CG-01高速风洞弹箭模型动稳定性导数实验系统设计

doi:10.3969/j.issn.1000-1093.2021.11.025

摘要/Abstract

摘要： 为在风洞中真实模拟弹箭飞行运动状态，提高弹箭模型动稳定性导数测量水平，在CG-01高速风洞全新研制了一套动稳定性导数实验系统。该系统包含控制子系统、数据采集子系统、数据处理子系统和中小长细比模型实验装置、大长细比模型俯仰振动实验装置、旋转弹模型实验装置3个不同的实验装置。针对中小长细比模型，采用传统强迫振动方法建立了滚转、偏航和俯仰振动的实验装置；通过尾部强迫振动方式，开发出针对小口径、大长细比模型的俯仰振动实验装置；利用电机驱动弹体旋转，研制出两自由度旋转模型实验装置。整套实验系统经过了标模风洞验证实验，结果表明：中小长细比模型动稳定性导数实验装置在不同马赫数和迎角下测量的结果具有较高的精度；与国内外实验数据和计算流体力学数据进行了对比分析，实验结果处在可接受的误差范围内。大长细比模型和旋转模型动稳定性导数实验装置具有较高的工程应用价值。

关键词: 弹箭模型, 动稳定性导数, 实验系统, 高速风洞, BasicFinner模型

Abstract: Wind tunnel test is one of the most important methods to obtain the dynamic derivatives. A test system for the high-speed wind tunnel was developed to simulate the actual flight motion of projectile/rocket in the wind tunnel and improve the measuring level of dynamic derivatives. The system includes a control subsystem, a data acquisition subsystem, a data processing subsystem, and three different test devices, i.e., small and medium slenderness ratio model test device, large slenderness model pitch oscillation test device and spinning projectile model test device. For the small and medium slenderness ratio (L/d＜15) models, the traditional forced vibration method is used to establish the roll, yaw and pitch oscillation test devices. For the small caliber and large slenderness ratio (L/d≥15) model, the tail-forced vibration method is adopted for test device. For two-degrees-of-freedom spinning projectile model, a motor is used as driven device. The entire system was validated through wind tunnel test with standard model. The results show that the measured results of the small and medium slenderness ratio models obtained at different Mach numbers and angles of attack have high accuracy. Compared with domestic and foreign experimental data and CFD data, the experimental results here are within acceptable error range. The dynamic derivative test devices for large slenderness ratio and spinning projectile models have high engineering application value.

Key words: projectile/rocketmodel, dynamicderivative, testsystem, high-speedwindtunnel, BasicFinnermodel

中图分类号:

TJ410.6

薛栋，刘金，王欢，尹晋涛，江春茂，袁先士. CG-01高速风洞弹箭模型动稳定性导数实验系统设计[J]. 兵工学报, 2021, 42(11): 2522-2530.

XUE Dong， LIU Jin， WANG Huan， YIN Jintao, JIANG Chunmao, YUAN Xianshi. Design of Dynamic Derivative Test System for Projectile/rocket Model in High-speed Wind Tunnel[J]. Acta Armamentarii, 2021, 42(11): 2522-2530.

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