空间折叠薄膜管充气展开过程气固耦合问题研究
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摘要
空间充气展开结构具有折叠体积小、重量轻和展开可靠性高等优点,因此在航天领域具有广阔的发展前景,也是近期国内外研究的热点之一。本文研究的空间折叠薄膜管是空间充气展开结构的基本构件,针对空间折叠薄膜管在充气展开过程中的动力学问题,综述了近20年来国际上的进展情况,包括充气展开模型、有限元模拟以及充气展开实验研究等。但由于空间折叠薄膜管充气展开过程存在复杂的气固耦合问题,目前国内外在这一方向的研究尚不成熟。
针对空间折叠薄膜管充气展开过程中存在非定常、可压缩的理想气体与柔性薄膜管之间的非线性气固耦合问题,本文引入任意拉格朗日-欧拉(ALE)描述方法,对可压缩理想流体的连续性方程和运动方程进行描述,构建了空间折叠薄膜管充气展开过程的气固耦合系统动力学模型,采用算子分裂方法并结合显式中心差分算法,解决了空间折叠薄膜管在充气展开过程中的大位移、小应变耦合界面的气固耦合问题。以V形折叠薄膜管为研究对象,分析了折叠薄膜管在充气展开过程中的速度场和压力场变化,讨论了充气速率和折叠角度对压力迟滞的影响。与分段充气控制体积模型计算的压力结果进行了比较,结果表明,分段充气控制体积模型误差较大,选用气固耦合模型更适合于研究薄膜管的充气展开动力学特性。
针对空间微重力环境,建立了折叠薄膜管的充气展开实验系统,采用气垫导轨,解决了地面重力对充气展开过程产生摩擦力的影响;采用非接触式的光电测量方式,有效地避免了接触式传感器对充气展开过程的干扰。针对V形折叠薄膜管,研究了不同的充气流量、薄膜管尺寸效应以及展开端有无有效载荷对充气展开动力学特性的影响;通过实验研究,选择充气流量、管子直径和载荷质量为主定参量,对充气展开过程进行量纲分析和实验误差分析。实验结果验证了用ALE有限元方法对空间折叠薄膜管充气展开过程气固耦合问题的数值模拟是有效的,这可为预报空间充气展开结构的展开动力学特性提供一定的依据。
针对粘扣控制下卷曲折叠薄膜管的充气展开过程,引入粘扣产生的阻力矩,采用刚体的平面运动理论,研究了有无粘扣控制下折叠薄膜管的充气展开动力学特性。然后考虑了薄膜管在卷曲折叠时的褶皱,采用ALE显式有限元方法对粘扣控制的折叠薄膜管进行气固耦合分析,研究了折叠薄膜管内的压力在充气展开过程中的变化,以及卷轴在充气展开过程中的展开速度和横向振动。对卷曲折叠薄膜管在粘扣控制下的充气展开过程进行了实验研究,结果表明,ALE有限元方法对粘扣控制的折叠薄膜管进行气固耦合分析是有效的,展开端部具有一定有效载荷的卷曲折叠薄膜管要可靠有序地展开,利用粘扣控制的方式是可行性的。
Increasing people focus on space inflatable deployment structures recently, which can offer inherent low packing volume, extremely low-mass and on-orbit deployment reliability, and they have extensive prospect in the space field. In this paper, space folded membrane booms are basic components for space inflatable structures. In view of their dynamics in the inflatable deployment process, the international advances of last twenty years have been summarized which including the inflatable deployment models, the finite element simulations and inflatable deployment experiments. But the research around the world is not mature enough for the complex gas-solid interaction problem existed in the space folded membrane booms during the inflatable deployment.
Considering the nonlinear gas-solid interaction which is existed in the space folded membrane booms between nonstationary, compressible gas and flexible boom wall during the inflatable deployment process, the arbitrary Lagrangian-Eulerian (ALE) method is introduced in this paper to describe the continuity equation and motion equation of compressible fluid. Gas-solid interaction dynamic model of space folded membrane booms in the inflatable deployment is established. Operator-split methodology is applied combining with explicit central difference algorithm to solve the problem of gas-solid interaction with interface of large displacement and small strain. The change of velocity field and pressure field of membrane booms during inflatable deployment is analyzed for V-folded membrane booms. The effects of inflation rate and folding angle on pressure delay are discussed. The pressure result is compared with segmented inflation control volume model. The result indicates that the control volume model has larger error, and the gas-solid interaction model is more suitable to study the deployment dynamic properties of membrane booms.
An inflation deployment experimental system in equivalent micro gravity environment is established based on air track which resolves the effect of gravity-caused friction. Non-contact photoelectricity measurement effectively avoids the disturbance of contact sensor to the inflation deployment process. The effectes of different inflation flows, variant geometry dimensions and loading/unloading on deployable end on dynamic properties are researched. Inflation flow, diameter, and payload mass are chosen as main parameters by the experiment. Inflation deployment process is analyzed by dimension theory, and analysis of experimental error is carried out. The experimental results show that the gas-solid interaction of the folded membrane boom during inflatable deployment is effective by ALE finite element method. This can offer gist to predict the deployment dynamics of space inflatable deployment structure.
