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Modeling of hypersonic vehicle via model migration method
WANG Haoliang , LI Qingdong , REN Zhang , ZHAO Qilun , DONG Xiwang , LIU Fei
Science and Technology on Aircraft Control Laboratory, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
Received: 2015-12-07; Accepted: 2016-03-11; Published online: 2016-04-13 15:37
Foundation item: National Natural Science Foundation of China (91216304, 91116002, 61333011)
Corresponding author. LI Qingdong, Tel.:010-82314573-11, E-mail:liqingdong@buaa.edu.cn
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.
Key words: hypersonic vehicle     affine similarity     hypersonic similar law     model migration     hypersonic boundary layer theory

1 飞行器仿射相似度评估

 (1)

 (2)

 图 1 基飞行器表面取点示意图 Fig. 1 Schematic diagram of selected points on surface of base vehicle
 (3)

 (4)

 (5)
2 模型迁移

 图 2 模型迁移流程 Fig. 2 Flowchart of model migration

2.1 提取特征信息

 (6)

 (7)

 (8)

 (9)

2.2 设计实验

2.3 评估差异

 (10)

 (11)

 (12)

2.4 偏差校正

 (13)

 (14)

 (15)

 (16)

3 仿真

 图 3 基飞行器 Fig. 3 Base vehicle
 图 4 新飞行器 Fig. 4 New vehicle

 图 5 基飞行器侧视图 Fig. 5 Side view of base vehicle

 (17)

n1=12, 则可以得到飞行器表面Y轴正方向上240组点。通过式(3)可以得到矩阵AB:

 (18)

Ma=13、h=40 km时的升力系数和阻力系数随攻角变化的曲线如图 6所示。此时新飞行器的气动参数是由基飞行器Ma=19.5时迁移得到的, 由于基飞行器的气动参数是考虑高超声速粘性效应的, 使得无黏流假设下得到的式(6)和式(7)迁移得到的新飞行器的气动参数产生较大误差, 所以需要对迁移过程进行偏差修正。

 图 6 实验和模型迁移得到的新飞行器升力系数与阻力系数随攻角变化的曲线 Fig. 6 Curves of lift coefficient and drag coefficient of new vehicle from experiment and model migration changing with attack angle

 编号 α/(°) Ma h/km CDn CLn 1 0 10 40 0.107 9 -0.2170 2 7 10 40 0.1336 0.4424 3 14 10 40 0.4410 1.4230 4 0 12 40 0.1015 -0.2195

 图 7 实验和修正得到的新飞行器升力系统与阻力系数随攻角变化的曲线 Fig. 7 Curves of lift coefficient and drag coefficient of new vehicle from experiment and offset correction changing with attack angle

 图 8 Ma=13、α=7.5°时新飞行器气动参数随高度变化的曲线 Fig. 8 Curves of aerodynamic parameters of new vehicle changing with altitude when Ma=13, α=7.5°
 图 9 Ma=11、α=12°时新飞行器气动参数随高度变化的曲线 Fig. 9 Curves of aerodynamic parameters of new vehicle changing with altitude when Ma=11, α=12°
4 结论

1) 利用仿射相似理论提供了评估飞行器气动外形相似度的方法, 有利于评估计算三维飞行器模型仿射相似度的值。

2) 研究了模型迁移理论在高超声速飞行器建模中的应用方法, 通过充分利用不同飞行器间的相似性，能有效减少新飞行器建模过程中的实验量，从而达到减小实验成本缩短建模周期的目的。仿真表明, 使用模型迁移方法对新飞行器进行建模, 能取得满意的建模效果。

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文章信息

WANG Haoliang, LI Qingdong, REN Zhang, ZHAO Qilun, DONG Xiwang, LIU Fei

Modeling of hypersonic vehicle via model migration method

Journal of Beijing University of Aeronautics and Astronsutics, 2016, 42(12): 2640-2647
http://dx.doi.org/10.13700/j.bh.1001-5965.2015.0807