Low-frequency unsteadiness of vortex wakes over slender bodies at high angle of attack

A type of flow unsteadiness with low frequencies and large amplitude was investigated experimentally for vortex wakes around an ogive-tangent cylinder. The experiments were carried out at angles of attack of 60–80 and subcritical Reynolds numbers of 0.6–1.8×105. The reduced frequencies of the unsteadiness are between 0.038 and 0.072, much less than the frequency of Karman vortex shedding. The unsteady flow induces large fluctuations of sectional side forces. The results of pressure measurements and particle image velocimetry indicate that the flow unsteadiness comes from periodic oscillation of the vortex wakes over the slender body. The time-averaged vortex patterns over the slender body are asymmetric, whose orientation is dependent on azimuthal locations of tip perturbations. Therefore, the vortex oscillation is a type of unsteady oscillation around a time-averaged asymmetric vortex structure.     

Multi-infill strategy for kriging models used in variable fidelity optimization

In this paper, a computationally efficient optimization method for aerodynamic design has been developed. The low-fidelity model and the multi-infill strategy are utilized in this approach. Low-fidelity data is employed to provide a good global trend for model prediction, and multiple sample points chosen by different infill criteria in each updating cycle are used to enhance the exploitation and exploration ability of the optimization approach. Take the advantages of low-fidelity model and the multi-infill strategy, and no initial sample for the high-fidelity model is needed. This approach is applied to an airfoil design case and a high-dimensional wing design case. It saves a large number of high-fidelity function evaluations for initial model construction. What’s more, faster reduction of an aerodynamic function is achieved, when compared to ordinary kriging using the multi-infill strategy and variable-fidelity model using single infill criterion. The results indicate that the developed approach has a promising application to efficient aerodynamic design when high-fidelity analyses are involved.     

Wing optimization of propeller aircraft based on actuator disc method

Propeller aircraft are widely used in general aviation. The rotating propeller has a strong effect on the aerodynamic performance of the wing. This paper uses an actuator disc to model the effect of the propeller. A wing optimization method is developed with the actuator disc method. Several wing optimizations with different slipstream settings are studied. The twist angle and airfoils of the wing are used as the design variables. The results show that the propeller slipstream and slipstream directions have a strong influence on the optimization process. Powered-on optimization with a slipstream can obtain better drag reduction results than unpowered optimization. The drag decomposition results show that most of the drag reduction comes from the form drag reduction. The symmetric “inboard-up” slipstream configuration is found to have the highest lift-to-drag ratios, which are 18.87 for the twist angle optimization and 19.15 for the airfoil optimization.     

火星稀薄大气参数对进入器气动特性的影响

针对火星稀薄大气环境的不确定性对进入器气动特性的影响问题,先以海盗号火星进入器的飞行试验数据对发展的三维并行直接模拟蒙特卡罗(DSMC)仿真软件进行了算例校验,再以火星科学实验室外形为例,计算气体组分、密度、温度及速度等来流参数的不确定性对进入器气动特性的影响偏差,定性定量给出火星高空稀薄环境下大气不确定性所带来的气动力特性规律。研究结果表明,通过与海盗号飞行实验数据的对比校验了所建立方法的正确性与可靠性;CO2大气环境对进入器气动特性的影响较大,利用空气稀薄环境中的计算及实验结果亦需进行CO2效应修正,这一点与连续流区的结论一致;来流密度及速度的不确定性对气动力、力矩特性均有影响,而来流温度影响的最大偏差小于0.5%;纵向压心对来流密度、温度及速度的扰动均不敏感。     

Aerodynamic characteristics of morphing wing with flexible leading-edge

The morphing wing can improve the flight performance during different phases. However, research has been subject to limitations in aerodynamic characteristics of the morphing wing with a flexible leading-edge. The computational fluid dynamic method and dynamic mesh were used to simulate the continuous morphing of the flexible leading-edge. After comparing the steady aerodynamic characteristics of morphing and conventional wings, this study examined the unsteady aerodynamic characteristics of morphing wings with upward and downward deflections of the leading-edge at different frequencies. The numerical results show that for the steady aerodynamic, the leading-edge deflection mainly affects the stall characteristic. The downward deflection of the leading-edge increases the stall angle of attack and nose-down pitching moment. The results are opposite for the upward deflection. For the unsteady aerodynamic, at a small angle of attack, the transient lift coefficient of the upward deflection, growing with the increase of deflection frequency, is larger than that of the static case. The transient lift coefficient of the downward deflection, decreasing with the increase of deflection frequency, is smaller than that of the static case. However, at a large angle of attack, an opposite effect of deflection frequency on the transient lift coefficient was demonstrated. The transient lift coefficient is larger than that of the static case when the leading edge is in the nose-up stage, and lower than that of the static one in the nose-down stage.     

细长飞行器的气动弹性发散分析

本文从下列两方面推广文献[1]中的二升力火箭弹体气动弹性发散分析:一是把两个集中升力扩大到任意个集中升力;二是计及空气动力干扰效应。     

气动辅助空间交会最优轨道设计与闭环导引律

给出了同平面HEO-LEO实现空间交会的必要条件;研究了基于气动辅助轨道转移技术实现同平面HEO-LEO的空间交会方案,通过设计一条标准的同平面HEO-LEO气动辅助轨道转移的最优轨迹,得到了轨道转移飞行器(OTV)与目标实现交会必须满足的标准相角;最后对大气飞行段设计了非线性最优闭环导引律,通过引入Lyapunov最陡下降函数,对函数中相应参数进行适当调整,使应用闭环导引律得到的大气内飞行轨迹与最优轨迹充分接近,仿真结果表明该气动辅助空间交会方法正确、可行。     

火星无人机实验台发展综述及构想

火星地表崎岖、环境复杂,火星无人机由于其具有高机动性和灵活性,为火星探测提供了一种新的工作模式,是未来深空探测的重要范式。本文对比了火星与地球相关地表环境参数的差异,分析了火星无人机需要克服的困难和主要用途,阐明了火星无人机实验台的重要性;详细介绍了国内外研究机构研发火星无人机实验台的技术特点与功能优劣,总结了实验台需要具备的模拟火星环境和测量相关参数。在此基础上,提出了构建火星无人机实验台设想,给出了总体设计思想和思路,并对火星无人机气动力学实验平台的应用前景进行了展望。     

用Schamberg方法计算卫星阻力系数

Schamberg的“超热自由分子流”粒子-表面作用模型比较真实地反映了高空大气分子与空间飞行器材料之间的相互作用,它可以用来计算卫星的阻力系数。本文简要叙述该模型的基本思想,介绍几种常见简单几何形体卫星的阻力系数计算公式,并给出计算曲线。     

Investigation of acceleration effects on missile aerodynamics using computational fluid dynamics

In this paper we describe the implementation and validation of arbitrarily moving reference frames in the block-structured CFD-code EURANUS. We also present results from calculations on two applications involving accelerating missiles with generic configurations. It is shown that acceleration affects wave drag significantly. Also, it is shown that strake-generated vortices move significantly in turns. These results clearly show the necessity of including the acceleration effects in the calculations.