确定颤振模型设计参数的方法研究
收稿日期: 2012-12-07
修回日期: 2013-01-21
网络出版日期: 2013-01-25
Research on Methods Used to Determine Flutter Model Design Factors
Received date: 2012-12-07
Revised date: 2013-01-21
Online published: 2013-01-25
罗务揆 , 谢怀强 , 谢怀强 , 霍应元 . 确定颤振模型设计参数的方法研究[J]. 航空学报, 2013 , 34(10) : 2383 -2390 . DOI: 10.7527/S1000-6893.2013.0076
Aircraft flutter test model design and actual testing are often delayed because of inaccurate model design parameters, and there are few research publications in this field. This paper studied the basic design scales and other factors such as overweight ratio, section shape, equivalent mass ratio, etc., for flutter test model design. Meanwhile, it discussed the equivalent mass ratio and the section dimensional ratio of the aircraft basic spar frame model. They are convenient concepts to evaluate the basic design scales and other factors for designing flutter test models. As an example, reasonable design scales and factors are provided by the proposed method for an aircraft component flutter model design, which thus succeeds in solving potential problems in the primary stage and shortens the design and manufacture period of the test model from 6 to 3 months.
[1] Lv B, Liu D G, Xie C C, et al. Optimization designing method of wing flutter model for low-speed wind tunnel test. Journal of Beijing University of Aeronautics and Astronautics, 2006, 32(2): 163-166. (in Chinese) 吕斌, 刘德广, 谢长川, 等. 机翼低速风洞试验颤振模型优化设计方法. 北京航空航天大学学报, 2006, 32(2): 163-166.
[2] Stanley R C, Jerry L G. Past, present, and future capabilities of the transonic dynamics tunnel from an aeroelasticity perspective. AIAA-2000-1767, 2000.
[3] Lu B, Yang X H, Luo J G. The research of full model flutter test technique in 2.4m wind tunnel. The 1st Proseminar About the Mechanical Problems in the Fields of Aeronautics and Aerospace, 2004: 132-135.(in Chinese) 路波, 杨兴华, 罗建国. 2.4 m风洞全模颤振试验技术研究. 首届全国航空航天领域中的力学问题学术研讨会, 2004: 132-135.
[4] Guan D. Aeroelasticity manual. Beijing:Aeronautical Industry Press, 1994: 215-239.(in Chinese) 管德. 气动弹性力学手册. 北京: 航空工业出版社, 1994: 215-239.
[5] Luo W K, Hong Z G, Xie H Q. Caculation method of the section dimension of rectangle bar with lug: China, 201110232655.8. 2011-08-15. (in Chinese) 罗务揆, 洪兆贵, 谢怀强. 带耳片矩形梁截面尺寸确定方法: 中国, 201110232655.8. 2011-08-15.
[6] Luo W K, Zeng X A, Tang C H. Caculation method of the section dimension of rectangle hollow bar with lug: China, 201110232656.2. 2011-08-15. (in Chinese) 罗务揆, 曾宪昂, 唐长红. 带耳片薄壁矩形空心梁截面尺寸的确定方法:中国, 201110232656.2. 2011-08-15.
[7] Hu Z Y, Xie H Q, Huo Y Y. Study of the mass percent effects on the flutter of the model. Journal of Vibration Engineering, 2010, 23(S1): 309-312. (in Chinese) 胡志勇, 谢怀强, 霍应元. 质量比变化对模型颤振特性的影响研究. 振动工程学报, 2010, 23(S1): 309-312.
[8] Xie C C, Wu Z G, Yang C. Aeroelastic analysis of flexible large aspect ratio wing. Journal of Beijing University of Aeronautics and Astronautics, 2003, 29(12): 1087-1090. (in Chinese) 谢长川, 吴志刚, 杨超. 大展弦比柔性机翼的气动弹性分析. 北京航空航天大学学报, 2003, 29(12): 1087-1090.
[9] Luo W K, Huo Y Y, Tan S G. Research on the affect of deformation to aeroelastic model. Aircraft Engineering, 2010(1): 1-3. (in Chinese) 罗务揆, 霍应元, 谭申刚. 考虑结构变形影响的振动及颤振分析. 飞机工程, 2010(1): 1-3.
[10] Shan H Z. Mechanics of materials. Beijing: Higher Education Press, 1999: 132-137.(in Chinese) 单辉祖. 材料力学. 北京: 高等教育出版社, 1999: 132-137.
[11] Liu B S, Yan Y, Qian W, et al. Design, modal analysis and tests of composites wing box. Journal of Beijing University of Aeronautics and Astronautics, 2003, 29(11): 1026-1028. (in Chinese) 刘兵山, 燕瑛, 钱卫, 等. 复合材料机翼盒段的设计、模态分析和试验.北京航空航天大学学报, 2003, 29(11): 1026-1028.
[12] Zeng D, Yan Y, Liu B S, et al. Design of low velocity wing tunnel flutter model of aircraft composite structure. Acta Aeronautica et Astronautica Sinica, 2006, 27(2): 232-235. (in Chinese) 曾东, 燕瑛, 刘兵山, 等. 复合材料飞机结构低速风洞颤振模型的设计. 航空学报, 2006, 27(2): 232-235.
[13] Li S H, Yang Z C, Gu Y S. Partial structure similarity method to design composite transonic flutter model. Journal of Mechanical Strength, 2009, 31(2):339-343. (in Chinese) 李少华, 杨智春, 谷迎松. 一种复合材料跨声速颤振模型的部分结构相似设计方法. 机械设计, 2009, 31(2): 339-343.
/
〈 | 〉 |