高速飞行条件下CMC材料细观热响应特性

doi:10.7527/S1000-6893.2024.30620

Abstract

Abstract:

The performance evaluation and design of high-temperature thermal protection structures are vital prerequisites for ensuring thermal safety in high-speed aircraft. Accurately predicting the non-steady-state thermal response characteristics of thermal protection structures under actual flight conditions is of utmost importance. This study investigates typical Ceramic Matrix Composite （CMC） thermal protection structures. The aerodynamic flow field around the leading edge of the aircraft was computed using both the Finite Volume Method （FVM） and Finite Difference Method　（FDM）. Additionally， simulations were conducted to model the thermal response process of Representative Volume （REV） and equivalent models of CMC materials under the coupling conditions of convection and radiation. A comparative analysis was performed to investigate the non-steady-state thermal response characteristics of CMC materials under transient aerothermal loads. The research findings indicate that the thermal response of the REV model exhibits a more complex spatiotemporal distribution under the coupling conditions of fluid flow and heat transfer. Under the prescribed conditions， with an aerothermal load condition of 150.34 kW/m²， the REV model shows a maximum temperature difference of 21.78 K on the wall， and the peak difference in heat flux occurs 2.39 s after the peak temperature difference. The internal temperature distribution of the structure is strongly influenced by the spatial distribution and thermal properties of the matrix and fiber yarn. Along the thickness direction， the temperature gradient exhibits an oscillatory waveform with a gradual attenuation. The conclusions of this study can provide important theoretical references for the low redundancy design of aircraft thermal protection systems and the accurate prediction of thermal environments. These findings can contribute to the development of more efficient and reliable thermal protection systems for aircraft， ensuring their thermal safety under high-speed flight conditions.

Key words: high-speed aircraft, CMC material, REV model, finite volume method (FVM), finite difference method (FDM), convective radiation coupling

CLC Number:

V211.3

Caichen WANG, Chao ZHANG, Xingkao CAI, Xiaofeng YANG, Guangming XIAO, Yanxia DU. Mesoscopic thermal response characteristics of CMC materials under high-speed flight conditions[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(3): 230620.

Figures/Tables 17

Fig.1

Fig.2

Table 1

Flight altitude and incoming flow parameters

高度/km	Ma	温度/K	压力/Pa	密度/（ $k g ⋅ m - 3$ ）
40	10	250.35	287.14	0.004

Table 1

Table 2

Fig.3

Fig.4

Table 3

Thermal property parameters of each component

材料组分	纱线	基体	等效模型
$k / (W ⋅ m - 1 ⋅ K - 1)$	1	25	4.75
$ρ / (k g ⋅ m - 3)$	1 760	1 046	1 433.99
$C p / (J ⋅ k g - 1 ⋅ K - 1)$	711	1 008	846.61

Table 3

Fig.5

Table 4

Cylinder flow experiment parameter

来流温度/K	Ma	Re/m^-1	初始温度/K	压力/Pa
241.5	6.47	$1.31 × 106$	294.4	648

Table 4

Fig.6

Fig.7

Fig.8

Table 5

Average temperature of different grid sizes at 1 s

网格规模	$T a v e / K$
160×160×80	407.01
192×192×96	422.49
224×224×112	423.27
256×256×128	422.94
288×288×144	423.50

Table 5

Fig.9

Fig.10

Fig.11

Fig.12

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Mesoscopic thermal response characteristics of CMC materials under high-speed flight conditions

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