跨越第二宇宙速度的膨胀管风洞研制

doi:10.7527/S1000-6893.2022.27729

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跨越第二宇宙速度的膨胀管风洞研制

吕治国¹(), 龚红明¹^,², 常雨¹^,², 廖振洋¹, 钟涌¹

^1.中国空气动力研究与发展中心超高速空气动力研究所，绵阳 621000
^2.中国空气动力研究与发展中心跨流域空气动力学重点实验室，绵阳 621000

收稿日期:2022-06-30 修回日期:2022-07-27 接受日期:2022-08-16 出版日期:2022-12-25 发布日期:2022-08-31
通讯作者: 吕治国 E-mail:lzgde2003@126.com
基金资助:
国家级项目

Development of an expansion tunnel with gas flow speed greater than escape velocity

Zhiguo LYU¹(), Hongming GONG¹^,², Yu CHANG¹^,², Zhenyang LIAO¹, Yong ZHONG¹

^1.Hypervelocity Aerodynamics Institute，China Aerodynamics Research and Development Center，Mianyang 621000，China
^2.Laboratory of Aerodynamics in Multiple Flow Regimes，China Aerodynamics Research and Development Center，Mianyang 621000，China

Received:2022-06-30 Revised:2022-07-27 Accepted:2022-08-16 Online:2022-12-25 Published:2022-08-31
Contact: Zhiguo LYU E-mail:lzgde2003@126.com
Supported by:
National Level Project

摘要/Abstract

摘要：

为了解决再入飞行器涉及到的高焓真实气体效应、辐射传热等关键气动问题，满足中国下一代航天飞行器研制对高焓环境模拟的需求，中国空气动力研究与发展中心建成了一座工程应用型的高焓膨胀管风洞。重点介绍了风洞的一些关键技术及解决途径，包括气动设计、活塞驱动、大口径耐冲击夹膜机构设计、双滚动浮动支撑运行、配套高焓瞬态测试技术，风洞流场调试的初步结果及测试技术验证等情况。流场调试结果表明：高焓膨胀管风洞实现的关键技术指标气流速度、焓值和有效试验时间范围分别是1.63~11.50 km/s、1.5~71.7 MJ/kg和0.1~1.1 ms，该风洞具备了进行高焓真实气体效应问题研究的地面试验模拟能力。

关键词: 膨胀管风洞, 活塞驱动, 高焓真实气体效应, 轻质气体驱动, 流场调试

Abstract:

In order to solve the high enthalpy real gas effect， radiation heat transfer and other key aerodynamic problems involved in reentry vehicles， and meet the needs of next generation spacecraft development for high enthalpy environment simulation， China Aerodynamics Research and Development Center has built a productive piston-driven high enthalpy expansion tunnel. This paper mainly introduces some key technologies and solutions of this expansion tunnel， including aerodynamic design， piston drive， and design of large-diameter impact resistant diagram， matching high enthalpy transient testing and other technologies， preliminary validation and calibration results. The flow field debugging results show that the key technical indicators of the high enthalpy expansion tunnel， such as gas flow velocity， enthalpy and effective test time range， are 1.63-11.50 km/s， 1.5-71.7 MJ/kg and 0.1-1.1 ms， respectively. This expansion tunnel has the ground test simulation capability to study the real gas effects of high enthalpy.

Key words: expansion tunnel, piston drive, high enthalpy real gas effect, light gas drive, flow calibration

中图分类号:

吕治国, 龚红明, 常雨, 廖振洋, 钟涌. 跨越第二宇宙速度的膨胀管风洞研制[J]. 航空学报, 2022, 43(S2): 138-151.

Zhiguo LYU, Hongming GONG, Yu CHANG, Zhenyang LIAO, Yong ZHONG. Development of an expansion tunnel with gas flow speed greater than escape velocity[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 138-151.

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

序号	V_∞/（km·s^-1）	H₀/（MJ·kg^-1）	t/ｍs	T_∞/K	ρ_∞/（kg·m^-3）	P_∞/kPa
1	2.5	3.9	1.10	702	0.087 0	18.10
2	8.1	35.3	0.32	2 574	0.002 7	2.07
3	11.5	71.7	0.10	2 340	1.55×10^-4	0.12

风洞	总长/m	压缩管内径/mm	压缩管长度/m	加速段长度/m	加速段直径/mm	喷管长度/m	喷管出口直径/mm
X3	65	500	12	24	182.6	3.007	447
本文	116	600	21.8	30	200	7.5	800

跨越第二宇宙速度的膨胀管风洞研制

Development of an expansion tunnel with gas flow speed greater than escape velocity

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