰值热流位置预测模型研究

旨在通过建立高超声速压缩拐角流动的再附点附近的模型理论来揭示峰值热流的产生机理以及如何可靠预测其位置.首先,分析再附点附近流动特征,提出了基于可压缩斜驻点流动模型来近似该处的局部流动.其次,近似求解了该流动模型,发现边界层厚度存在极小值的特征,从而揭示了再附点后峰值热流的产生机理,并由此得到了再附点和峰值热流点间距离的半解析半数值估算方法.最后,对此结果作了数值验证,并做了讨论.      

昆虫翼拍动中受载变形的粘弹性本构模型

昆虫翼拍动受载时发生被动变形,被看作为有助于改善飞行性能的机制之一．决定这种被动变形大小的一个关键因素是昆虫翼的材料本构关系,至今缺乏研究．基于蜻蜓翼(离体)的应力松弛实验和模型翼拍动时受载变形的有限元数值分析,揭示了粘弹性本构关系是昆虫翼材料性能的合理描述,并研究了粘弹性参数对被动变形的影响．     

具有局部稀薄气体效应的高超声速尖锥气动加热特征研究

以微钝尖锥为飞行器前缘模型,采用基于分子运动论的DSMC方法模拟不同前缘曲率半径的尖锥在高超声速来流下的气动热环境,计算驻点热流率,并与Fay-Riddell公式和其他修正理论作对比,研究具有局部稀薄气体效应的高超声速尖锥气动加热特征及其变化规律.发现修正的Cheng参数适合作为工程上判断驻点区域稀薄气体效应影响大小的判据.