宇航学报 ›› 2021, Vol. 42 ›› Issue (9): 1139-1149.doi: 10.3873/j.issn.1000-1328.2021.09.009

• 制导、导航、控制与电子 • 上一篇    下一篇

高超声速滑翔飞行器再入气动系数改进拟合模型

徐慧,蔡光斌,张胜修   

  1. 火箭军工程大学导弹工程学院,西安 710025
  • 收稿日期:2020-10-12 修回日期:2021-01-22 出版日期:2021-09-15 发布日期:2021-09-15
  • 基金资助:
    国家自然科学基金(61773387)

Modified Aerodynamic Coefficient Fitting Models of Hypersonic Gliding Vehicle in Reentry Phase

XU Hui, CAI Guang bin, ZHANG Sheng xiu   

  1. College of Missile Engineering, Rocket Force University of Engineering, Xi ’an 710025, China
  • Received:2020-10-12 Revised:2021-01-22 Online:2021-09-15 Published:2021-09-15

摘要: 为提升高超声速滑翔飞行器再入气动系数的刻画精度,基于公开的CAV H气动系数数据,本文提出了一种改进的高超声速滑翔飞行器再入气动系数拟合模型。首先,建立攻角二次项和马赫数负指数幂项相结合的气动系数拟合模型。其次,利用多元非线性最小二乘法对模型进行参数辨识,并采用拟合优度评价了该模型对气动系数数据的解释程度。然后,依据该模型从升阻比角度分析了气动模型飞行特点。最后,对本文改进模型进行数据拟合仿真,分析升阻比特性,并进行再入轨迹优化任务仿真。气动数据拟合实验表明,与现有典型模型相比,改进模型拟合误差降低,拟合优度进一步提高。不同定升阻比的飞行仿真实验表明,应用改进模型可全面刻画再入滑翔飞行特性。再入滑翔飞行任务仿真结果表明,相较于对比模型,改进模型得到的再入轨迹更为平稳。


关键词: 高超声速滑翔飞行器, 气动系数, 拟合优度, 升阻比, 再入轨迹优化

Abstract: In order to improve the characterization accuracy of the reentry aerodynamic coefficients of a hypersonic glide vehicle, based on the published CAV H aerodynamic coefficient data, an improved fitting model is proposed for the reentry aerodynamic coefficients of a hypersonic glide vehicle in this paper. Firstly, a fitting model of aerodynamic coefficients combining the quadratic term of the angle of attack and the negative exponential term of the velocity is established. Secondly, the multivariable nonlinear least squares method is used to identify the parameters of the model, and the goodness of fit is used to evaluate the degree of interpretation of the aerodynamic coefficient data. Then, according to the model, the flight characteristics of the aerodynamic model are analyzed from the perspective of lift to drag ratio. Finally, data fitting simulation is performed on the model, the lift to drag ratio characteristics of the model are analyzed, and the reentry trajectory optimization task simulation is performed. The aerodynamic data fitting experiment shows that compared with the existing typical models, the fitting error is greatly reduced, and the goodness of fit is greatly improved. The flight simulation experiments with different constant lift drag ratios fully demonstrate the characteristics of re entry gliding flight using this model. The simulation results of the reentry gliding mission show that the reentry trajectory obtained by the model in this paper is more stable than the comparison model.


Key words: Hypersonic gliding vehicle, Aerodynamic coefficient, Fit goodness, Lift to drag ratio, Reentry trajectory optimization

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