高超声速飞行器中圆柱类贮箱液固耦合动力学研究
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摘要
液固耦合问题广泛存在于工程实际中,研究这类问题具有广泛的现实意义;而近空间范畴内的高超声速飞行器也一直是人们研究的热点问题。研究飞行器中液体燃料贮箱内的液固耦合问题可以有效地控制飞行器的稳定性并有利于采取更好的制导措施。本文主要是对高超声速飞行器中的液体燃料贮箱类液固耦合问题进行了研究,由四部分组成。
第一部分介绍了高超声速飞行器(高超声速技术)的相关内容,着重对X-43A高超声速飞行器进行了描述,并介绍了液固耦合的相关理论、问题的研究方法及其发展情况。
第二部分首先对一般柱形液体贮箱模型进行研究,分析系统的动力学方程及其耦合边界条件,然后依据X-43A高超声速飞行器中具体的液体燃料贮箱外形,将模型贮箱的形状近似为圆柱形,根据动力学方程及耦合的边界条件等建立了Lagrange函数,并根据Lagrange方程建立了非线性耦合系统的动力学方程组。
第三部分是对第二部分建立的非线性方程组简化处理,得到两个自由度的耦合系统,在只考虑横向激振力的作用下,对系统内分别为不存在内共振和存在内共振两种情况下的为主共振、非共振、2倍超谐共振和组合共振等情况运用多尺度方法进行了解析分析。
第四部分是对第二部分建立的非线性耦合动力学方程组进行了数值求解,画出了各自由度相应的时间历程图、对应的频谱图及其稳态时的相图,并就有关图形与解析解的情况进行了对照。然后对改变阻尼因子进行了数值分析。
通过对高超声速飞行器中液体燃料贮箱的建模以及动力学分析,深入地研究了受横向外激励后贮箱及其内部燃料液体的运动情况,通过将得到的解析解和数值解的对比可以确知这两种方法的解的情况是基本吻合的。由解的情况可知,高超声速飞行器中液体燃料贮箱内部的晃动是比较大的,相应地对贮箱及其固联系统(或整个飞行器)的稳定性会造成很大的影响,选择适当的防晃挡板等装置来抑制液体的运动。这对于高超声速飞行器中液固耦合问题的研究具有一定的实际意义。
It is of great value to deal with liquid-solid coupling problems, which lie in engineering problems widely. The research on liquid-solid coupling problems has important significance. And hypersonic vehicle of near-space has been a hot issue. The research is of benefit to control the stability of flight vehicle and controlling the guidance effective. The paper primary researched the liquid-solid coupling problems in fuel container in flight vehicle of near space. There are four parts in the paper.
As the first part, the relate contents of hypersonic vehicles and the technology of hypersonic are introduced, especially the X-43A hypersonic vehicle. And then introduced the relevant theory and development of the liquid-solid coupling The second part, of the cylindrical fuel tank in the general study on the basis of the analysis system and the coupled dynamic equations of boundary conditions, and then based on X-43A hypersonic vehicle fuel container in a specific shape, the shape of the model similar to tank for the cylindrical, according to dynamic equations and boundary conditions, such as coupling the establishment of a Lagrange function, Lagrange equation based on the establishment of a nonlinear coupled system of dynamics equations.
The third part is based on the establishment of simplified nonlinear equations for the coupled system of two degrees of freedom in the second part, only to consider the role of lateral excitation, for the absence or the existence of internal resonance and internal resonance respectively of two mainly in case of resonance, non-resonant, 2 times the super-harmonic resonance and combination resonance such as the use of multi-scale analysis methods to resolve.
And the last part is also based on the establishment of the nonlinear coupling dynamics equations in the second part. For the corresponding analytic solution of the numerical solution, draw the corresponding degree of freedom of the time history diagram, the corresponding amplitude-frequency curve and the steady state phase maps, and graphics on the analysis carried out with the control.
By founding the liquid fuel tank in the modeling and dynamic analysis for hypersonic vehicle, the paper studies the movement of internal fuel tank due to cross-cutting incentives outside in-depth. By comparing the analytical solution and the numerical solution, we can see the results of the two ways are of the basic within the tank is relatively larger in the hypersonic vehicle, and the stability of the tank and its joint system (or the entire aircraft) will be greatly affected. We should join suited devices such as anti-Huang partition to curb the movement of liquid. The research of hypersonic vehicle for liquid-solid coupling problems has some practical significance.
