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为了研究空中发射运载火箭的气动特性,本文针对15°半顶角的圆锥-圆柱组合体火箭模型,在1.2m×1m的低速风洞进行实验研究。利用六分量天平测量0°<α<80°、60m/s以下8个速度的力和力矩特性,基于圆锥底部的雷诺数范围由0.129×106到0.456×106。实验结果显示,随着迎角的增加,火箭流场经历了附体流动、对称旋涡、非对称旋涡到类卡门涡街的变化历程,旋涡的变化决定了火箭的气动特性。特别是30°<α<70°的大迎角区域,侧力受雷诺数的影响明显,反映了雷诺数变化对火箭流场亚临界区域和临界区域的影响规律。为提高火箭纵向稳定性和姿态的调整,设计了收敛-扩张形尾部并进行了实验验证。研究结果可为空射火箭的外形设计和稳定性分析奠定一定的理论基础。
In order to study the aerodynamic characteristics of launch vehicle, the paper studies the 15 ° semi-apex cone-cylinder combination rocket model in a 1.2m × 1m low-speed wind tunnel. The force and moment characteristics of 8 speeds of 0 ° <α <80 ° and 60m / s were measured by the six-component balance. The Reynolds numbers of the bottom of the cone were from 0.129 × 106 to 0.456 × 106. The experimental results show that with the increase of angle of attack, the rocket flow field undergoes the process of exponential flow, symmetric vortex and asymmetric vortex to quasi-Carmen vortex street, and the change of vortex determines the aerodynamic characteristics of the rocket. Especially in the high angle of attack range of 30 ° <α <70 °, the lateral force is significantly affected by the Reynolds number, which reflects the influence of the Reynolds number variation on the subcritical and critical regions of rocket flow field. In order to improve the longitudinal stability and attitude adjustment of the rocket, a convergent-divergent tail is designed and experimentally verified. The research results can lay a theoretical foundation for the design and stability analysis of the air-launched rockets.