For Velcro-controlled deployment process of rolled booms, resistance moment induced by Velcro is introduced using the theory of rigid motion of the plane to research the deployment dynamic properity of the rolled boom with and without Velcro. Then considering the wrinkle of membrane boom at the rolled state, the gas-solid interaction of the Velcro-controlled rolled boom is analyzed by ALE finite element method. Variation of the gas pressure inside boom, the deployment velocity, and the transverse vibrations are studied. Results show that gas-solid interaction analysis on the rolled boom is effective using the ALE finite element method. It is feasible that the rolled boom with some payload is reliably deployed using Velcro-controlled mode.
针对空间折叠薄膜管充气展开过程中存在非定常、可压缩的理想气体与柔性薄膜管之间的非线性气固耦合问题,本文引入任意拉格朗日-欧拉(ALE)描述方法,对可压缩理想流体的连续性方程和运动方程进行描述,构建了空间折叠薄膜管充气展开过程的气固耦合系统动力学模型,采用算子分裂方法并结合显式中心差分算法,解决了空间折叠薄膜管在充气展开过程中的大位移、小应变耦合界面的气固耦合问题。以V形折叠薄膜管为研究对象,分析了折叠薄膜管在充气展开过程中的速度场和压力场变化,讨论了充气速率和折叠角度对压力迟滞的影响。与分段充气控制体积模型计算的压力结果进行了比较,结果表明,分段充气控制体积模型误差较大,选用气固耦合模型更适合于研究薄膜管的充气展开动力学特性。
针对空间微重力环境,建立了折叠薄膜管的充气展开实验系统,采用气垫导轨,解决了地面重力对充气展开过程产生摩擦力的影响;采用非接触式的光电测量方式,有效地避免了接触式传感器对充气展开过程的干扰。针对V形折叠薄膜管,研究了不同的充气流量、薄膜管尺寸效应以及展开端有无有效载荷对充气展开动力学特性的影响;通过实验研究,选择充气流量、管子直径和载荷质量为主定参量,对充气展开过程进行量纲分析和实验误差分析。实验结果验证了用ALE有限元方法对空间折叠薄膜管充气展开过程气固耦合问题的数值模拟是有效的,这可为预报空间充气展开结构的展开动力学特性提供一定的依据。
针对粘扣控制下卷曲折叠薄膜管的充气展开过程,引入粘扣产生的阻力矩,采用刚体的平面运动理论,研究了有无粘扣控制下折叠薄膜管的充气展开动力学特性。然后考虑了薄膜管在卷曲折叠时的褶皱,采用ALE显式有限元方法对粘扣控制的折叠薄膜管进行气固耦合分析,研究了折叠薄膜管内的压力在充气展开过程中的变化,以及卷轴在充气展开过程中的展开速度和横向振动。对卷曲折叠薄膜管在粘扣控制下的充气展开过程进行了实验研究,结果表明,ALE有限元方法对粘扣控制的折叠薄膜管进行气固耦合分析是有效的,展开端部具有一定有效载荷的卷曲折叠薄膜管要可靠有序地展开,利用粘扣控制的方式是可行性的。
Increasing people focus on space inflatable deployment structures recently, which can offer inherent low packing volume, extremely low-mass and on-orbit deployment reliability, and they have extensive prospect in the space field. In this paper, space folded membrane booms are basic components for space inflatable structures. In view of their dynamics in the inflatable deployment process, the international advances of last twenty years have been summarized which including the inflatable deployment models, the finite element simulations and inflatable deployment experiments. But the research around the world is not mature enough for the complex gas-solid interaction problem existed in the space folded membrane booms during the inflatable deployment.
Considering the nonlinear gas-solid interaction which is existed in the space folded membrane booms between nonstationary, compressible gas and flexible boom wall during the inflatable deployment process, the arbitrary Lagrangian-Eulerian (ALE) method is introduced in this paper to describe the continuity equation and motion equation of compressible fluid. Gas-solid interaction dynamic model of space folded membrane booms in the inflatable deployment is established. Operator-split methodology is applied combining with explicit central difference algorithm to solve the problem of gas-solid interaction with interface of large displacement and small strain. The change of velocity field and pressure field of membrane booms during inflatable deployment is analyzed for V-folded membrane booms. The effects of inflation rate and folding angle on pressure delay are discussed. The pressure result is compared with segmented inflation control volume model. The result indicates that the control volume model has larger error, and the gas-solid interaction model is more suitable to study the deployment dynamic properties of membrane booms.
An inflation deployment experimental system in equivalent micro gravity environment is established based on air track which resolves the effect of gravity-caused friction. Non-contact photoelectricity measurement effectively avoids the disturbance of contact sensor to the inflation deployment process. The effectes of different inflation flows, variant geometry dimensions and loading/unloading on deployable end on dynamic properties are researched. Inflation flow, diameter, and payload mass are chosen as main parameters by the experiment. Inflation deployment process is analyzed by dimension theory, and analysis of experimental error is carried out. The experimental results show that the gas-solid interaction of the folded membrane boom during inflatable deployment is effective by ALE finite element method. This can offer gist to predict the deployment dynamics of space inflatable deployment structure.
For Velcro-controlled deployment process of rolled booms, resistance moment induced by Velcro is introduced using the theory of rigid motion of the plane to research the deployment dynamic properity of the rolled boom with and without Velcro. Then considering the wrinkle of membrane boom at the rolled state, the gas-solid interaction of the Velcro-controlled rolled boom is analyzed by ALE finite element method. Variation of the gas pressure inside boom, the deployment velocity, and the transverse vibrations are studied. Results show that gas-solid interaction analysis on the rolled boom is effective using the ALE finite element method. It is feasible that the rolled boom with some payload is reliably deployed using Velcro-controlled mode.
引文
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