非烧蚀防热材料地面模拟试验有效性分析

Wang Guolin; Meng Songhe; Jin Hua

doi:10.11729/syltlx20180122

非烧蚀防热材料地面模拟试验有效性分析

doi: 10.11729/syltlx20180122

王国林^{1, 2,},
孟松鹤¹,
金华^1, ,

1.
哈尔滨工业大学特种环境复合材料技术国家级重点实验室, 哈尔滨 150080
2.
中国空气动力研究与发展中心超高速空气动力研究所, 四川绵阳 621000

基金项目: 国家自然科学基金青年科学基金项目(11502058),黑龙江省博士后启动基金项目(LBH-Q1605),中央高校基本科研业务专项资金资助项目(HIT.NSRIF.201823)

详细信息

中图分类号: V211.73
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出版历程
- 收稿日期: 2018-05-11
- 修回日期: 2018-08-14
- 刊出日期: 2018-12-25

The validity analysis of ground simulation test for non-ablative thermal protection materials

Wang Guolin^{1, 2
,},
Meng Songhe¹,
Jin Hua^{1
, ,}

1.
National Key Laboratory of Science and Technology on Advanced Composites in Special Environments, Harbin Institute of Technology, Harbin 150080, China
2.
Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

More Information

Author Bio:
Wang Guolin (1973-), male, born in Dingxi city, Gansu province, doctoral candidate, researcher.Engaged in non-equilibrium and material's coupled heat and mass transfer research.Address:Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center (621000).E-mail:wgl65269@163.com

Corresponding author: Jin Hua, E-mail:jinhua2007@hit.edu.cn

摘要

摘要: 流场化学非平衡度与材料表面催化反应的耦合控制着服役于化学非平衡流场中非烧蚀防热材料表面的气动热载荷，若在该类防热材料性能模拟研究中忽略这一耦合效应，地面模拟试验将无法获得材料的有效使用性能。为此，本文依据钝头体高超声速飞行器边界层驻点热流关系式，分析了影响驻点热流的主要流场参数、地面高焓模拟设备所提供的高焓超声速流场特点以及与飞行热环境之间的主要差异，采用CFD分析了"三参数"模拟方法的有效性。针对化学非平衡边界层驻点传热分析，提出"四参数"模拟方法并分析了"四参数"模拟方法中离解焓无法模拟时的防热材料性能并提出初步解决方法。
- 非烧蚀防热材料 /
- 地面模拟试验 /
- 化学非平衡流 /
- 催化特性 /
- 数值模拟
Abstract: The aerodynamic heat load on the surface of the non-ablative thermal protection materials which served in the chemical non-equilibrium flow field, is controlled by the coupling of chemical non-equilibrium degree of flow field and the surface catalytic reaction of the materials. If the coupled effect is neglected in the performance simulation, the effective service performance cannot be obtained through the ground simulation test. Therefore, according to the stagnation-point heat flux relationship within the boundary layer of the blunt body supersonic vehicle, the present paper analyzes the principal flow field parameters, the characteristics of high-enthalpy supersonic field provided by ground simulation equipment, and the differences between ground and flight environments. The validity of the Three-Parameter-Simulation method is analyzed by the CFD simulation. A Four-Parameter-Simulation method is presented for analyzing the heat transfer of the chemical non-equilibrium stagnation-point boundary layer. Besides, the properties of the thermal protection materials is analyzed and a preliminary solution is proposed when the dissociation enthalpy in the Four-Parameter-Simulation is unable to be simulated.
- non-ablative thermal protection materials /
- ground simulation test /
- chemical non-equilibrium flow /
- surface catalytic characteristics /
- numerical simulation

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图 1 随着α和Dam_w的变化规律

Figure 1. The variation of along with α and Dam_w

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图 2 平衡下α随压力和焓值的变化

Figure 2. The equilibrium air α changed with pressure and enthalpy

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图 3 各参数沿着电弧风洞喷管轴线和出口的分布

Figure 3. Distribution of parameters along the axis and exit of the AHWT nozzle

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图 4 钝头试样(R_n^F=200mm)驻点线上参数分布

Figure 4. Parameter distributions on the stagnation-point line of the blunt body sample with R_n^F=200mm

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图 5 球头试样(R_n^F=35mm)驻点线上参数分布

Figure 5. The parameter distributions on R_n^F=35mm vehicle and stagnation-point line of the test sample

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图 6 随Dam_w变化规律

Figure 6. The variation of with Dam_w

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图 7 在不同θ条件下随Dam_w的变化规律(其中θ=α^F/α^S, α^S=0.4)

Figure 7. The variation of with Dam_w under different θ(where, θ=α^F/α^S, α^S=0.4)

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表 1 The states of supersonic flow fields in arc-heated wind tunnels for calculation

Table 1. The states of supersonic flow fields in arc-heated wind tunnels for calculation

	AHWT
In-chamber pressure/kPa	180.0
In-chamber enthalpy/(kJ·kg^-1)	2.3×10⁴
Nozzle throat/mm	Φ30.0
Nozzle outlet/mm	Φ200.0

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表 2 The flight conditions

Table 2. The flight conditions

	R_n^F/mm	U_∞^F/(m·s^-1)	p_∞^F/Pa	T_∞^F/K	C^F_O₂	C^F_N₂	C_O^F	C_N^F	C_NO^F
Case 1 Case 2	200 35	6930	8	229.5	0.234	0.766	0	0	0

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表 3 The AHWT simulation conditions

Table 3. The AHWT simulation conditions

	R_n^S/mm	U_∞^S(m·s^-1)	p_∞^S/Pa	T_∞^S/K	C^S_O₂	C^S_N₂	C_O^S	C_N^S	C_NO^S
Case 1	35	4654	107	920	0	0.508	0.234	0.258	0

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表 4 The stagnation-point heat flux & pressure for flight environment

Table 4. The stagnation-point heat flux & pressure for flight environment

	R_n^F/mm	p^F_s/Pa	Heat flux of full surface catalysis /(kW·m^-2)			Heat flux of non surface catalysis /(kW·m^-2)
	R_n^F/mm	p^F_s/Pa
Case 1	200	5540	1096	830	1926	1089	0	1089	0.565
Case 2	35	5540	3247	1531	4778	3176	50	3176	0.665

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表 5 The stagnation-point heat flux & pressure for simulated environment

Table 5. The stagnation-point heat flux & pressure for simulated environment

	R_n^F/mm	p_s^F/Pa	Heat flux of full surface catalysis /(kW·m^-2)			Heat flux of non surface catalysis /(kW·m^-2)
	R_n^F/mm	p_s^F/Pa
Case 1	35.00	5500	1118	834	1952	1120	0	1120	0.574
Case 2	26.65	5500	2483	2391	4874	2229	0	2229	0.457

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表 6 The compared of conduction & diffussion stagnation-point heat flux between flight and simulated environment

Table 6. The compared of conduction & diffussion stagnation-point heat flux between flight and simulated environment


Case 1	2.01%	0.482%	1.35%	2.85%	2.85%
Case 2	-23.53%	56.17%	2.01%	-29.82%	-29.82%

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