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基于自适应回归算法的导弹表面温度预测 被引量:1

Prediction on Surface Temperature of Missile Based on Adaptive Regression Algorithm
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摘要 为预测导弹高速飞行时由于气动加热而升高的表面温度,根据已知的物理模型和试验数据,建立了一种基于自适应回归算法的导弹表面温度预测模型,使用该模型预测出温度数据,然后与实际试验数据进行对比。抽样选取含有55个个体的样本,按个体时间顺序排列样本个体,使用样本中的前50个个体训练预测模型,再使用剩余5个个体对预测模型进行检验。在前50个个体的相应时刻,预测值比实际值平均减小1.24%,标准差为1.27%;在最后5个个体的相应时刻,预测值比实际值平均减小1.42%,标准差为0.16%。结果表明,采用基于自适应回归算法的导弹表面温度预测模型对导弹的表面温度进行预测具有较高的精度,达到了预测导弹表面温度的目的。 When the missile flies at high speed, the surface temperature rises due to aerodynamic heating. In order to predict the surface temperature of missile, a prediction model of missile surface temperature based on adaptive regression algorithm was established according to the known physical model and test data. The model was used to predict the temperature data, which were compared with the experimental data. A sample of 55 individuals was selected, and the individual samples were arranged according to the time order. The first 50 individuals were used to train the prediction model, and then the remaining 5 indi- viduals were used to test the prediction model. At the corresponding time of the first 50 individuals, the predicted value was reduced by i. 24% , and the standard deviation was i. 27%. At the corresponding time of the last 5 individuals,the predicted value was reduced by an average of 1.42% ,and the standard deviation was about 0. 16%. The results show that the surface-temperature prediction-model of missile based on adaptive regression algorithm has high precision to predict the surface temperature of missile, and achieves the purpose of predicting the surface temperature of missile.
出处 《弹道学报》 CSCD 北大核心 2017年第1期93-96,共4页 Journal of Ballistics
关键词 导弹 自适应回归算法 温度预测模型 missile adaptive regression algorithm temperature prediction model
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  • 1吕丽丽,张伟伟,叶正寅.高超声速再入体表面热流计算[J].应用力学学报,2006,23(2):259-262. 被引量:18
  • 2范绪箕.气动加热和热防护系统[M].北京:科学出版社,2003.
  • 3HHT Ullmann. Reentry flight and ground testing experience with hot structures of C/C-SiC material[R].AIAA 2003-1667.
  • 4Aiichiro Tsukahara et al. Advanced TPS for RLV [R]. AIAA2001-1909.
  • 5J T Dorsty et al. Metallic TPS requirements, Environments, and integrated concepts[J]. J.of S.R.41(2), 2004.
  • 6HS Kanner et al. Recession curve generation for space shuttle rocket booster TPS coatings[R]. AIAA 2002-3334.
  • 7Conference on spacecraft structures, Materials and mechanical testing, ESA-SP-386 1996.
  • 8W D Sherborne, J D Milhoan. A radiant heating test facility for space shuttle orbiter TPS certification[R]. 11th space simulation conference, NASA CP-2150, 1980.
  • 9WG Beesley. Space shuttle entry thermal testing techniques[R]. AIAA 78-1628.
  • 10Thermoacoustic tests to quality TPS design[R]. ESA-SP-386, 1996.

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