HPC-based Virtual Flight Test Method for Multidisciplinary Multiphysical Field Coupling

doi:10.16182/j.issn1004731x.joss.19-0406

Abstract

Abstract: Multidisciplinary simulation based on virtual flight system testbed (FST) will become an alternative way for the overall performance validation of near space hypersonic vehicles (HSV). The complexity of multi-physical field coupled modeling and simulation challenges the accuracy and efficiency of virtual experiment. Therefore, a multi-physical-field coupling simulation model is established. The architecture of HPC-FST is explicitly expounded for large-scale parallel multidisciplinary virtual flight tests and multi-physics coupling simulation of whole vehicle. Moreover, an integration algorithm is developed for heterogeneous CAE models in collaborative simulation. A HPC based parallel virtual flight test method with a task-level and algorithm-level hybrid large-scale parallel simulation technology is developed for whole flight envelope simulation, and a large-scale parallel simulation algorithm is proposed for efficient simulation of aerodynamic flow field. Based on the supercomputer, HPC-FST is a high efficient platform for overall performance validation of HSV, which will reduce development cost as well as improve integrated design capability.

Key words: virtual flight system testbed, near space vehicle, multi-physical coupling, high performance computing, overall performance

CLC Number:

V411.8

Tie Ming, Yu Ying, Zhang Xing, Wang Jianlin. HPC-based Virtual Flight Test Method for Multidisciplinary Multiphysical Field Coupling[J]. Journal of System Simulation, 2019, 31(9): 1733-1740.

References

[1] Pezzella G.Hypersonic environment assessment of the CIRA FTB-X reentry vehicle[J]. Aerospace Science and Technology (S1270-9638), 2013, 25(1): 190-202.
[2] Tao X, Li N, Li S.Multiple model predictive control for large envelope flight of hypersonic vehicle systems[J]. Information Sciences (S0020-0255), 2016, 328(1): 115-126.
[3] Conway E.Simulation and spacecraft design: engineering Mars landings[J]. Technology and Culture (S0040-165X), 2015, 56(4): 812-838.
[4] Sockalingam S, Tabiei A.Fluid/thermal/chemical non- equilibrium simulation of hypersonic reentry vehicle[J]. International Journal of Multiphysics (S1750-9548), 2009, 3(3): 293-306.
[5] Li Z, Jiang X, Wu J.Study on high performance parallel algorithm for spacecraft re-entry aerodynamics in the whole of flow regimes using Boltzman model equation[J]. Chinese Journal of Computers (S0254-4164), 2016, 39(9): 1801-1811.
[6] Frezzotti A, Ghiroldi G, Gibelli L.Solving the Boltzmann equation on GPUs[J]. Computer Physics Communications (S0010-4655), 2011, 182(1): 2445-2453.
[7] Brown P, Woods C, McIntosh S, et al. A massively multicore parallelization of the Kohn-Sham energy gradients[J]. Journal of Computational Chemistry (S0192-8651), 2010, 31(10): 2008-2013.
[8] McNamara J, Friedmann P. Aeroelastic and aerothermoelastic analysis in hypersonic flow: Past, present, and future[J]. AIAA Journal (S0001-1452), 2011, 49(6): 1089-1121.
[9] Zhang S, Chen F, Liu H.Time-adaptive, loosely coupled strategy for conjugate heat transfer problems in hypersonic flows[J]. Journal of Thermophysics and Heat Transfer (S0887-8722), 2014, 28(4): 635-646.
[10] 铁鸣, 吴旭生, 毕敬, 等. 高超声速飞行器总体性能虚拟飞行试验验证系统[J]. 系统工程与电子技术, 2013, 35(9): 2004-2010.
Tie Ming, Wu Xusheng, Bi Jing, et al.Virtual flight test system for overall performance of hypersonic vehicles[J]. System engineering and Electronics, 2013, 35(9): 2004-2010.
[11] Cicirelli F, Furfaro A, Giodano A, et al.HLA_ACTOR_REPAST: An approach to distributing RePast models for high- performance simulations[J]. Simulation Modelling Practice and Theory (S1569-190X), 2011, 19(1): 283-300.
[12] Zhang S, Yuan R, Wu Y.Implementation and efficiency analysis of parallel computation using OpenACC: a case study using flow field simulations[J]. International Journal of Computational Fluid Dynamics (S1061-8562), 2016, 30(1): 79-88.
[13] Tian S, Wu Y, Xia J.Numerical simulation of unsteady flow field around helicopter in forward flight using a parallel dynamic overset unstructured grids method[J]. Modern Physics Letters B (S0217-9849), 2009, 23(3): 325-328.
[14] Lei J, Wang X, Xie G.High performance computation of a jet in crossflow by Lattice Boltzmann based parallel direct numerical simulation[J]. Mathematical Problems in Engineering (S1024-123X), 2015, 956827: 1-11. DOI: 10.1155/2015/956827.