超声速流中壁板颤振的抑制和地面试验研究

发布时间：2018-04-19 10:11

本文选题：壁板颤振 + 形状记忆合金　；参考：《哈尔滨工业大学》2017年博士论文

【摘要】：壁板颤振是一种自激振动现象,它是壁板在惯性力、弹性力以及气动力相互耦合作用下产生的。随着飞行器飞行马赫数的提高,气动热效应变得越来越显著。温度升高会引起壁板面内的热应力以及热力矩,这会影响壁板的气动弹性稳定性。因此在分析超声速或高超声速下壁板的颤振问题时,就必须要考虑气动加热对壁板稳定性的影响。近些年来,智能材料被广泛地应用于壁板的主动控制或被动控制。目前壁板地面颤振实验的相关研究仍然较少。为此,本文主要针对以下几个问题展开研究:采用Kirchhoff经典板理论、von-Karman非线性位移应变关系以及Hamilton原理建立了超声速流中复合材料壁板运动的偏微分方程。采用三阶非线性活塞理论模拟气动力,并采用Galerkin方法获得了壁板运动的常微分方程。研究了壁板在气动载荷和热载荷联合作用下的稳定性边界。采用频域分析方法研究了壁板弯曲固有频率、临界热屈曲温度和临界颤振动压。分析了气动非线性项对发生颤振时极限环振动幅值的影响。研究了壁板温度、长宽比和铺设角度对颤振边界的影响。采用在复合材料层合板中铺设形状记忆合金的方法对壁板颤振以及热屈曲实施抑制。采用Kirchhoff经典板理论模拟壁板位移,采用von-Karman大变形理论描述壁板非线性位移-应变关系,壁板表面所承受的气动力采用三阶活塞非线性理论来描述,采用一维Brinson热力学模型描述形状记忆合金产生的回复力。铺设形状记忆合金壁板的运动偏微分方程组由Hamilton原理建立,随后通过Galerkin离散法得到系统运动的常微分方程组,建立了一种研究铺设形状记忆合金壁板气动热弹性问题的新方法。采用非线性理论分析了系统的稳定性区域和颤振边界。研究了形状记忆合金的铺设角度、铺设位置、份数、预应变和温度对壁板热屈曲和颤振抑制效果的影响。研究了高超声速气流中三维复合材料层合板的非线性气动弹性-气动热耦合问题,构建了壁板温度随飞行高度、气流密度和飞行速度等环境参数的函数。建模过程中采用Ecker's参考温度方法计算气动力所产生的气动加热,壁板内的瞬态热传导方程由差分方法求解,采用三阶非线性活塞理论模拟气动压力,实现了气壁板动弹性-气动热耦合分析。数值分析中考虑了斜激波前后参数对气流参数、临界颤振动压和极限环振动幅值的影响,计算了壁板在气动弹性-气动热耦合作用下的时域响应。提出了一种新的壁板地面颤振试验方法。给出了缩减分布式非定常气动力为集中力的方法。试验研究和数值计算对象为一块四边简支薄铝板。采用三阶非线性活塞理论模拟超声速壁板的非定常气动力。试验过程中应用d Space控制系统实时采集并分析壁板某几个点的位移和速度信息,然后计算所需要产生的气动力并且施加于激振器。采用激光位移传感器测量壁板最大位移点处的振动响应,来判断壁板所处于的运动状态。数值分析中应用Hamilton原理、Galerkin离散方法和Rung-Kutta法对壁板的非线性动力学响应进行分析。最后对试验和数值计算结果进行分析对比,包括壁板临界颤振动压以及极限环振动幅值。
[Abstract]:Panel flutter is a self-excited vibration phenomenon, it is siding in the inertial force, elastic force generated and aerodynamic coupling. With the flight of Maher number increase, the aerodynamic heating effect becomes more and more significant. The temperature will cause the wall surface in the thermal stress and thermal moment, this will affect the panel the aeroelastic stability. Therefore the analysis of supersonic or hypersonic panel flutter problem, we must consider the influence of aerodynamic heating on the wall stability. In recent years, active control of intelligent materials have been widely used in panel or passive control. The related research panel flutter experiment ground is still small. Therefore in this paper, the following problem: the Kirchhoff von-Karman classical plate theory, the nonlinear displacement strain relation and Hamilton principle established in supersonic flow composite material The partial differential equation of panel movement. By simulation of three order nonlinear aerodynamic piston theory, and uses the Galerkin method to obtain the differential equation of motion. On the wall panel in the aerodynamic stability of the combined effect of boundary load and thermal load. The frequency of plate bending natural frequency analysis method, the critical temperature and critical thermal buckling flutter dynamic pressure analysis. The aerodynamic nonlinearity of limit cycle flutter vibration amplitude. The effect of wall temperature on the impact, the ratio of length to width and ply angle on the flutter boundary. The method of laminate laid shape memory alloy composite material on thermal buckling and flutter suppression. The classic Kirchhoff board theoretical simulation of wall displacement, the nonlinear displacement strain relationship description panel using von-Karman large deformation theory, the aerodynamic surface panel under the three order piston To describe the nonlinear theory, the one-dimensional Brinson thermodynamic model to describe the restoring force of the shape memory alloy produced by laying shape memory alloy panel. Partial differential equations are established by the principle of Hamilton, followed by a set of ordinary differential equations of motion of the system through the Galerkin method, a new method of laying aerothermoelasticity problem of shape memory alloy panels gas. Using nonlinear theory to analyze the stability region and the flutter boundary system. On the laying angle, shape memory alloy laying position, the number of copies, effects of pre strain and temperature on the wall thermal buckling and flutter of hypersonic flow in three-dimensional nonlinear gas composite laminates - dynamic elastic pneumatic thermal coupling problem, construct the wall temperature with altitude, air density and function of environmental parameters of flight velocity. In the modeling process. Calculation of aerodynamic force generated by the Ecker's reference temperature method of aerodynamic heating and transient heat conduction in the wall by difference method, using three order piston theory nonlinear simulation of pneumatic pressure, the gas wall dynamic elastic pneumatic thermal coupling analysis. The numerical analysis to consider the oblique shock wave parameters on the flow parameters before and after the critical flutter dynamic pressure effect, and the limit cycle amplitude, panel on aeroelastic response time - pneumatic thermal coupling under calculated. Put forward a new method of panel flutter test ground is given. The distributed reduction of unsteady aerodynamic force as the concentrated force. Experimental study and numerical it is a piece of simply supported thin plate. The unsteady aerodynamic simulation of supersonic panel three order nonlinear piston theory. The application of D Space control system in real-time and analysis of some points in the test process The displacement and velocity information, and then calculate the aerodynamic force needs to produce and are applied to the vibration exciter. Using laser displacement sensor to measure the maximum displacement response at the panel point, to determine the state of motion in the wall. The application of Hamilton principle in numerical analysis, the response of Galerkin discrete method and Rung-Kutta method to analyze the nonlinear dynamic panel at the end of the experiment. And the numerical results are analyzed and compared, including panel critical flutter dynamic pressure and the limit cycle amplitude.

【学位授予单位】：哈尔滨工业大学
【学位级别】：博士
【学位授予年份】：2017
【分类号】：V215.34

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