火星再入飞行器风洞试验与真实飞行之间相关性的探讨

刘方彬; 袁军娅

doi:10.13700/j.bh.1001-5965.2018.0434

火星再入飞行器风洞试验与真实飞行之间相关性的探讨

doi: 10.13700/j.bh.1001-5965.2018.0434

刘方彬^{1, 2},
袁军娅^1, ,

1.
北京航空航天大学宇航学院, 北京 100083
2.
深圳易信科技股份有限公司, 深圳 518000

详细信息

作者简介:
刘方彬男, 硕士。主要研究方向:高超速飞行器化学反应

袁军娅女，硕士生导师，高级工程师。主要研究方向：高超声速飞行器气动热环境与热防护

通讯作者:
袁军娅, E-mail: yuanjy@buaa.edu.cn

中图分类号: V476.4
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- 被引次数: 0
出版历程
- 收稿日期: 2018-07-18
- 录用日期: 2018-11-23
- 网络出版日期: 2019-04-20

Discussion on correlation between wind tunnel test and flight of Mars reentry vehicle

LIU Fangbin^{1, 2},
YUAN Junya^{1
, ,}

1.
School of Astronautics, Beihang University, Beijing 100083, China
2.
Shenzhen Esin Technology Stock Inc., Ltd., Shenzhen 518000, China

More Information

Corresponding author: YUAN Junya, E-mail: yuanjy@buaa.edu.cn

摘要

摘要:
由于风洞试验条件限制，难以完全模拟火星再入飞行器真实飞行环境，因此需要建立火星再入飞行器风洞条件与真实飞行之间的关联关系。基于国外文献公开数据，采用数值方法和对比分析方法探讨了类"探路者号"外形的火星再入飞行器的风洞试验与真实飞行之间的外推方法。结果表明，在高焓空气风洞和常规空气风洞试验条件下，可以将模型驻点附近的无量纲压力和压力系数作为相关性参数，将风洞条件与飞行条件相关联起来，但是不能直接利用风洞试验的热流、无量纲热流和Stanton数作为关联参数；在高焓CO₂风洞试验条件下，可以利用模型驻点附近的无量纲压力、压力系数和Stanton数作为外推参数，但是不能直接将风洞试验的热流、无量纲热流作为相关性参数，将风洞条件下的风洞数据通过外推获取飞行条件下飞行器的性能参数。
- 火星 /
- 高超声速 /
- 风洞 /
- 再入 /
- 相关性 /
- 气动力 /
- 气动热
Abstract:
Due to the limitations of wind tunnel test conditions, the real flight environment of Mars reentry aircraft is difficult to fully be simulated, so it is necessary to establish the relationship of Mars reentry vehicle between windtunnel conditions and real flight. In this investigation, based on the published data of the literatures, the numerical method is used to study the extrapolation methods between the wind tunnel test and the real flight of Mars re-entry vehicle with the shape of the Pathfinder. The results show that under the conditions of high enthalpy air wind tunnel and conventional air wind tunnel test, the dimensionless pressure and pressure coefficient of near the stagnation point of the windtunel model can be used as a correlation parameters between the wind tunnel that and the flying conditions. However, the heat flow, the dimensionless heat flow and Stanton number of wind tunnel test cannot be directly used as correlation parameters under the conditions of high enthalpy air wind tunnel test and conventional air wind tunnel test. Under the high enthalpy CO₂ wind tunnel test conditions, the pressure coefficient, dimensionless pressure and Stanton number near the windtunnel model's stagnation point can be used as extrapolation parameters, but not the heat flow and dimensionless heat flow of the wind tunnel test are directly used as correlation parameters to obtain the performance parameters of the aircraft under flight conditions.
- Mars /
- hypersonic /
- wind tunnel /
- reentry /
- correlation /
- aerodynamic force /
- aerothermodynamics

HTML全文

图 1 “Pathfinder”计算模型^[11]

Figure 1. Calculation model of "Pathfinder"^[11]

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图 2 “MP-1”计算模型^[12]

Figure 2. Calculation model of "MP-1"^[12]

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图 3 “MP-1”的网格

Figure 3. Mesh of "MP-1"

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图 4 “Pathfinder”的网格

Figure 4. Mesh of "Pathfinder"

