高超声速大动压下整流罩分离测力风洞试验

钟俊; 林敬周; 解福田; 赵健

doi:10.11729/syltlx20210194

高超声速大动压下整流罩分离测力风洞试验

doi: 10.11729/syltlx20210194

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

详细信息

作者简介:
钟俊：（1986—），男，四川内江人，硕士，工程师。研究方向：高超声速喷流干扰试验技术，级间分离试验技术，压力测量试验方法。通信地址：四川省绵阳市涪城区二环路南段6号15信箱505分信箱（621000）。E-mail：zhongjun@cardc.cn

通讯作者:
E-mail：jzou2000@sina.com

中图分类号: V211.71
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- 被引次数: 0
出版历程
- 收稿日期: 2021-12-28
- 修回日期: 2022-04-14
- 录用日期: 2022-04-20
- 网络出版日期: 2022-05-27

Wind tunnel force test of fairing separation in hypersonic and high dynamic pressure situation

Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang　621000, China

摘要

摘要: 针对高超声速试验模型整体式整流罩的反推火箭拔罩分离问题，开展了反推火箭喷流模拟方法和风洞测力试验装置设计研究，试验模拟了马赫数5、动压33 kPa时整流罩反推喷流干扰效应和分离距离影响，获得了反推喷流和分离距离影响下的整流罩气动特性。试验研究表明：反推火箭拔罩分离过程中，喷流干扰作用主导了整流罩的气动特性，使得法向力系数、轴向力系数和俯仰力矩系数出现了最大分别为44.5%、32.4%和198.6%的变化量；在负迎角下，整流罩压心前移显著，使得静稳定设计的整流罩呈现出静不稳定性，不利于整流罩安全分离；分离距离越大，分离距离变化对整流罩气动特性的影响越弱；将分离初始迎角限定为小的正迎角，整流罩在分离过程中容易保持姿态稳定，有利于整流罩安全分离。
- 整流罩分离 /
- 反推火箭喷流 /
- 天平测力试验 /
- 大动压 /
- 高超声速
Abstract: For the problem of the monolithic fairing separating from a hypersonic test demonstrator in a high dynamic situation, the reverse-thrust jets simulation method and wind tunnel force test model design have been developed, to meet the requirements of simulating the jets interaction effect and separation distance influence in the hypersonic wind tunnel. The fairing’s aerodynamic characteristics, including the jets interaction effect and the separation distance influence, were obtained by the strain balance in circumstances where the Mach number of the free-stream was 5 and the dynamic pressure was 33 kPa. The study indicates that the jets interaction effect dominates fairing’s aerodynamic characteristics in the separation process. The maximum coefficients’ variation of the normal force, axial force and pitching moment are 44.5%, 32.4% and 198.6% respectively. The pressure center moves forward obviously, making the fairing with designed static stability presents un-stability features in the minus attack angles. The influence of the separation distance on fairing’s aerodynamic characteristics becomes weaker as the separation distance increases. Using a small positive angle as the initial separation attack angle is helpful for the fairing maintaining a stable attitude, benefitting separation security during the separation process.
- fairing separation /
- reverse-thrust jets /
- balance force test /
- high dynamic pressure /
- hypersonic.

HTML全文

图 1 某高超声速试验模型及整流罩反推火箭喷管出口示意图

Figure 1. Sketch of hypersonic test demonstrator and reverse-thrust jet's orifices on fairing

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图 2 CARDC的Φ1 m高超声速风洞

Figure 2. Φ1 m hypersonic wind tunnel of CARDC

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图 3 反推喷管短边出口横截面示意图

Figure 3. Cross-section of shot side exit of reverse-thrust jets

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图 4 串联级间分离的通常支撑方式

Figure 4. Conventional support method of stage separation

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图 5 不同分离距离下的一体化试验装置

Figure 5. Integrated test models with different separation distances

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图 6 缩比飞行器原型前体和4个修形前体

Figure 6. Original and redesigned fore-body of scaled test demonstrator

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图 7 整流罩模型和喷流模拟装置照片

Figure 7. Photos of fairing model and jet simulation device

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图 8 2.2 D分离距离下有/无喷流试验的纹影照片

Figure 8. Schlieren comparison between jets off and on conditions in x_d=2.2 D

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图 9 数值计算网格示意图

Figure 9. Sketch of CFD grid

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图 10 有/无喷流时整流罩表面的压力云图

Figure 10. Comparison of fairing surface pressure between jets off and on

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图 11 2.2 D分离距离、有/无喷流时的试验结果

Figure 11. Data comparison between jets off and on conditions in x_d=2.2 D

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图 12 0 D～2.2 D分离距离下随迎角变化的有喷流试验结果

Figure 12. Jets-on test result with attack angles in separation distance from 0 D to 2.2 D

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图 13 迎角±3°时随分离距离变化的有喷流试验结果

Figure 13. Jets-on test result with separation distance at α=−3° and 3°

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表 1 天平主要技术参数

Table 1. Main parameters of balance

天平分量	设计载荷	精度/（% FS）	准度/（% FS）
轴向力A	150 N	0.2	0.4
法向力N	500 N	0.2	0.4
侧向力Z	100 N	0.2	0.4
俯仰力矩M_z	20 N·m	0.2	0.4
偏航力矩M_y	4 N·m	0.2	0.4
滚转力矩M_x	1 N·m	0.2	0.4

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表 2 冷喷流模拟参数

Table 2. Parameters of Cooling jets

p_j /p_∞	p_j /kPa	M_j	p_0j /MPa	γ
286	541.3	1.982	4.12	1.4

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表 3 试验结果与数值计算结果对比

Table 3. Comparison between test result and CFD data

迎角	数值计算结果			风洞试验结果			计算与试验的相对偏差
迎角	C_N	C_A	C_Mz	C_N	C_A	C_Mz	ΔC_N	ΔC_A	ΔC_Mz
α=0°	–0.000012	0.100925	0	0.00056	0.10657	–0.00006	0.59%	2.69%	–4.08%
α=3°	0.056205	0.102275	–0.000217	0.05275	0.10737	–0.00016	–3.58%	2.43%	3.88%
α=9°（基准）	–	–	–	0.09639	0.20973	0.00147	–	–	–
注：基准为α=9°、无喷流工况下气动载荷系数试验值的绝对值。

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