• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文会议>3rd AIAA spacecraft structures conference 2016 >Mechanical Development of a Novel Inflatable and Rigidizable Structure
【24h】

Mechanical Development of a Novel Inflatable and Rigidizable Structure

机译：新型充气刚性结构的机械开发

获取原文
获取原文并翻译 | 示例
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

A self-contained inflatable and rigidizable truss based substructure, its constraining mechanism, and stowage enclosure were developed for the RemoveDEBRIS technology demonstrator. RemoveDebris is a European Commission FP7 funded mission due for launch in late 2016. The hardware discussed in this paper will be integrated with the DebrisSat-1 microsatellite. During the course of the mission, active debris removal will be achieved by capturing DebrisSat-1 with the aid of a net fired from the primary platform. The inflatable module is key to this experiment as it allows the simulation of a much larger piece of debris than would be possible with a CubeSat alone. Following its capture, the inflatable structure will continue with its second objective as an end of life removal solution by passively drag augmenting DebrisSat-1's orbit to re-entry. The inflatable structure is constructed with six aluminum-polymer laminate cylindrical booms. These are connected in an axial manner to form a regular octahedron with a cross sectional area of 0.5 m2. A set of eight triangular polyester film segments or sails enclose the structure. The segments serve a dual purpose: firstly to increase the aerodynamic drag of the spacecraft, and secondly to distribute impact loads between the compressive inflatable members. A single cool gas generator (CGG) is utilised to deploy and rigidize the structure. This paper examines the development of the inflatable module from the early conceptual stages to the pre-qualification test level.
机译：为RemoveDEBRIS技术演示器开发了一个独立的可充气且可硬化的桁架基础子结构，其约束机制和储物罩。 RemoveDebris是欧盟委员会FP7资助的一项任务，定于2016年底发射。本文讨论的硬件将与DebrisSat-1微卫星集成。在执行任务的过程中，将借助于从主平台发射的网来捕获DebrisSat-1，从而实现主动清除碎片。充气模块是该实验的关键，因为它可以模拟比单独使用CubeSat更大的碎片。捕获后，可充气结构将继续其第二个目标，即通过被动拖动增加的DebrisSat-1轨道使其重新进入，从而达到消除寿命的解决方案。充气结构由六个铝聚合物层压圆柱吊杆构成。它们以轴向方式连接以形成横截面积为0.5 m2的规则八面体。一组八个三角形聚酯薄膜片段或帆包围了该结构。这些部分具有双重目的：首先增加航天器的空气动力学阻力，其次在压缩可充气构件之间分配冲击载荷。单个冷气发生器（CGG）用于部署和加固结构。本文考察了可充气模块从早期概念阶段到资格预审水平的发展。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号