一种三扰流片机构的侧向力调节特性

Lateral force regulation characteristic of a three-tab mechanism

针对扰流片机构3个扰流片圆周对称的布局特点、径向旋转的作动方式,本文提出一种仅以三扰流片旋转角为变量的侧向力计算方案。数值计算和试验结果表明:该扰流片机构进行推力矢量调节时,喷管扩张段壁面几乎不产生侧向力,侧向力主要由3个扰流片配合差动产生。俯仰侧力与2号扰流片和1、3号扰流片旋转角平均值之差呈正相关;偏航侧力与1、3号扰流片旋转角之差呈正相关。在进行起始角度为52°,终止角度为23°的小角度调节时,三扰流片间气动力干扰很小,在3%以内,推力损失与扰流片旋转角近似呈线性关系。侧向力计算结果与试验结果偏差在6%以内,验证了该方法的正确性,所提出的计算式具有封闭可解性,能够根据推力损失和俯偏方向的期望侧向力反向求解出目标旋转角,进而提供一种三扰流片机构姿态调节的方法。

In view of the layout feature of three tabs in circular symmetry and action mode of radial rotation,a lateral force calculation scheme with only three-tab rotation angles as variables was proposed.Numerical and experimental results showed that the lateral force on the wall of nozzle expansion section was almost non-existent when thrust vector was adjusted by the mechanism,and lateral force was mainly generated by differential action of three tabs.The pitch force was positively correlated with difference value between average rotation angle of spoiler 2 and spoiler 1,spoiler 3.The yaw force was positively correlated with difference value between rotation angle of spoiler 1 and spoiler 3.When performing small angle adjustment with a starting angle of 52°and ending angle of 23°,the aerodynamic interference between three tabs was small to be within 3%,and the thrust loss was approximately linear with tab rotation angle.The deviation of the calculation result of lateral force from the test result was less than 6%,which verified the correctness of this method.The proposed formula had closed solvability,and the rotation angle of the target can be solved according to thrust loss and expected lateral force in reverse solving,thus providing a method for attitude adjustment of three-tab mechanism.