上海交通大学学报

上海交通大学学报（自然版） ›› 2013, Vol. 47 ›› Issue (11): 1757-1761.

• 能源与动力工程 • 上一篇    下一篇

高空远程滑翔无人水下航行器气动参数估算

刘欢欢，潘光，杜晓旭
  

  1. (西北工业大学 航海学院， 西安 710072)
     
  • 收稿日期:2012-12-26
  • 基金资助:

    教育部新世纪优秀人才支持计划资助项目（NCET090074）

Estimation and Research of Aerodynamic Parameter of High-Altitude Long-Range Gliding UUV

LIU Huanhuan,PAN Guang,DU Xiaoxu
  

  1. (College of Marine Engineering, Northwestern Polytechnical University, Xi’an 710072, China)
  • Received:2012-12-26

摘要：

为了研究高空远程滑翔无人水下航行器（UUV）气动参数特性，根据飞机气动参数估算的方法，通过类比方式在小迎角、小侧滑角和尾翼偏转不大的情况下对高空远程滑翔UUV的纵向、横向气动参数和操纵导数进行计算.结合风洞试验结果进行对比分析，结果证明：计算和试验结果显示了良好的一致性，通过2种方式获得的气动特性均满足航行器的低阻特性和静稳定性要求，说明借鉴飞机参数的估算方法是可行的，为进一步对航行器的弹道设计、载荷计算、控制参数的选择和完善设计提供有力依据.

 
 

关键词: 无人水下航行器, 高空滑翔, 参数估算, 风洞试验, 气动特性

Abstract:

In order to study the pneumatic parameter characteristics of the high-altitude long-range gliding  unmanned underwater vehicle （UUV), and according to the method used on planes, the longitudinal aerodynamic parameters, the lateral aerodynamic parameters and the manipulation derivative were calculated and estimated in the case of little small angle of attack, sideslip angle and tail deflection. A comparison of wind tunnel test results show that the calculated and experimental results are consistent. The aerodynamic characteristics meet the requirements of the low draft characteristics and the static stability of the UUV. The result proves that the method used on planes is feasible, and provides a strong basis for the further ballistic design, load calculation, selection of control parameters and improvement of the design.
 

Key words: unmanned under water vehicle (UUV), highaltitude gliding, parameter estimation, wind tunnel test, aerodynamic characteristic

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