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- 2016
基于模型迁移方法的高超声速飞行器建模
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Abstract:
摘要 高超声速飞行器的研发是一个小批量多批次的过程。为了降低实验成本缩短建模周期，引入了模型迁移方法计算具有相似外形的高超声速飞行器的气动参数。首先研究了一种评价飞行器气动外形间仿射相似度的方法，当相似度满足要求时，可使用模型迁移方法计算新飞行器的气动参数。接着基于高超声速相似律，使用基飞行器的气动参数对新飞行器气动参数初次迁移。当初次迁移结果不能满足建模精度要求时，应用偏差校正的方法对迁移过程修正。最后为了消除飞行高度对高超声速流黏性的影响，引入高超声速边界层理论迁移飞行器不同高度上的气动参数。通过对仿真结果的分析，验证了模型迁移方法对具有相似外形的高超声速飞行器建模的有效性。
Abstract：The development of hypersonic vehicle is a process of multi-product and small-batch production. In order to reduce the cost of experiments and decrease the period of the modeling of hypersonic vehicles, model migration method is used to calculate the aerodynamic parameters of the vehicles with similar shapes. First, a method for assessing the similarity degree of hypersonic vehicles is explained. If the similarity of the hypersonic vehicles is sufficient, the model migration method will be used in the modeling of the new vehicle. Then the first model migration for the new vehicle will be expatiated using the aerodynamic parameters of the base vehicle based on the hypersonic similar law. The method of offset correction will be applied if the result of the first model migration cannot meet the precision requirement. Finally, in order to eliminate the influence of hypersonic viscosity, hypersonic boundary layer theory will be used to calculate the aerodynamic parameters of different altitude. The effectiveness of the model migration in modeling the vehicles with similar shapes is verified by the simulation.
| [1] | COX R N,CRABTREE L F.Elements of hypersonic aerodynamics[M]. London:The English Universities Press LTD.,1965:18-55. |
| [2] | HAYES W.Hypersonic flow theory[M].New York:Academic Press,2012:36-67. |
| [3] | 瞿章华,刘伟,曾明,等.高超声速空气动力学[M].长沙:国防科技大学出版社,2001:40-47.QU Z H,LIU W,ZENG M,et al.Hypersonic aerodynamics[M].Changsha:National University of Defense Technology Publishing,2001:40-47(in Chinese). |
| [4] | NEICE S E,EHRET D M.Similarity laws for slender bodies of revolution in hypersonic flow[J].Journal of the Aeronautical Science,1951,18(8):527-538. |
| [5] | VANDYKE M D.The combined supersonic-hypersonic similarity rule[J].Journal of the Aeronautical Sciences,2012,18(7):499-500. |
| [6] | HAMAKER F M,NEICE S E,EGGERS JR A J.The similarity law for hypersonic flow about slender three-dimensional shapes:NO.NACA-TN-2443[R].Washington,D.C.:National Aeronautics and Space Administration Moffett Field Caames Research Center,1951:1-22. |
| [7] | 张涵信.高超声速空气动力学[M].长沙:国防科技大学出版社,1982:32-50.ZHANG H X.Hypersonic aerodynamics[M].Changsha:National University of Defense Technology Publishing,1982:32-50(in Chinese). |
| [8] | SCHLICHTING H,GERSTEN K.Boundary-layer theory[M].London:Springer,2000:23-57. |
| [9] | FEDOROV A V,MALMUTH N D.Application of similarity in hypersonic transition prediction[J].AIAA Journal,1995,33(8):1523-1525. |
| [10] | 叶友达.高空高速飞行器气动特性研究[J].力学进展,2009,39(4):387-397.YE Y D.Study on aerodynamic characteristics of high velocity vehicle flying at high altitede[J].Advances in Mechanics,2009,39(4):387-397. |
| [11] | LU J,YAO Y,GAO F.Model migration for development of a new process model[J].Industrial & Engineering Chemistry Research,2008,48(21):9603-9610. |
| [12] | LU J,GAO F.Model migration with inclusive similarity for development of a new process model[J].Industrial & Engineering Chemistry Research,2008,47(23):9508-9516. |
| [13] | LU J,GAO F.Process modeling based on process similarity[J].Industrial & Engineering Chemistry Research,2008,47(6):1967-1974. |
| [14] | ANDERSON J D.Hypersonic and high temperature gas dynamics[M].New York:Mc Graw-Hill Book Company,1989:2-12. |
| [15] | MORGAN B,DURAIAMY K,NGUYEN N,et al.Flow physics and RANS modeling of oblique shock/turbulent boundary layer interaction[J].Journal of Fluid Mechanics,2013,729:231-284. |
| [16] | JAUNET V,DEBIEVE J F,DUPONT P.Length scales and time scales of a heated shock-wave/boundary-layer interaction[J].AIAA Journal,2014,52(11):2524-2532. |
| [17] | HERMES V,OLIVIER H.On the transformation of the angle of attack for supersonic similarity rules[J].Journal of Aircraft,2013,50(1):302-304. |
