高超声速飞行器气动防热新概念研究

传统乘波构型的高超声速飞行器尖锐的前缘存在严重的气动加热问题,而简单的前缘钝化气动防热方法由于造成很大的升阻比损失,难以发挥实质性作用. 引入``人工钝前缘(ABLE)'概念,拟以一种新的思路解决这一矛盾. 通过定义ABLE构型的外形参数,并采用CFD数值计算方法研究了各参数对气动力和气动热特性的影响规律,在流场分析的基础上进行了外形优化,最终得到令人满意的新型高超声速飞行器头部外形,总结了运用ABLE概念进行气动防热的相关设计原则和规律.      

给定前缘线平面形状的密切锥乘波体设计方法

乘波体因其高超声速阶段的高升阻比性能成为目前研究的热点,但其本身的诸多性能缺陷限制了其在工程中的实际应用. 密切锥乘波体设计 是目前应用较广的乘波体外形设计方法,具有较高的灵活性和生成效率. 本文以弥补乘波体性能缺陷,提高乘波体设计灵活性为目的, 拓展了密切锥乘波体设计方法,推导设计方法中激波出口型线、流线追踪起始线与平面形状轮廓线之间的几何关系,并使用一个微分方程 组给出了具体的数学表达,奠定了定平面形状乘波体设计的理论基础. 通过介绍此微分方程组的数值求解过程,并分析应用此关系的注意 事项,本文提出了给定前缘线平面形状的密切锥乘波体设计方法. 根据此设计几何关系,以渐变前缘、弯曲前缘和双后掠等为例生成定平 面形状乘波体外形,结合计算流体力学方法分析这几类外形的流场,通过流场分布与设计曲线的比较,说明通过此方法设计得到的乘波体 外形保持了高超声速状态的乘波特性,并可以方便的控制平面形状,为提高乘波体的设计灵活性、改善性能缺陷提供了新的途径.      

Superorbital expansion tube tests of a caret waverider

A computational and experimental study was conducted to assess the potential of testing waverider configurations in a high-performance, short-duration expansion tube facility. The tests were performed in the newly commissioned X3 superorbital expansion tube and provide the first experimental data of a waverider tested at a stagnation enthalpy and equivalent flight speed exceeding 40 MJ/kg and 9 km/s, respectively. Two simple caret configurations were chosen as benchmark test cases to test the use of the facility, instrumentation and numerical models to investigate these flows. The general performance of the sharp and blunt leading edge waveriders at angles of attack ranging from 0° to 5° were analyzed and compared to CFD and theoretical predictions. For the conditions tested, the presence of a strong viscous interaction caused the shock wave to be detached from the leading edge of the models resulting in a significant loss in performance. An analytical model was developed to account for the strong coupling between the shock wave and boundary layer. Results were shown to be in very good agreement with CFD estimates for both configurations at all angles of attack considered. Finite-rate chemistry CFD simulations indicated that real gas effects other than the residual levels of nonequilibrium freestream dissociation present in the expansion tube flow were negligible for the conditions tested. The study also revealed that a past flow visualization technique gave a false indication of the leading edge shock location. An improved experimental visualization technique was successfully tested with results from these tests correlating well with computational estimates. This study successfully demonstrated the use of the facility to study waverider performance at speeds representative of orbital flight.      

涡波一体乘波飞行器宽速域气动优化设计研究

涡波一体宽速域乘波飞行器通过在低速引入涡效应,显著改善了传统乘波体在低速状态下的升阻特性,具有在未来宽速域空天飞行器总体气动设计当中得到广泛应用的巨大潜力.但是,该设计方法的研究尚不完善,特别是在基准流场建立过程中忽略了三维效应、低速效应、黏性效应以及头部/前缘的钝化效应,因此其高低速气动特性均有优化设计的空间.针对此问题,本文结合高保真RANS求解器、自由变形参数化方法、鲁棒的结构网格变形方法、离散伴随方法以及序列二次规划算法,发展了基于离散伴随的宽速域飞行器气动优化设计方法.基于上述方法,针对涡波一体乘波飞行器开展了兼顾低速与高超声速气动性能的三维整机气动优化设计研究,获得了宽速域优化构型并对其进行了流动机理分析.结果表明,相较于初始构型,宽速域优化构型可以将飞行器高超声速状态下升阻特性略微提升的同时,显著增强低速状态飞行器背风面的旋涡效应,进而使飞行器低速状态的升力和升阻比均提升10%以上,改善了涡波一体宽速域乘波飞行器的高低速气动性能.     

