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Large spacecraft fall out of orbit and re-enter the atmosphere at the end of their lifetime, and they can break up into small debris upon re-entry. The spacecraft debris generated by the disintegration may lead to high risk when the surviving debris reaches the ground. One way to reduce the damage risk of spacecraft is to simulate the spacecraft disintegration process and accurately predict the falling area. Aerodynamics seriously affects the re-entering process, especially in the continuous flow regime. Aerodynamic force and heat are the main factors leading to debris disintegration. High dynamic pressure leads to sharp changes in attitude and complex trajectories during debris fall. A numerical method based on an unstructured Cartesian grid was developed to simulate the disintegrating separation problem by coupling the Navier–Stokes equation and the six-degree-of-freedom trajectory equation. A method combining the numerical method for dynamic processes with numerical simulation based on a static aerodynamic/dynamic characteristic database was developed for forecasting the falling area. Spacecraft disintegrating separation from 60 km was simulated using the method, and the multibody aerodynamic interference and the separation trajectory were predicted. The falling process was forecast by a numerical simulation method based on the static aerodynamic database/dynamic characteristic database when the debris went out of the influence domain. This method has good forecasting efficiency while considering the aerodynamic interference, making it a valuable method for forecasting disintegrating separation and falling debris.
Reyhanoglu, M., Alvarado, J. Estimation of debris dispersion due to a space vehicle breakup during reentry. Acta Astronautica, 2013, 86: 211–218.
Balakrishnan, D., Kurian, J. Material thermal degradation under reentry aerodynamic heating. Journal of Spacecraft and Rockets, 2014, 51(4): 1319–1328.
Wu, Z., Hu, R., Qu, X., Wang, X., Wu, Z. Space debris reentry analysis methods and tools. Chinese Journal of Aeronautics, 2011, 24(4): 387–395.
Caggiano, A., Etse, G. Coupled thermo-mechanical interface model for concrete failure analysis under high temperature. Computer Methods in Applied Mechanics and Engineering, 2015, 289: 498–516.
Li, Z., Ma, Q., Cui, J. Finite element algorithm for dynamic thermoelasticity coupling problems and application to transient response of structure with strong aerothermodynamic environment. Communications in Computational Physics, 2016, 20(3): 773–810.
Peng, A., Li, Z., Wu, J., Jiang, X. Implicit gas-kinetic unified algorithm based on multi-block docking grid for multi-body reentry flows covering all flow regimes. Journal of Computational Physics, 2016, 327: 919–942.
Li, Z., Peng, A., Wu, J., Ma, Q., Tang, X., Liang, J. Gas-kinetic unified algorithm for computable modeling of Boltzmann equation for aerothermodynamics during falling disintegration of Tiangong-type spacecraft. AIP Conference Proceedings, 2019, 2132(1): 100013.
Liang, J., Li, Z. H., Li, X. G., Shi, W. B. Monte Carlo simulation of spacecraft reentry aerothermodynamics and analysis for ablating disintegration. Communications in Computational Physics, 2018, 23(4): 1037–1051.
Li, Z., Peng, A., Ma, Q., Dang, L., Tang, X., Sun, X. 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, 2019, 1: 4.
Oberg, J. E. The things that fell to the Earth. Air & Space Magazine, 2005: 50–56.
Lips, T., Fritsche, B. A comparison of commonly used re-entry analysis tools. Acta Astronautica, 2005, 57(2–8): 312–323.
Fritsche, B., Klinkrad, H., Kashkovsky, A., Grinberg, E. Spacecraft disintegration during uncontrolled atmospheric re-entry. Acta Astronautica, 2000, 47(2–9): 513–522.
Lips, T., Fritsche, B., Koppenwallner, G., Klinkrad, H. Spacecraft destruction during re-entry—Latest results and development of the SCARAB software system. Advances in Space Research, 2004, 34(5): 1055–1060.
Tewari, A. Entry trajectory model with thermomechanical breakup. Journal of Spacecraft and Rockets, 2009, 46(2): 299–306.
Hashiguchi, K. General description of elastoplastic deformation/sliding phenomena of solids in high accuracy and numerical efficiency: Subloading surface concept. Archives of Computational Methods in Engineering, 2013, 20(4): 361–417.
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