Investigation of roll damping derivative of aircraft by wind tunnel tests
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摘要: 介绍了中国航天空气动力技术研究院针对滚转阻尼导数试验中不同试验要求，为航空航天飞行器开展的多项滚转阻尼导数风洞试验技术研究。针对不同模型，分别采用一体式弹性铰自由振动试验技术、组合式弹性铰自由振动试验技术和基于气浮轴承的自由滚转试验技术进行了多项试验，对机械阻尼特性、试验频率和抗载荷能力等关键性能进行了综合分析和研究。风洞试验结果表明：合理利用各项试验技术进行试验，试验数据大小合理、规律性好；各试验技术能够满足不同的试验振动频率范围，并且体现出了机械阻尼量级的规律性变化。针对不同飞行器外形进行风洞试验时，应结合试验要求和多方面因素选取合适的试验技术和试验方案。Abstract: Roll damping derivative experimental techniques for air vehicles are investigated in wind tunnel of CAAA. The free oscillation dynamic derivative technique based on the integrated roll flexible hinge, the free oscillation dynamic derivative technique based on the combined roll flexible hinge, and the free rolling experimental technique based on the air bearing are studied respectively for different models. The mechanical damping characteristics, frequencies and anti-load capacity are the key points for the development of experimental technique. The study show that the test data have good regularity, and the test vibration frequency ranges are met when the proper technique is adopted. Thus the appropriate test technique should be chosen according to the test requirements for different vehicle shapes.
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Key words:
- aircraft /
- roll damping derivative /
- wind tunnel test techniques /
- flexible hinges /
- air bearing
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图 4 自由振动滚转阻尼导数试验机械阻尼特性
Figure 4. Mechanical damping characteristics of wind-tunnel free-oscillation experiment
表 1 一体式弹性铰无风试验结果
Table 1. Experimental results under no wind condition (integrated flexible hinge)
厚度/mm 模型 f/Hz L0 1.2 A 6.26 -8.17×10-4 B 10.84 -6.93×10-4 1.6 A 9.1 -3.24×10-3 B 16 -2.61×10-3 
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表 2 组合式弹性铰无风试验结果
Table 2. Experimental results under no wind condition (combined flexible hinge)
结构 模型 f/Hz L0 0.8mm×2 C 12.5 -4.00×10-4 D 9.0 -8.40×10-4 0.8mm×4 B 6.4 -2.87×10-3
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表 3 无风试验时气浮轴承机械阻尼测量结果(转速范围约150~600r/min)
Table 3. Experimental results under no wind condition (150~600r/min)
模型1 模型2 模型3 L0 -1.7×10-5 -2.1×10-5 -2.5×10-5
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表 4 某制导炸弹风洞试验结果
Table 4. The experimental results of model A
Ma α/(°) Lp 0.5 0 -0.13 3 -0.13 0.7 0 -0.12 3 -0.17
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