Preliminary Design And Analysis Of Inflatable And Deployable Cabin

At present,most of the orbiting manned spacecrafts including International Space Station(ISS)belong to the rigid metallic cabin.Due to the disadvantages of large rigid cabin,such as heavy weight,large size,high cost and difficult to assemble,it becomes harder and harder to satisfy the need of deep space exploration in the future.Due to the advantages of light quality,collapsible,low costs,higher ratio of volume and quality and better protective properties compared with the traditionalrigid metallic cabin,inflatable and deployable cabin is the ideal choice to solve the contradiction between weak carrying capacity and fast growing space missions,which has extensive application prospects.Main Research of this paper on inflatable and deployable space cabin can be listed as follows:(1)Through the analysis of principle and requirement of inflatable and deployable space cabin,the basic structure design was done in this paper,mainly including structural core,planetary gear hatch mechanism,deployable structure of floor,the airlock and so on.Then based on the harsh space environment,flexible shell made of multilayer composite materials was designed.Finally,inflation system and charging circuit of cabin was designed.(2)Firstly,3-dimentional mode created by SolidWorks was simplified and imported into ABAQUS.The finite element model of structure core was done through the seting of material parameters,boundary conditions,interaction,restraint and so on.Then,6 extended natural frequency and modal shape of the structure core was obtained based on Lanczos after job submition.Finally,modal optimization was done based on the vibration stability criterion to ensure the structure core satisfy the requirement of vibration stability.(3)To provide a reference for the stress estimation of the restraint layer under the action of air pressure in the preliminary design stage,circumferential stress and axial stress of the restraint layer were derived in this paper.Von Mises stress was adopted to describe the two-direction stress state of the restraint layer.then the result was compared with FEA(finite element analysis)result in ABAQUS,and the effectiveness of the derivation process was verified.Then,stiffness maximization,stress distribution more uniform,superficial area minimum were choosed as the optimization objectives and multi-objective optimization of restraint layer was done based on the genetic algorithm to make it has optimized shape.(4)Based on the 3-dimentional mode and FEA results,the prototype of the inflatable and deployable space cabin was manufactured.Then,feasibilities of deployable structure and driving scheme of floor,sealing performance of the caibn and inflation system inflatable and deployable apace cabin was proved through the deploying experiment of floor and inflatable shell.