Structure Control of Pneumatic Structure in the Space Environment

空间环境气动结构的结构控制

基本信息

批准号：
10650898
负责人：
ISHIDA Ryohei
金额：
$ 2.18万
依托单位：
Osaka Prefecture University
依托单位国家：
日本
项目类别：
Grant-in-Aid for Scientific Research (C)
财政年份：
1998
资助国家：
日本
起止时间：
1998 至 2000
项目状态：
已结题

项目摘要

The main purpose of this research is to do the conceptual design of the pneumatic structure in the space field. We consider the structure that mankind can live long time in the lunar regarding the application of the pneumatic structure in the space field. We consider the pneumatic structure of the half sphere that was covered with the topsoil of the lunar surface in consideration of the constraint condition in lunar surface environment, as a conceptual design example.We describe nonlinear differential equation that governs a uniform tension membrane face and Poisson equation as the linear approximation with respect to the governing equation of pneumatic structure. Furthermore, we perform approach from differential geometry and strict solution that used an approximation equation and formulation of the finite element method and numerical calculation. Also, actual pneumatic structure summarized it about the principle of virtual work regarding pneumatic structure, from such a viewpoint tha … More t is not a uniform tension membrane face.Next, we describe a condition that is requested to the pneumatic structure as the residence space in the space field and numerical analysis by the Ritz's method based on the principle of virtual work and concept design regarding the pneumatic structure in the earth outer planet. Similarity law that materializes between the model and the actual structure especially is newly formulated. Also we perform a fundamental experiment to confirm similarity law. As a result, the similarity law was almost confirmed.It is conceivable that it is important to control inner pressure about the structure control of the pneumatic structure. It is conceivable that inner pressure changes the membrane thickness partially for a partial structure control. The change of the partial membrane thickness is disadvantageous constructionally, because the change of the partial membrane thickness causes large membrane stress. However, it is possible to statically control the structure, by covering planetary topsoil to a membrane face. Less

本研究的主要目的是对半月气动结构在太空领域的应用进行气动结构的概念设计，以考虑人类能够在月球上长期生存的结构。考虑到月球表面环境的约束条件，以覆盖有月球表面表土的球体作为概念设计实例。我们将控制均匀张力膜面的非线性微分方程和泊松方程描述为此外，我们还对气动结构的控制方程进行了线性逼近，并使用有限元法和数值计算的近似方程进行了严格求解，并总结了实际的气动结构的原理。关于气动结构的虚功，从这样的角度来看，它不是一个均匀的张力膜面。接下来，我们描述了气动结构作为空间场中的驻留空间所要求的条件，并进行了数值模拟。特别是针对地球外行星的气动结构，基于虚拟功原理和概念设计的里兹方法进行了分析，特别是在模型和实际结构之间进行了新的相似性定律的分析，并进行了基础实验以确认相似性。结果，相似定律几乎被证实。可以想象，控制内部压力对于气动结构的结构控制是重要的。可以想象，内部压力对于部分结构控制来说部分地改变膜厚度。改变部分膜厚度的变化在结构上是不利的，因为部分膜厚度的变化会导致大的膜应力，但是，可以通过将行星表土覆盖到膜表面来静态地控制结构。