增阻离轨气球设计及空间热环境影响分析  

Design and Space Thermal Environment Analysis of Deorbiting Spheres

作　　者：徐彦[1] 尹潇锋 吴桐 XU Yan;YIN Xiaofeng;WU Tong(School of Aeronautics and Astronautics,Zhejiang University,Hangzhou 310027,China)

机构地区：[1]浙江大学航空航天学院,杭州310027

出　　处：《航天返回与遥感》2024年第6期27-36,共10页Spacecraft Recovery & Remote Sensing

基　　金：国家自然科学基金项目(12472166,91748209)。

摘　　要：随着空间碎片对航天器的威胁日益加剧,有必要研究航天器寿命末期离轨技术。针对轨道舱当前空间环境的离轨需求,设计并分析了充气增阻离轨球装置。完成了轨道舱-增阻球系统的离轨建模,分析了增阻离轨球受到的大气阻力,基于非线性有限元分析了在大气阻力和充气气压共同作用下的离轨球变形,确定了离轨球尺寸和设计充气气压。研究了空间热环境对增阻离轨球的影响,建立了充气薄膜结构的热力耦合顺序分析框架,着重考虑了内腔气体状态的变化及对离轨球构型的影响,得到了离轨球在飞行过程中的温度场、热变形、热应力和内腔气体状态参数的瞬态变化。结果表明:直径为7 m的离轨球能够使轨道舱在3个月内离轨,离轨过程中空间热环境对离轨球构型和内腔气压有一定的影响,文章的设计和分析方法为后续研发增阻离轨球提供技术支撑。With the increasing threat of space debris to spacecraft,it is necessary to study the de-orbit technology at the end of spacecraft life.According to the requirement of deorbiting of orbital module in the current space environment,an inflatable deorbiting sphere device is designed and analyzed.The de-orbit modeling of orbital module-deorbiting sphere system is conducted,and the atmospheric drag force of the deorbiting sphere is analyzed.The deformation of the sphere under the atmospheric drag force and air pressure is analyzed based on nonlinear finite element method,and the size and design inflation pressure of the deorbit sphere are determined.The influence mechanism of space thermal environment is studied,and a thermodynamic coupling sequence analysis framework for space inflatable structures is established.The change of gas state in the inner cavity and its influence on the configuration of the deorbiting spheres are considered.The temperature field,thermal deformation,thermal stress response and the state parameters of the gas in the cavity are obtained during the flight.The results show that the orbital module can be removed from orbit within 3 months with a 7 m sphere,and the space thermal environment has a certain influence on the configuration of the orbital diameter and the pressure in the inner cavity.The design and analysis methods in this paper provide technical support for the development of the inflatable deorbiting spheres in future.

关 键 词：轨道舱 增阻离轨球 离轨建模 空间热环境 热力耦合分析 

分 类 号：V474[航空宇航科学与技术—飞行器设计]