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图 5 气动热对比(风洞条件)

Figure 5. Comparison of aerodynamics (wind tunnel condition)

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图 6 风洞条件和飞行条件压力系数

Figure 6. Pressure coefficient of wind tunnel and flight conditions

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图 7 风洞条件和飞行条件无量纲压力

Figure 7. Dimensionless pressure of wind tunnel and flight conditions

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图 8 风洞条件和飞行条件的马赫数对比

Figure 8. Mach number comparison of wind tunnel and flight conditions

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图 9 风洞条件和飞行条件的温度对比

Figure 9. Temperature comparison of wind tunnel and flight

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图 10 风洞条件和飞行条件的压力对比

Figure 10. Pressure comparison of wind tunnel and flight

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图 11 壁面热流分布

Figure 11. Distribution of wall surface heat flow

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图 12 壁面Stanton数的分布

Figure 12. Distribution of wall Stanton number

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表 1 计算条件^[12]

Table 1. Calculation conditions ^[12]

变量	CASE 1		CASE 2		CASE 3
变量	飞行条件	风洞条件	飞行条件	风洞条件	飞行条件	风洞条件
u_∞/(m·s^-1)	7 009	1 416	7 263	1 422	7 185	5 162	4 772
ρ_∞/(kg·m^-3)	1.66×10^-4	8.680×10^-3	8.64×10^-5	4.51×10^-3	1.095×10^-4	5.712×10^-3	5.789×10^-3
T_∞/K	160.3	52.45	156.5	53.31	158.8	1 113	1 088
p_∞/Pa	5.10	130.6	2.60	69	3.338	1 824	1 191
Ma_∞	34	9.80	35.5	9.68	36.20	7.93	9.71
	0.12×10⁶	3.187×10⁶	0.095×10⁶	1.621×10⁶	0.126×10⁶	0.66×10⁶	0.66×10⁶
ρ_∞L/(kg·m^-2)	4.41×10^-4	4.41×10^-4	2.29×10^-4	2.29×10^-4	2.94×10^-4	2.90×10^-4	2.94×10^-4
组分(体积分数)	97%CO₂+3%N₂	21%O₂+79%N₂	97%CO₂+3%N₂	21%O₂+79%N₂	97%CO₂+3%N₂	21%O₂+79%N₂	100%CO₂

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表 2 5组分化学反应模型^[13]

Table 2. Mechanism with five species chemical reactions ^[13]

编号	化学反应
1	N₂+MN+N+M M=N₂，O₂，NO，N，O
2	O₂+MO+O+M M=N₂，O₂，NO，N，O
3	NO+MN+O+M M=N₂，O₂，NO，N，O
4	NO+ON+O₂
5	N₂+ONO+N

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表 3 8组分9化学反应模型^[14]

Table 3. Mechanism with eight species and nine chemical reactions ^[14]

编号	化学反应
1	CO₂+MCO+O+M M₁=N₂，O₂，NO，CO₂，CO； M₂=N，O，C
2	CO+MC+O+M M₁=N₂，O₂，NO，CO₂，CO； M₂=N，O，C
3	N₂+MN+N+M M₁=N₂，O₂，NO，CO₂，CO； M₂=N，O，C
4	O₂+MO+O+M M₁=N₂，O₂，NO，CO₂，CO； M₂=N，O，C
5	NO+MN+O+M M₁=N，O，C，NO，CO₂； M₂=N₂，O₂，CO
6	NO+ON+O₂
7	N₂+ONO+N
8	CO+OC+O₂
9	CO₂+OCO+O

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表 4 对比条件和计算结果(飞行条件)

Table 4. Comparison conditions and computation results(flight condition)

高度/ km	速度/(m· s^-1)	驻点热流
高度/ km	速度/(m· s^-1)	文献[8]结果/ (10⁶W·m^-2)	计算结果/ (10⁶W·m^-2)	误差/ %
85.000	7 504	0.099	0.105	6.00
64.599	7 472	0.392	0.383	1.26
56.026	7 364	0.565	0.550	2.72
43.097	6 774	1.140	1.132	0.87
41.204	6 596	1.180	1.163	0.84

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参考文献(16)

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