首页> 外文会议>European conference on spacecraft structures, materials mechanical testing >RELIABLE NUMERICAL APPROACH FOR A DESIGN OF AN INFLATABLE MOON/MARS HABITATBASED ON MATERIAL TESTS IN THE SAS SIMULATOR
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RELIABLE NUMERICAL APPROACH FOR A DESIGN OF AN INFLATABLE MOON/MARS HABITATBASED ON MATERIAL TESTS IN THE SAS SIMULATOR

机译:基于SAS仿真器中材料测试的充气月球/火星人居设计的可靠数值方法

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Inflatable structures provide a solution to reduce thecosts associated with design, fabrication and launch ofan orbit, Moon or Mars habitat while simultaneouslyincreasing the volume at disposal to the crew. Thisresearch focuses on the design of an inflatable habbased on a non-linear analysis numerical code SamtechMecano that will test the deployment and structuralcharacteristics of an inflatable habitat and includesASTM mechanical tests, UV and IR radiation tests onthe materials which compose its multi-layer structure.The multi-layer laminate is divided in two parts: theinner layers are the so called 'pneumatic retention'layers and their duty is to keep the air leakage in safeparameters and capable to resist at one atmospherepressure. The outer layers provide a space debris andmicrometeoroids shielding and thermal protectionsystem. The materials were selected from severalcandidates like for the multi-layer pneumatic retentionpart are polymer sheets, ortho-fabrics and elastomerslike urethane coated Mylar sheets, Nylon ripstop, coatedKevlar fabric and Zylon fabric. The materials used forthe shielding and thermal protection layers are Nextel,Kevlar and Zylon fabric. This paper includes also themodelling of the mechanical properties for thenumerical code's material data library. Once inflated werealized which and what kind of materials are bestsuited for these structures concerning the pressure andmechanical resistance aspect. The information acquiredfrom the simulation aims also on the deploymentattitude of the inflatable hab and gives us the clues toimprove the geometry characterization for a stable andmore reliable inflation. The protection layers will bealso tested by the numerical code AUTODYN in orderto create the most feasible configuration. The goal ofthis research is to acknowledge and study a suitablegeometry and choose an appropriate combination ofmaterials for an experimental future model that will betested in our Space Environment Simulator and in ourMars Environment Simulator.
机译:充气结构提供了一种解决方案,以减少与设计,制造和发射轨道,月球或火星栖息地相关的成本,同时增加可供乘务员使用的体积。本研究的重点是基于非线性分析数字SamtechMecano的充气船的设计,该试验将测试充气栖息地的部署和结构特征,包括对构成其多层结构的材料进行ASTM机械测试,UV和IR辐射测试。多层层压板分为两部分:内层是所谓的“气动保留”层,其作用是将漏气保持在安全的参数范围内,并能够抵抗一个大气压。外层提供了空间碎片和微流星体的屏蔽和热保护系统。该材料选自多种候选材料,例如用于多层气动保持部件的是聚合物片材,原织物和弹性体,如涂有聚氨酯的聚脂薄膜,聚酯薄膜,尼龙防撕裂涂层,芳纶纤维涂层和Zylon织物。用于屏蔽和隔热层的材料是Nextel,Kevlar和Zylon织物。本文还包括数字代码的材料数据库的机械性能建模。一旦充气,就压力和机械阻力方面而言,哪种和哪种材料最适合这些结构。从模拟中获得的信息还针对可充气舱的展开程度,并为我们提供了一些线索,可改进几何特征以实现稳定且更可靠的充气。保护层也将通过数字代码AUTODYN进行测试,以创建最可行的配置。这项研究的目的是承认和研究合适的几何形状,并为未来的实验模型选择合适的材料组合,这些模型将在我们的空间环境模拟器和火星环境模拟器中进行测试。

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  • 会议地点 Noordwijk(NL)
  • 作者

    S.Mileti; G.Bitetti; M.Marchetti;

  • 作者单位

    Dep. Of Aerospace and Astronautical Engineering University 'La Sapienza' via Eudossiana 18 00184 Rome Italy E-mail: sandromileti@libero.it;

    Dep. Of Aerospace and Astronautical Engineering University 'La Sapienza' via Eudossiana 18 00184 Rome Italy E-mail: Grazia.Bitetti@uniroma1.it;

    Dep. Of Aerospace and Astronautical Engineering University 'La Sapienza' via Eudossiana 18 00184 Rome Italy E-mail: mario.marchetti@uniroma1.it;

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  • 入库时间 2022-08-26 14:39:29

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