大型航天器离轨再入气动融合结构变形失效解体落区数值预报与应用  

Study and Application of Deformation Failure Disintegration Algorithm for Large-scale Spacecraft Reentry Aerodynamic Coupling Structure

作　　者：李志辉[1,2] 彭傲平 马强[2,3] 石卫波 党雷宁[1] 梁杰 蒋新宇[1] 唐小伟[1] LI Zhihui;PENG Aoping;MA Qiang;SHI Weibo;DANG Leining;LIANG Jie;JIANG Xinyu;TANG Xiaowei(Hypervelocity Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;National Laboratory for Computational Fluid Dynamics,Beihang University,Beijing 100191,China;College of Mathematics,Sichuan University,Chengdu 610043,China)

机构地区：[1]中国空气动力研究与发展中心超高速空气动力研究所,绵阳621000 [2]国家计算流力学实验室,北京100191 [3]四川大学数学学院,成都610041

出　　处：《载人航天》2020年第4期403-417,共15页Manned Spaceflight

基　　金：国家自然科学基金(91530319、11325212、11902339);973计划(2014CB744100)。

摘　　要：准确可靠求解大型航天器服役期满离轨再入跨流域气动环境与金属(合金)桁架结构变形失效解体非线性力学行为,是解决航天器失联无控或受控再入坠毁飞行航迹落区数值预报软件研制的关键基础。在求解Boltzmann模型方程的气体动理论统一算法(GKUA)基础上,采用转动惯量描述气体分子自旋运动,利用分子总角动量守恒作为一个新的碰撞不变量,引入能量模式配分函数和非弹性碰撞松弛数,确立了描述复杂飞行器跨流域高超声速流动非平衡输运现象统一Boltzmann模型方程,构造了直接捕捉Boltzmann模型速度分布函数演化更新数值格式,提出了离散速度空间区域分解大规模并行计算策略与高效数据通信模型,建立了稳定运行数万CPU核求解大型航天器离轨再入跨流域气动力/热环境高性能并行算法。针对无控航天器非常规再入问题,提出瞬态热传导方程与材料热弹性动力学方程耦合数学模型,建立了强气动力热环境致结构变形热力响应有限元算法,发展了适于高超声速再入气动环境与结构热力耦合计算技术。通过对竖直平板、中空球体、类天宫飞行器高超声速流场计算与结构响应变形非线性力学行为一体化计算验证,证实统一算法大规模并行计算策略与热力响应变形有限元算法精度可靠性,建立了服役期满大型航天器离轨再入跨流域气动环境与结构热力耦合响应变形失效/解体飞行航迹一体化模拟平台,开展了该平台在类天舟一号货运飞船受控再入、天宫一号目标飞行器无控陨落、天宫二号空间实验室受控再入解体落区数值预报中的应用研究。Accurate and reliable solution of the hypersonic aerothermodynamics around large-scale spacecraft on expiration of service and nonlinear mechanical behavior in deformation failure and disintegration of metal(alloy)truss structure during falling crashing process from outer space to earth,is the key basis to resolve the numerical forecast of the falling area of the reentry crash and flight path after the completion of the spacecraft mission.In this paper,on the basis of the Gas-Kinetic Unified Algorithm(GKUA)for solving the Boltzmann model equations,the rotational inertia is used to describe the spin motion of gas molecules,and the conservation of total angular momentum of molecules is taken as a new Boltzmann collision invariant,then the unified Boltzmann model equation involving rotational non-equilibrium effect is presented for various flow regimes.The energy mode partition function and inelastic collision relaxation number are introduced to establish the unified Boltzmann model equation for describing the hypersonic non-equilibrium transport phenomenon of complex aircraft covering various flow regimes.The discrete velocity ordinate technique and numerical quadrature methods are applied to discretize the velocity space,and the gas-kinetic finite-difference numerical scheme is constructed to captures the time evolution of the discretized velocity distribution functions.The gas-kinetic massive parallel computing strategy is developed to solve the hypersonic aerothermodynamics with the processor cores 500~45,000 at least 80%parallel efficiency.For falling and crashing problem during the unconventional reentry of un-controlling spacecraft,a coupling mathematical model of transient heat conduction equation and thermo-elastic dynamic equation of materials is proposed,and then the finite-element algorithm of dynamic thermal-force coupling response is presented under strong aero-thermodynamic environment.The coupling computational technique of reentry aerodynamic environment and structural thermal response is developed,

关 键 词：非常规再入落区数值预报 板舱桁架结构大型航天器 跨流域空气动力学 BOLTZMANN模型方程 气体动理论统一算法 结构响应变形/毁坏有限元算法 

分 类 号：O35[理学—流体力学] V11[理学—力学]