超空泡航行器舵效的水洞试验研究

Experimental Research on Tail Rudder Efficiency of Super-Cavitaion Vehicle

为了获得超空泡航行器可控弹道与总体设计输入条件,对通气超空泡的生成和尾翼舵角的力学特性进行了缩比模型试验.通过改变通气量和尾翼舵角,对模型超空泡的形态和力学特性进行了深入分析,获得了尾翼舵角对升力的影响规律及尾翼舵效随攻角和通气量变化的规律,并探讨了由于空泡尾部重力效应引起的上漂现象的补偿方法.试验结果表明:在沾湿条件下,水下超空泡航行器尾翼舵面升力线斜率可取正值常数进行全域投影,这与同样条件下常规水下航行器相同;完成超空化后,当攻角为0.4°时,主体空泡耦合升力损失将导致舵效减小,且舵效对通气量的改变不敏感;当攻角大于1.2°后,舵效特性逐步恢复,此时主体空泡已经脱离翼面,舵面处于沾湿状态.

In order to acquire the input conditions of super-cavitaion vehicle control trajectory and overall design, a scaled model experiment on tail rudder was carried out to investigate the generation of ventilated supercavity and the dynamics characteristics of tail rudder angle of an underwater vehicle. The effects of ventilation air amount and tail rudder angle upon the configuration and hydrodynamics characteristics of a model supercavity were analyzed to obtain the influence regularities of tail rudder angle on lift force and angle of attack （AOA） and ventilation air amount on tail rudder efficiency. In addition, compensation measures for the supercavity tail floating-up caused by gravity were discussed. The experiment results show that in a wet state, the lift curve slope of tail rudder surfaces of an underwater super-cavitaion vehicle is a positive constant to be projected to the global area as the same as a common underwater vehicle under the same condition; when the super-cavitaion occurs and the AOA is 0.4°, the rudder effect will be reduced because of coupling lift force loss of main cavity, and it is insensitive to ventilation air amount; when the AOA is bigger than 1.2°, the characteristics of the rudder effect will be gradually restored, at the moment the main cavity has been away from the wing and the rudder surfaces are in a wet state.