超声速颤振风洞试验技术研究

闫昱; 余立; 吕彬彬; 罗建国

doi:10.11729/syltlx20160078

超声速颤振风洞试验技术研究

doi: 10.11729/syltlx20160078

中国空气动力研究与发展中心, 四川绵阳 621000

详细信息

通讯作者:
闫昱(1985-), 男, 河南新郑人, 工程师。研究方向:气动弹性风洞试验技术。通信地址:四川省绵阳市中国空气动力研究与发展中心(621000)。E-mail:junziyu@126.com

中图分类号: V215.3
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出版历程
- 收稿日期: 2016-05-09
- 修回日期: 2016-10-16
- 刊出日期: 2016-12-25

Research on flutter test technique in supersonic wind tunnel

China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

摘要

摘要: 颤振试验中，为避免暂冲式超声速风洞起动/关车过程中的冲击载荷损坏复合材料模型，依托FL-23风洞研制了一套超声速颤振投放系统。该系统的主要功能是在超声速流场建立后能够快速将模型投入流场，并在试验完成或模型振动临近发散时将模型收回。试验结果表明，该投放系统能够有效防止风洞起动/关车冲击载荷损坏模型，放宽了对超声速颤振试验模型强度的限制；亚临界预测的颤振临界速压与风洞试验直吹颤振结果一致；初步建立了工程实用的超声速颤振试验平台。
- 超声速 /
- 气动弹性 /
- 颤振 /
- 风洞试验 /
- 投放系统
Abstract: When the wind tunnel starts or ends running, there is a large impact load which could damage the flutter model easily. In order to solve the problem, a supersonic flutter insertion system is developed in FL-23 wind tunnel of CARDC. During the flutter tests, the insertion system pushes the model into the flow after the impact load disappears, and at the end of the tests or if the flutter occurs, the insertion system pulls the model back quickly. The test results show that the insertion system could protect the flutter model from damage effectively and ease the intensity limit of the model. The dynamic pressure achieved from the subcritical prediction is close to the flutter test result. As a conclusion, a practical supersonic flutter testing platform has been established in CARDC.
- supersonic /
- aeroelasticity /
- flutter /
- wind tunnel test /
- insertion system

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图 1 2m×2m超声速风洞冲击载荷示意

Figure 1. Impact load in 2m×2m supersonic wind tunnel

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图 2 试验段侧壁驻室(颤振投放机构安装位置)

Figure 2. Wind tunnel test section sidewall

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图 3 投放系统组成示意图

Figure 3. Sketch of the insertion system

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图 4 投放机构组成示意图

Figure 4. Sketch of the insertion machine

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图 5 FL-23风洞速压范围

Figure 5. Dynamic pressure of FL-23 wind tunnel

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图 6 模型在风洞中的安装照片

Figure 6. Model in the wind tunnel

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图 7 舵面模型振动响应信号(Ma=1.5)

Figure 7. Vibration response signals of the rudder (Ma=1.5)

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图 8 舵面模型振动响应信号(Ma=0.8)

Figure 8. Vibration response signals of the rudder (Ma=0.8)

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图 9 亚临界预测结果(Ma=0.8)

Figure 9. Subcritical prediction of flutter parameter(Ma=0.8)

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表 1 颤振参数测量结果

Table 1. Results of flutter parameters

Ma	Step	q/kPa	1/A	f/Hz	γ/%
	1	67.87	1.000	38.05	3.599
	2	78.73	1.267	39.50	3.927
2.0	3	85.84	1.491	40.81	4.633
	4	93.01	1.327	42.22	4.557
	5	100.18	0.868	42.92	3.964
	1	85.79	1.000	42.83	0.674
	2	96.47	1.276	43.32	0.977
1.5	3	107.20	1.376	43.29	0.980
	4	115.78	1.815	43.78	1.446
	5	120.00	2.842	43.96	1.930

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表 2 颤振参数测量结果

Table 2. Results of flutter parameters

Ma	Step	q/kPa	1/A	f/Hz	γ/%
	1	62.30	1.000	47.95	2.960
1.2	2	68.50	0.640	48.26	1.774
	3	74.71	0.192	48.44	1.183
	1	44.02	1.000	68.50	2.324
	2	51.39	0.586	67.14	4.718
0.8	3	54.27	0.551	65.16	4.599
	4	57.18	0.387	62.48	4.593
	5	60.08	0.111	59.75	2.391

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