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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.
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图 1 基飞行器表面取点示意图
Figure 1. Schematic diagram of selected points on surface of base vehicle
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
Figure 6. Curves of lift coefficient and drag coefficient of new vehicle from experiment and model migration changing with attack angle
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
Figure 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
Figure 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
Figure 9. Curves of aerodynamic parameters of new vehicle changing with altitude when Ma=11, α=12°
表 1 新飞行器的实验数据
Table 1. Experiment data of new vehicle
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 
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