航天器空腔结构隔热屏设计及安装方法OA

To solve problems such as structural complexity,high material density,insufficient support force during installation,and the risk of foreign object debris in the design of heat shield for cavity structure in spacecraft,a suspended heat shield design and installation method is pro-posed.The design utilizes a composite heat shield structure consisting of two layers of aramid fi-ber frames and one multilayer insulation blankets.A quantitative formula for detecting the tight-ening force of the aramid fibers is derived.Concurrently,the installation process method for this type of heat shield is described.The proposed heat shield is implemented and experimentally vali-dated on a three ultra-stable platform spacecraft featuring a central load-bearing cylinder cavity structure.Results demonstrate that temperature fluctuations of equipment on the spacecraft are effectively reduced,with the orbital temperature variation of the camera constrained within[-2℃,+2℃],thereby significantly improving its in-orbit imaging quality.The design and method resolve the thermal insulation challenges associated with cavity structures in spacecraft,expands the diversity of thermal control implementation strategies,and can be applied to other cavity structures and equipment on spacecraft.