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Gas-kinetic unified algorithm for computable modeling of Boltzmann equation and application to aerothermodynamics for falling disintegration of uncontrolled Tiangong-No.1 spacecraft
Advances in Aerodynamics Pub Date : 2019-02-22 , DOI: 10.1186/s42774-019-0009-4
Zhi-Hui Li , Ao-Ping Peng , Qiang Ma , Lei-Ning Dang , Xiao-Wei Tang , Xue-Zhou Sun

How to solve the hypersonic aerothermodynamics around large-scale uncontrolled spacecraft during falling disintegrated process from outer space to earth, is the key to resolve the problems of the uncontrolled Tiangong-No.1 spacecraft reentry crash. To study aerodynamics of spacecraft reentry covering various flow regimes, a Gas-Kinetic Unified Algorithm (GKUA) has been presented by computable modeling of the collision integral of the Boltzmann equation over tens of years. On this basis, the rotational and vibrational energy modes are considered as the independent variables of the gas molecular velocity distribution function, a kind of Boltzmann model equation involving in internal energy excitation is presented by decomposing the collision term of the Boltzmann equation into elastic and inelastic collision terms. Then, the gas-kinetic numerical scheme is constructed to capture the time evolution of the discretized velocity distribution functions by developing the discrete velocity ordinate method and numerical quadrature technique. The unified algorithm of the Boltzmann model equation involving thermodynamics non-equilibrium effect is presented for the whole range of flow regimes. 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. To validate the accuracy of the GKUA, the hypersonic flows are simulated including the reentry Tiangong-1 spacecraft shape with the wide range of Knudsen numbers of 220~0.00005 by the comparison of the related results from the DSMC and N-S coupled methods, and the low-density tunnel experiment etc. For un-controlling spacecraft falling problem, the finite-element algorithm for dynamic thermal-force coupling response is presented, and the unified simulation of the thermal structural response and the hypersonic flow field is tested on the Tiangong-1 shape under reentry aerodynamic environment. Then, the forecasting analysis platform of end-of-life large-scale spacecraft flying track is established on the basis of ballistic computation combined with reentry aerothermodynamics and deformation failure/disintegration.

中文翻译:

玻尔兹曼方程可计算模型的气动力学统一算法及其在热力学中用于失控天宫一号航天器坠落分解的应用

如何解决外空坠落分解过程中大型失控航天器周围的高超音速空气动力学问题,是解决天工一号航天器再入撞毁问题的关键。为了研究覆盖各种流动状态的航天器再入的空气动力学,通过对玻尔兹曼方程碰撞积分的可计算建模,提出了一种气体动力学统一算法(GKUA),历时数十年。在此基础上,将旋转和振动能模作为气体分子速度分布函数的自变量,通过将玻尔兹曼方程的碰撞项分解为弹性和非弹性,提出了一种涉及内能激发的玻尔兹曼模型方程。冲突条款。然后,通过发展离散速度纵坐标法和数值正交技术,构造了气体动力学数值格式,以捕获离散速度分布函数的时间演化。提出了在整个流态范围内涉及热力学非平衡效应的玻尔兹曼模型方程的统一算法。气体动力学大规模并行计算策略是为解决高超声速空气动力学问题而开发的,处理器内核为500〜45,000,并行效率至少为80%。为了验证GKUA的准确性,通过比较DSMC和NS耦合方法的相关结果,并模拟了低速超声流,包括折返天宫一号飞船的形状,其努森数范围在220〜0.00005之间,范围很广。密度隧道实验等 针对失控的航天器坠落问题,提出了动态热力耦合响应的有限元算法,并在再入空气动力学环境下,对天宫一号形进行了热结构响应和高超音速流场的统一仿真。然后,在弹道计算,再入空气热力学和变形破坏/解体的基础上,建立了寿命终止的大型航天器飞行轨迹的预测分析平台。
更新日期:2019-02-22
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