第一部分介绍了高超声速飞行器(高超声速技术)的相关内容,着重对X-43A高超声速飞行器进行了描述,并介绍了液固耦合的相关理论、问题的研究方法及其发展情况。
第二部分首先对一般柱形液体贮箱模型进行研究,分析系统的动力学方程及其耦合边界条件,然后依据X-43A高超声速飞行器中具体的液体燃料贮箱外形,将模型贮箱的形状近似为圆柱形,根据动力学方程及耦合的边界条件等建立了Lagrange函数,并根据Lagrange方程建立了非线性耦合系统的动力学方程组。
第三部分是对第二部分建立的非线性方程组简化处理,得到两个自由度的耦合系统,在只考虑横向激振力的作用下,对系统内分别为不存在内共振和存在内共振两种情况下的为主共振、非共振、2倍超谐共振和组合共振等情况运用多尺度方法进行了解析分析。
第四部分是对第二部分建立的非线性耦合动力学方程组进行了数值求解,画出了各自由度相应的时间历程图、对应的频谱图及其稳态时的相图,并就有关图形与解析解的情况进行了对照。然后对改变阻尼因子进行了数值分析。
通过对高超声速飞行器中液体燃料贮箱的建模以及动力学分析,深入地研究了受横向外激励后贮箱及其内部燃料液体的运动情况,通过将得到的解析解和数值解的对比可以确知这两种方法的解的情况是基本吻合的。由解的情况可知,高超声速飞行器中液体燃料贮箱内部的晃动是比较大的,相应地对贮箱及其固联系统(或整个飞行器)的稳定性会造成很大的影响,选择适当的防晃挡板等装置来抑制液体的运动。这对于高超声速飞行器中液固耦合问题的研究具有一定的实际意义。
It is of great value to deal with liquid-solid coupling problems, which lie in engineering problems widely. The research on liquid-solid coupling problems has important significance. And hypersonic vehicle of near-space has been a hot issue. The research is of benefit to control the stability of flight vehicle and controlling the guidance effective. The paper primary researched the liquid-solid coupling problems in fuel container in flight vehicle of near space. There are four parts in the paper.
As the first part, the relate contents of hypersonic vehicles and the technology of hypersonic are introduced, especially the X-43A hypersonic vehicle. And then introduced the relevant theory and development of the liquid-solid coupling The second part, of the cylindrical fuel tank in the general study on the basis of the analysis system and the coupled dynamic equations of boundary conditions, and then based on X-43A hypersonic vehicle fuel container in a specific shape, the shape of the model similar to tank for the cylindrical, according to dynamic equations and boundary conditions, such as coupling the establishment of a Lagrange function, Lagrange equation based on the establishment of a nonlinear coupled system of dynamics equations.
The third part is based on the establishment of simplified nonlinear equations for the coupled system of two degrees of freedom in the second part, only to consider the role of lateral excitation, for the absence or the existence of internal resonance and internal resonance respectively of two mainly in case of resonance, non-resonant, 2 times the super-harmonic resonance and combination resonance such as the use of multi-scale analysis methods to resolve.
And the last part is also based on the establishment of the nonlinear coupling dynamics equations in the second part. For the corresponding analytic solution of the numerical solution, draw the corresponding degree of freedom of the time history diagram, the corresponding amplitude-frequency curve and the steady state phase maps, and graphics on the analysis carried out with the control.
By founding the liquid fuel tank in the modeling and dynamic analysis for hypersonic vehicle, the paper studies the movement of internal fuel tank due to cross-cutting incentives outside in-depth. By comparing the analytical solution and the numerical solution, we can see the results of the two ways are of the basic within the tank is relatively larger in the hypersonic vehicle, and the stability of the tank and its joint system (or the entire aircraft) will be greatly affected. We should join suited devices such as anti-Huang partition to curb the movement of liquid. The research of hypersonic vehicle for liquid-solid coupling problems has some practical significance.
引文
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