充气式减速结构壁面变形对热化学非平衡流场的影响

doi:10.7527/S1000-6893.2024.30727

Abstract

Abstract:

Under the pressure of hypersonic inflow， the surface of the inflatable deceleration structure will deform on the windward side， thereby changing the flow field. To analyze the influence of surface deformation on the flow， simulations are conducted for the flow past the inflatable deceleration structure before and after surface deformation based on the thermochemical non-equilibrium reaction model. The shape of inflatable deceleration structure is a blunt nosed cone with a radius of 2.4 m and a half cone angle of 60°， consisting of a rigid head face and 6 inflatable rings. The numerical model adopts a 5-component dual-temperature thermochemical reaction model， and the wall catalytic conditions include non-catalytic and fully catalytic wall. The influence of surface deformation on flow characteristics， heat flux， and pressure under different attack angles is investigated. The results show that surface deformation can lead to periodic temperature and pressure fluctuations in the shock layer of the inflatable deceleration structure， as well as non-uniform distribution of dissociated components. The influence of surface deformation on flow variables weakens as the attack angle increases. After surface deformation， the change in velocity leads to increase in the heat flux and decrease in the pressure at inflatable rings， as well as decrease in the heat flux and increase in the pressure at the concavities between inflatable rings. The effect of surface deformation on the pressure is weaker than that on the heat flux. There is no significant change in the aerodynamic coefficients of the front face of the inflatable deceleration structure after deformation.

Key words: inflatable deceleration, hypersonic flow, aerothermodynamics, non-equilibrium reaction, dual-temperature model

CLC Number:

V211

Yu LIU, Miao ZHAO, Qingsong HE. Influence of surface deformation of inflatable deceleration structure on thermochemical non-equilibrium flow[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(1): 630727.

Figures/Tables 33

Table 1

Five-component chemical reaction model

化学反应	A/（m³·mol^-1·s^-1）	B	C/K
$N 2 + M ↔ 2 N + M$	3.70×10¹⁵（M=N₂，O₂，NO）	-1.6	113 200
$N 2 + M ↔ 2 N + M$	1.11×10¹⁶（M=N，O）	-1.6	113 200
$O 2 + M ↔ 2 O + M$	2.75×10¹³（M=N₂，O₂，NO）	-1.0	59 500
$O 2 + M ↔ 2 O + M$	8.25×10¹³（M=N，O）	-1.0	59 500
$N O + M ↔ N + O + M$	2.30×10¹¹（M=N₂，O₂，NO）	-0.5	75 500
$N O + M ↔ N + O + M$	4.60×10¹¹（M=N，O）	-0.5	75 500
$N 2 + O ↔ N O + N$	2.16×10²	1.29	19 220
$N O + O ↔ O 2 + N$	3.18×10⁷	0.10	37 700

Table 1

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Table 2

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迎角/（°）	气动力系数	原壁面	变形壁面	相对变化/%
0	C_x	1.487	1.484	-0.20
5	C_x	1.456	1.461	0.34
	C_y	3.582×10^-2	3.610×10^-2	0.78
	C_m	2.088×10^-2	2.167×10^-2	3.78
10	C_x	1.300	1.304	0.31
	C_y	1.050×10^-1	1.039×10^-1	-1.05
	C_m	6.717×10^-2	6.693×10^-2	-0.36

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Influence of surface deformation of inflatable deceleration structure on thermochemical non-equilibrium flow

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