乘波体前体/进气道一体化设计研究

为了研究乘波体几何外形参数和飞行参数对前体/进气道一体化设计的影响,采用理论分析和数值模拟相结合的方法,以马赫数Ma=6和攻角α=0为设计状态、进气道总压恢复系数和前体阻力系数为目标函数,对乘波体前体/进气道进行了优化设计,并在此基础上研究了攻角、马赫数、前缘半径、前体宽度对气动参数的影响。结果表明:该乘波体前体/进气道构型具有良好的攻角特性,总压恢复系数比基准构型提高17.79%,阻力系数比基准构型降低78.5%,符合高超声速飞行器高升力、低阻力的要求,且非常适合小攻角高超声速巡航飞行;为了得到较高升阻比的前体,在前缘半径R≤2mm的范围内进行流场反设计时,可以将设计马赫数的取值比预期低一些。     

上下反翼对双后掠乘波体低速特性的影响

相比于传统乘波体外形, 双后掠乘波体在保持高超声速良好性能的条件下能够提升乘波体低速气动性能, 但其仍存在低速稳定性不好等缺陷. 本文从密切锥乘波体理论提出给定前缘型线的乘波体设计方法, 通过给定三维前缘型线分别生成具有相同平面投影形状的上反和下反机翼双后掠乘波体. 使用CFD技术评估不同上下反程度外翼乘波体的低速性能, 分析升阻特性以及流场涡结构特点. 选取稳定性判据, 研究上下反翼对纵向和横侧向稳定性的影响. 结果表明, 机翼上下反对乘波体低速升阻特性影响较小; 不同外形均为纵向静不稳定的, 且俯仰力矩变化趋势比较类似, 机翼下反可使气动焦点位置后移, 提升纵向稳定性; 机翼上反有助于提升乘波体的横向静稳定性, 而下反则会下降; 机翼上反可以提升侧向稳定性, 且上反程度越大提升效果越明显; 同时机翼上反使乘波体的偏航动态稳定性有明显提升, 下反则会降低, 影响程度与机翼上下反程度呈正相关. 通过结果分析, 说明通过机翼上下反改善乘波体低速稳定性是可行的, 为乘波体在宽速域高超声速飞行器中的应用拓展了途径.      

基于局部偏转吻切方法的多级压缩乘波体设计

乘波体因优异的气动特性,被认为是突破现有"升阻比屏障"的有效途径之一,已成为高超声速飞行器气动设计的研究热点.针对常规单级压缩乘波前体压缩量不足的问题,基于局部偏转吻切方法提出一种多级压缩乘波体设计方法,实现了多道非轴对称激波的逆向乘波设计.通过引入多道非轴对称激波,可充分发挥乘波前体的预压缩效果,并为复杂外形条件下的...     

乘波体压缩面变化对其气动性能影响分析

乘波体是一种利用激波包裹特性获得高升阻比的高速飞行器构型.已有研究中,乘波体气动性能的改善主要依赖于给定源流场条件下的前缘型线优化.本文采用数值优化和计算流体力学模拟为主要手段分析了乘波体压缩面变化对其气动性能的影响,以期有效拓展乘波体的设计空间.主要内容如下:首先给出了一种基于表面局部变形的乘波体设计方法.其次结合运用增量修正参数化方法、计算流体力学分析和微分演化算法构造了乘波体压缩面外形气动优化设计流程,以一种椭圆锥形流场生成的乘波体作为基准构型开展了无黏优化.之后从优化结果中选择升阻比递增的6个典型构型进行前缘钝化处理后,基于N-S方程对其气动性能进行了评估.最后综合依据无黏/黏性计算结果分析了乘波体压缩面变化对其气动性能的影响.结果表明该部分形状的改变对乘波体气动性能影响十分明显,在升力面积不变的条件下,乘波体压缩面形状变化可导致其升阻比出现成倍变化,即使在升力不减条件下,升阻比较基准构型也可获得超过14%的提升.此外,还可导致乘波体相对压心系数出现明显偏移.     

高升阻比乘波构型优化设计

在M∞ =6, 30km高空条件下，以升阻比为目标函数，进行了锥形流乘波体的黏性优化设计，讨论 了影响乘波体升阻比的因素，并对优化结果进行了数值验证. 结果表明：对于升阻比最大的 黏性优化乘波体，存在最优圆锥角使得源自该基本流场的乘波体升阻比最大；摩阻和波阻处 于同一量级；体积率、细长比和展长比都随着基本流场圆锥角的增大而增大.     

