舰面流场中起动位置对旋翼瞬态气弹响应影响

Influence of starting position of ship surface flow field on rotor transient aeroelastic response

为研究舰面流场中直升机起动位置对旋翼瞬态气弹响应影响,通过CFD方法模拟得到舰面流场速度分布信息。旋翼动力学建模采用非线性准定常气动模型和中等变形梁假设,结合不同起动位置对动力学方程进行求解。结果表明:直升机起动位置越靠近舰艏和左舷,桨叶负向挥舞越大。在甲板中心1m范围内,最靠近舰艏和左舷的位置负向最大位移可达15.9%旋翼半径,中心处负向最大位移仅为8.5%旋翼半径,源于靠近舰艏和左舷位置垂向气流变化梯度明显高于舰艉和右舷。研究表明舰面流场垂向气流变化梯度对旋翼瞬态气弹响应影响明显,改变直升机起动位置能有效降低旋翼瞬态气弹响应。

In order to study the influence of starting position of helicopter on rotor transient aeroelastic response in ship surface flow field,the velocity distribution information of ship surface flow field was simulated by CFD method.Nonlinear quasi-steady aerodynamic model and moderately deformed beam assumption were used in rotor dynamics modeling,and the dynamic equations were solved by combining different starting positions.The results showed that if the starting position of helicopter was closer to the bow and the port side,the negative swing of blade was greater.Within 1 mof the deck center,the maximum negative displacement near the port side of the bow can reach 15.9% of the rotor radius,while the maximum negative displacement at the center was only 8.5% of the rotor radius.The vertical airflow gradient near the port side and the bow was obviously higher than that near the starboard side and the stern.The results show that the vertical airflow gradient has a significant effect on the transient aeroelastic response of the rotor.Changing the starting position of helicopter can effectively reduce the transient aeroelastic response of the rotor.