Scaling of interaction lengths for hypersonic shock wave/turbulent boundary layer interactions

The interaction length induced by Shock Wave/Turbulent Boundary-Layer Interactions (SWTBLIs) in the hypersonic flow was investigated using a scaling analysis, in which the interaction length normalized by the displacement thickness of boundary layer was correlated with a corrected non-dimensional separation criterion across the interaction after accounting for the wall temperature effects. A large number of hypersonic SWTBLIs were compiled to examine the scaling analysis over a wide range of Mach numbers, Reynolds numbers, and wall temperatures. The results indicate that the hypersonic SWTBLIs with low Reynolds numbers collapse on the supersonic SWTBLIs, while the hypersonic cases with high Reynolds numbers show a more rapid growth of the interaction length than that with low Reynolds numbers. Thus, two scaling relationships are identified according to different Reynolds numbers for the hypersonic SWTBLIs. The scaling analysis provides valuable guidelines for engineering prediction of the interaction length, and thus, enriches the knowledge of hypersonic SWTBLIs.     

Study on UAV Path Planning Approach Based on Fuzzy Virtual Force

This article proposes a novel fuzzy virtual force (FVF) method for unmanned aerial vehicle (UAV) path planning in complicated environment. An integrated mathematical model of UAV path planning based on virtual force (VF) is constructed and the corresponding optimal solving method under the given indicators is presented. Specifically, a fixed step method is developed to reduce computational cost and the reachable condition of path planning is proved. The Bayesian belief network and fuzzy logic reasoning theories are applied to setting the path planning parameters adaptively, which can reflect the battlefield situation dynamically and precisely. A new way of combining threats is proposed to solve the local minima problem completely. Simulation results prove the feasibility and usefulness of using FVF for UAV path planning. Performance comparisons between the FVF method and the A* search algorithm demonstrate that the proposed approach is fast enough to meet the real-time requirements of the online path planning problems.     

Numerical simulation of compression corner flows at Mach number 9

A hypersonic vehicle encounters a wide range of conditions during its complete flight regime. These flight conditions may vary from low to high Mach numbers with varying angles of attack. The near-wall viscous dissipation associated with flows at combined high Mach and Reynolds numbers leads to significant wall heat transfer rates and shear stresses. The shock wave/boundary-layer interaction results in a flow separation region, which commonly augments total pressure losses in the flow and lowers the efficiency of aerodynamic control surfaces such as fins installed on a vehicle. The standard turbulence models, when used to resolve such flows, result in incorrect separation bubble size for large separated flows. Therefore, it results in an inaccurate aerodynamic load, such as the wall pressures, skin friction distribution, and heat transfer rate. In previous studies, the application of the shock-unsteadiness correction to the standard two-equation k-ω turbulence model improved the separation bubble size leading to an accurate pressure prediction and shock definition with the assumption of constant Prandtl number. In the present work, the new shock-unsteadiness modification to the k-ω turbulence model is applied to the hypersonic compression corner flows. This new model with variable Prandtl number is based on the model parameter, which depends upon the local density ratio. The computed wall pressures, heat flux and flow field are compared to the experimental data. A parametric study is carried out by varying compression deflection angles, free stream Reynolds number and wall temperatures to compute the flow field and wall data accurately, particularly in the shock boundary layer interaction region. The new shock-unsteadiness modified k-ω model with variable Prandtl number shows an accurate prediction of initial pressure rise location, pressure distribution in the plateau region and heat flux in comparison to the standard k-ω model.     

双脉冲发动机EPDM软隔层黏超弹本构模型

三元乙丙橡胶（EPDM）用于软隔层式双脉冲固体火箭发动机软质脉冲隔离装置（PSD）时,主要在Ⅰ脉冲工作时起到绝热抗烧蚀作用,同时保证Ⅱ脉冲能够可靠工作。根据橡胶类材料连续介质力学理论,建立了描述EPDM软隔层在有限变形下的黏超弹本构模型。模型由超弹部分和非线性黏弹性部分构成：超弹部分在Mooney-Rivlin模型的基础上进行了改进,使之能够描述大应变时的硬化现象;非线性黏弹性部分采用广义黏弹性模型,采用无量纲形式的KWW方程替代了传统的Prony级数,使得用2个参数就能预测较大应变率范围内的力学响应。利用万能材料实验机对EPDM软隔层进行了多步松弛实验和单轴等速率拉伸实验,然后根据实验结果,采用分步拟合的方法求出模型参数,利用所建立的本构模型对其余的实验结果进行预测并与实验结果进行比较,对比结果表明所建立的模型能较好地预测EPDM软隔层伸长比在800%以内的单轴等速拉伸响应。最后利用文献中的实验数据验证了所建立的模型能够较好地预测多种工况下的力学响应。     