Notes on gas–dynamic design of supersonic flying vehicles

It is shown that the lift–to–drag ratio of a thin delta wing is significantly lower than the lift–to–drag ratio of an infinitely long swept plate with an identical lift force. The effect of sweep on a finite wing may be used by excluding disturbances from the leading edge of the wing via introducing a hardened stream surface (wedge) and increasing the wing length. A three–shock waverider is proposed for choosing the optimal parameters. The sharp wedge may be avoided by replacing planar shock waves by a cylindrical shock wave upstream of the blunted wedge. If the leading edge of the wedge is not parallel to the rib that is a source of the expansion wave, a plate with zero wave drag, generating a lift force, may be obtained behind this rib. The system of regularly intersecting shock waves may be applied to design a forward–swept wing.     

Stabilization of flow over an attachment line using a near-wall body force

The problem of the control of steady flow in the vicinity of the attachment line on the leading edge of a swept wing is considered. It is assumed that the control is realized by means of near-wall body force action for the purpose of increasing the flow stability. The stability problem is solved under the assumption of the streamwise homogeneity of the undisturbed three-dimensional flow. The dependence of the stabilizing effect on the action amplitude and the width of the region, where the near-wall force is applied, is studied.     

Relation between the Hydrodynamic and Elastic Parameters in Surface Wave Diffraction on a Floating Plate

The problem of surface wave diffraction on a floating elastic plate is considered. The relation between the parameters of the elastic vibrations of the plate and the transmitted and reflected wave amplitudes is investigated. It is shown that the maximum amplitudes of the plate stresses and deflections depend nonmonotonically on the incident wave frequency and are reached simultaneously with the maxima of both the transmission coefficient and the length of the wave penetrating into the plate. This makes it possible to use the transmission coefficient as a parameter for investigating the maximum and minimum amplitudes of the hydroelastic vibrations of the plate. As an example, this criterion is used to minimize the vibrations of a plate whose leading edge is elastically connected to the bottom.     

Drag of a Plate Planing on the Shallow Water with Formation of Waves

The plane problem of the plate planing at a constant velocity on the surface of a heavy, ideal, incompressible, finite-depth fluid is considered. The approximate, depth-independent expression for the force acting on the plate is derived from the linear distribution of the fluid velocity along the plate and the height of the flow stagnation point, without regard for jet formation near the leading edge. In this approximate formulation the plate drag depends on its velocity and the trailing edge immersion and does not depend on the planing angle. Experiments and numerical calculations in the exact formulation are performed in the near-critical flow regimes. It is shown that the wave patterns in the experiments and numerical calculations coincide, the formula for the drag being in agreement with the numerical experiments. An approximate criterion of the formation of waves going away from the plate in the forward direction is proposed.     

Flow along an attachment line controlled by a near-wall body force

The problems of the control of steady three-dimensional viscous incompressible flows modeling the gas flow in the vicinity of the attachment line on the leading edge of a swept wing are considered. It is assumed that the control is realized by means of the body force action approximating the action of a periodic sequence of plasma actuators mounted perpendicular to the leading edge. The corresponding boundary value problems for the system of Navier–Stokes equations are numerically solved using the Fourier method along the longitudinal coordinate and second-order difference approximation in the vertical coordinate. An important role played by the control-induced pressure gradient is shown.     

Excitation of controllable perturbations in the three-dimensional boundary layer using plasma actuators

Two versions of the structure of a multi-discharge plasma actuator intended to excite boundary layer perturbations in the neighborhood of the leading swept-wing edge are suggested. The actuator must prevent from appearance and development of the crossflow instability modes leading to laminarturbulent transition under the normal conditions. In the case of flow past a swept wing, excitation of controllable perturbations by the plasma actuator is simulated numerically in the steady-state approximation under the typical conditions of cruising flight of a subsonic aircraft. The local body force and thermal impact on the boundary layer flow which is periodic along the leading wing edge is considered. The calculations are carried out for the physical impact parameters realizable in the near-surface dielectric barrier discharge.     

