Full-time coupling method and application of a hypersonic all-movable wing

SHEN Ennan; GUO Tongqing; WU Jiangpeng; HU Jialiang; ZHANG Guijiang

doi:10.7527/S1000-6893.2021.25773

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2021 , Vol. 42 >Issue 8: 525773 - 525773

DOI: https://doi.org/10.7527/S1000-6893.2021.25773

Article

Full-time coupling method and application of a hypersonic all-movable wing

SHEN Ennan ,
GUO Tongqing ,
WU Jiangpeng ,
HU Jialiang ,
ZHANG Guijiang

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1. AVIC Shenyang Aircraft Design and Research Institute, Shenyang 110035, China;
2. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received date: 2021-04-18

Revised date: 2021-05-08

Online published: 2021-05-21

Supported by

Ph.D. Innovation Foundation of Shenyang Aircraft Design and Research Institute(SBJ-004)

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Abstract

Based on the synchronous method of flow-structure temperature field, a multi field full-time coupling method is established for the aerothermoelastic stability and transient response analysis of a hypersonic all-movable wing along the trajectory. The aerothermal synchronization algorithm is used to simulate the hypersonic flow and the structural temperature field. The interpolation methods of aerodynamic and the structure temperature field are established. The non-inertial frame of reference describing the attitude, and the dynamic grids methods describing the wing vibration are superimposed by coordinate transformation. The coupling unsteady effect of the attitude and vibration of the all-movable wing is considered. Finally, an aerothermoelastic stability analysis method combining synchronization algorithm with full-time coupling method is established. The present method is applied to the thermal flutter prediction and transient response analysis of a hypersonic all-movable wing operating along a given trajectory. It is found that due to the influence of structural vibration, fluctuation amplitude of heat flux at the monitoring point accounts for about 10% of the peak, while temperature decreased about 0.3%. A coupled bending-torsion flutter is obtained by the full-time coupling method is between the 4-5 trajectory state points, which is consistent with the results of the "modal freezing" thermal flutter method.

Key words： hypersonic; all-movable wing; full-time coupling; aerothermoelastic; unsteady; flutter

Cite this article

SHEN Ennan , GUO Tongqing , WU Jiangpeng , HU Jialiang , ZHANG Guijiang . Full-time coupling method and application of a hypersonic all-movable wing[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021 , 42(8) : 525773 -525773 . DOI: 10.7527/S1000-6893.2021.25773

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