翼型气动优化设计问题多极值特性研究

认识翼型气动外形优化问题设计空间的多极值特性,有助于人们在翼型设计阶段选择合理的优化算法,提高优化效率、缩短设计周期。研究RAE2822 翼型在优化减阻过程中设计空间的多极值特性,采用ADODGcase2算例,使用自由变形方法(FFD)对翼型进行参数化,通过拉丁超立方抽样方法对翼型加入初始扰动;使用基于梯度的优化算法对经过不同扰动后的翼型进行优化,并将优化结果与全局优化算法的优化结果进行对比。结果表明:ADODGcase2可能是一个单峰值气动设计问题,梯度算法能够得到相对满意的最优解,并且具有更高的优化效率;在给定面积约束的条件下,对于翼型跨声速单点减阻优化问题,设计空间很可能是单峰值的,可直接使用梯度优化算法。     

叶片弯曲对大折转压气机叶栅内分离结构的影响

通过数值模拟,分析了叶片周向弯曲对大折转角压气机叶栅内分离结构的影响。弯角分别为±10°,±20°,±30°。应用壁面流谱的拓扑法则,详细讨论了不同弯角下的分离形态。结果表明,正弯可以有效遏止角区分离,改变吸力面的分离形态,但不能完全消除吸力面的分离。因此一定范围内的叶片正弯可以改善流动,但当弯角大于20°时,流动重新恶化。反弯则使得叶栅内分离趋势增加,气动性能明显降低。     

飞行器突起物周围气动加热的计算方法

有压缩拐角区域的突起物的局部气动加热问题表现为流动的分离与再附。许多研究人员对这类突起物的气动加热问题做了大量的理论和实验研究。本文通过对其流动情况的分析，结合大量的实验数据，对压缩拐角区域气动加热问题，给出了一种有效的工程计算方法。     

斜激波串与上游激波干扰特性试验研究

为研究斜激波串在背压条件下前移与上游激波相互干扰的流场结构和运动规律,在来流为马赫数 2.7 的直管道内设计一种等宽度斜楔,采用动态压力测量、高速纹影和粒子图像测速(PIV)技术等手段进行了试验。研究结果表明：内置斜楔在管道内产生入射激波、分离激波、膨胀波、再附激波和激波诱导分离等复杂上游激波流场,在分离区附近形成有顺压梯度和逆压梯度的区域。当增大下游压比时,斜激波串逐渐向上游激波流场移动;经过斜楔产生的分离区时,斜激波串的移动速度急剧提升,同时出现非对称分离偏转方向的切换。对比了三种长度尺寸的等楔角斜楔所产生的上游激波流场的差异性,发现在相同的斜楔前缘起始点和楔角时,随着斜楔长度的增加,上游激波流场中激波诱导的分离尺度逐渐变大。     

多星分离速度设计

针对多量分离过程对星间最小间距的要求,运用Ｈｉｌｌ方程,对其相对运动进行了分析,提出了一种分离速度设计方法,讨论了最小间距最大化问题,并给出了最小间距最大的等 条件,最后,针对一箭五星情况进行了仿真计算,结果表明,该方法简单、有效,最小间距的最大值明显大于设计要求值,这就分离速度的设计、选择提供了很大的余地。     

基于小波变换和不变矩的车标识别方法

形状特征是目标识别的重要参数,小波变换的低频部分代表物体的总体形状特征,而图像中的噪声主要分布于高频部分。根据这一特征,利用小波变换消除噪声提取目标形状,进而利用特征不变矩距离进行分类,实现目标识别,将该方法应用在实测车标图像的识别中,结果表明识别效果较好。