高超声速钝前缘乘波构型优化设计研究

乘波体的高升阻比优势使其在高超声速飞行器设计中极具应用前景. 在实际工程应用中, 为了满足防热要求, 乘波体前缘必须进行钝化处理, 前缘钝化对乘波体气动性能会产生显著影响. 因此, 原始尖前缘最优乘波体并不能保证钝化后仍为最优. 针对这一问题, 首先研究了前缘钝化对不同构型升阻特性的影响程度和作用机理. 结果表明: 前缘钝化会造成乘波体升力小幅度降低, 阻力大幅增加, 升阻比显著降低; 其中钝前缘本身的波阻在阻力增量中起主导作用, 而钝前缘本身的摩阻增加量与物面的摩阻降低量十分接近. 基于上述结果, 提出了一种高效评估钝前缘乘波体气动力的方法, 并结合遗传算法, 开展了直接考虑前缘钝化影响的乘波构型优化设计研究, 获得了钝前缘最优构型. 通过CFD数值模拟对最优构型的气动力特性进行评估, 结果表明: 在不同飞行高度、不同升力和不同钝化半径约束下, 相比尖前缘最优构型, 钝前缘最优构型宽度变窄, 相同纵向位置处的后掠角增大, 且升阻比显著提升. 在M_∞ = 15, H = 50 km, CL = 0.3约束条件下, 钝化半径R = 10 mm的钝前缘最优构型设计点升阻比相比尖前缘最优构型提升量可达9.32%.      

Effect of interface stresses on the image force and stability of an edge dislocation inside a nanoscale cylindrical inclusion

Dislocation mobility and stability in inclusions can affect the mechanical behaviors of the composites. In this paper, the problem of an edge dislocation located within a nanoscale cylindrical inclusion incorporating interface stress is first considered. The explicit expression for the image force acting on the edge dislocation is obtained by means of a complex variable method. The influence of the interface effects and the size of the inclusion on the image force is evaluated. The results indicate that the impact of interface stress on the image force and the equilibrium positions of the edge dislocation inside the inclusion becomes remarkable when the radius of the inclusion is reduced to nanometer scale. The force acting on the edge dislocation produced by the interface stress will increase with the decrease of the radius of the inclusion and depends on the inclusion size which differs from the classical solution. The stability of the dislocation inside a nanoscale inclusion is also analyzed. The condition of the dislocation stability and the critical radius of the inclusion are revised for considering interface stresses.     

Two kinds of contact problems in three-dimensional icosahedral quasicrystals

Two kinds of contact problems, i.e., the frictional contact problem and the adhesive contact problem, in three-dimensional(3D) icosahedral quasicrystals are discussed by a complex variable function method. For the frictional contact problem, the contact stress exhibits power singularities at the edge of the contact zone. For the adhesive contact problem, the contact stress exhibits oscillatory singularities at the edge of the contact zone. The numerical examples show that for the two kinds of contact problems, the contact stress exhibits singularities, and reaches the maximum value at the edge of the contact zone. The phonon-phason coupling constant has a significant effect on the contact stress intensity, while has little impact on the contact stress distribution regulation. The results are consistent with those of the classical elastic materials when the phonon-phason coupling constant is 0. For the adhesive contact problem, the indentation force has positive correlation with the contact displacement, but the phonon-phason coupling constant impact is barely perceptible. The validity of the conclusions is verified.     

玉米根茬剪切力学性能试验与分析

为提高免耕播种机破茬刀的工作性能,需要分析剪切速度、切刀刃型及剪切方式对根茬剪切性能的影响规律,采用微机控制电子万能试验机对玉米根茬进行上述三因素随机区组剪切性能试验。结果表明:剪切方式对最大剪切力的影响最大,其次是剪切速度;切刀刃型对最大剪切力的影响较小;最大剪切力随着剪切速度的增大而减小;同一刃型切刀在相同剪切速度下,横切时最大剪切力最大,劈切时最大剪切力最小;同一剪切方式在相同剪切速度下,直刃切刀的最大剪切力最大,凸圆刃切刀的最大剪切力最小;不同剪切方式,切茬过程的负荷-变形曲线不同。     

Features of the turbulent flow around symmetric elongated bluff bodies

The flow fields around three elongated bluff bodies with the same chord-to-thickness ratios but distinct leading and trailing edge details were measured at a Reynolds number of 3×10⁴. These models each represent a case where: leading edge shedding dominates, trailing edge shedding dominates and a case where there is a balance between the two. The results show that the vortex street parameters vary between the models, and in particular, the shedding frequencies are significantly altered by the geometry. However, contrary to the current understanding for shorter bluff bodies, the scale of the recirculation region is found to be similar for each model, even though the shedding frequency changes within the range from 0.15 to 0.24. Also, the base pressure does not follow trends with shedding frequency expected from shorter bluff bodies. A force balance of the recirculation region shows that the near wake of each body is significantly affected by the Reynolds shear stress distribution and the resultant force due to the pressure field in the mean recirculation region. These differences infer that the distinct vortex formation characteristics depend on the state of the trailing edge shear layers. The boundary layers at the trailing edge have been quantified, as have the leading edge separation bubbles, and the marked differences in the wake details are shown to depend on the leading edge separation.