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| Study on finite element algorithm for three dimensional transient heat transfer during falling reentry of spacecraft with metal truss structure |
| Received:November 29, 2017 Revised:February 05, 2018 |
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| DOI：10.7511/jslx20171129003 |
| KeyWord:spacecraft with metal truss structure falling reentry from the outer space 3-dimensinal transient heat transfer finite-element computational model |
| Author | Institution |
| 石卫波 |
中国空气动力研究与发展中心, 绵阳 |
| 孙海浩 |
中国空气动力研究与发展中心, 绵阳 |
| 唐小伟 |
中国空气动力研究与发展中心, 绵阳 |
| 马强 |
四川大学 数学学院, 成都 |
| 李志辉 |
中国空气动力研究与发展中心, 绵阳 ;国家计算流体力学实验室, 北京 |
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| Abstract: |
| To construct the finite element model for the heat transfer of large-scale complex spacecraft with a metal truss structure during in reentry in aerothermodynamic environment,is the key to accurately predict the temperature distribution of the end-of-life spacecraft during the process of falling reentry and disintegration.In this paper,the four-node tetrahedron element is used to discretize the space,and the heat transfer equation is discretized into a set of algebraic equations.The symmetric positive-definite stiffness matrix with a highly sparse and non-zero element distribution is obtained by the overall synthesis of the finite element method.The one-dimensional variable bandwidth storage technique is developed to effectively resolve the data storage of large sparse matrix.To effectively depress the temperature oscillations appearing in time and space in the solving process,the centralized heat capacity matrix coefficient method is developed.The elements on the same row or column elements of the heat capacity matrix are summed to replace the diagonal elements,so that only the diagonal elements of the new heat capacity matrix are non-zero,and the remaining elements are zero.The two-point backward difference scheme,Crank-Nicolson scheme and Galerkin scheme are constructed to solve the three-dimensional transient temperature field.By computational analysis of transient heat transfer of a rectangular cylinder body,the converged temperature solutions of the above-said three schemes are found to be in good agreement,and the results are consistent with those of the existing finite-element software ANSYS,which confirms the precision and reliability of the present 3D finite-element model for transient heat transfer.The heat transfer computation is carried on the shell structure of a low-orbit spacecraft made of aluminium alloy,and the transient temperature distribution of the Tiangong's two-capsule structure is simulated and analyzed from the flight altitude of 107.5 km~90 km,which provides the theoretical support and computable model for the forecast of disintegration of the end-of-life spacecraft during falling reentry. |
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