固定鸭舵导引组件修正力模型改进及参数辨识

Improvement and Parameter Identification of Correction Force Model for Fixed-canard Guidance Kit

固定鸭舵双旋弹道修正弹通过调整固定鸭舵相位角控制修正力方向,从而改变弹体姿态,实现弹道修正。准确的导引组件修正力模型是提高修正弹修正精度的关键。本文在风洞试验基础上验证了数值计算的有效性。针对非零攻角下翼身干扰不对称现象,基于小扰动理论建立了基于4片舵片考虑翼身干扰的修正力模型。使用计算流体力学(CFD)所得数据,通过Levenberg-Marquardt算法对修正力模型进行参数辨识。辨识结果表明:基于4片舵片气动模型的y轴方向、z轴方向修正力随相位角呈正弦规律变化;在给定马赫数情况下,所建立的气动模型弹头对舵片的干扰系数对攻角变化不敏感,干扰系数随攻角相对变化小于4. 9%;所建立的修正力气动工程模型y轴方向和z轴方向修正力的残差平方和比现有模型更小,头部修正组件的修正力模型与CFD计算结果吻合较好。

Abstract : The attitude of fixed canard dual-spin trajectory correction projectile is changed by adjusting the phase angle of fixed canard to control the direction of correction force. An exact correction force model of precision guidance kit is the key to improve the correction accuracy of the correction projectile. The validity of the numerical calculation is verified on the basis of wind tunnel test. Based on the small disturbance theory, a modified correct force model of guidance kit is established for the correction projectile with four canards. Levenberg-Marquardt algorithm is used to identify the parameters of the modified correction force model based on the data of computational fluid dynamics(CFD). The results show that y and z directions vary sinusoidally with phase angle in the correction force model based on four canards. The disturbance coefficient of warhead is insensitive to the angle of attack at a given Mach number. The change of disturbance coefficient with angle of attack is less than 4.9%. The residual sum of squares of correction forces in y and z directions in the proposed modified correction force model is smaller than that in the existing model. The calculated results of correction force model of guidance kit are in good agreement with CFD calculations.