固定鸭舵导引组件修正力模型改进及参数辨识
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摘要
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。
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.
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.
引文
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[2]吴萍,陈少松,杨晋伟,等.旋转控制固定鸭舵二维弹道修正弹气动特性[J].弹道学报,2014,26(3):6-10.WU P,CHEN S S,YANG J W,et al. Aerodynamic characteristics fortwo-dimension trajectory correction projectile with spin-control fixed-canard[J]. Journal of Ballistics,2014,26(3):6-10.(in Chinese)
[3] SAHU J,HEAVEY K,BURETTA R. Numerical computations oftransonic flow over a course corrected spinning projectile[C]∥Proceedings of 26th AIAA Applied Aerodynamics Conference.Dallas,TX,US:AIAA,2006:6740.
[4] SAHU J,COSTELLO M,MONTALVO C. Development and ap-plication of multidisciplinary coupled computational techniques forprojectile aerodynamics[C]∥Proceedings of 7th InternationalConference on Computational Fluid Dynamics. Big Island,HI,US:ICCFD,2012:ICCFD7-4504.
[5]纪秀玲,王海鹏,曾时明,等.可旋转鸭舵对旋转弹丸纵向气动特性的影响[J].北京理工大学学报,2010,31(3):265-268.JI X L,WANG H P,ZENG S M,et al. CFD prediction of longitu-dinal aerodynamics for a spinning projectile with fixed canards[J]. Transactions of Beijing Institute of Technology,2010,31(3):265-268.(in Chinese)
[6]许安勇.二维弹道修正弹的气动特性研究[D].南京理工大学,2010.XU A Y. Study of two-dimension trajectory correction projectileaerodynamic characteristic[D]. Nanjing:Nanjing University ofScience and Technology,2010.(in Chinese)
[7] LIANG K,HUANG Z,ZHANG J M,et al. Optimal design of theaerodynamic parameters for a supersonic two-dimensional guidedartillery projectile[J]. Defence Technology,2017,13(3):206-211.
[8]殷婷婷,贾方秀,于纪言,等.双旋弹丸弹道修正组件控制响应模型研究[J].北京理工大学学报,2018,38(2):183-189.YIN T T,JIA F X,YU J Y,et al. Roll control response model ofthe dual-spin trajectory correction component[J]. Transactions of Bei-jing Institute of Technology,2018,38(2):183-189.(in Chinese)
[9]程杰,于纪言,王晓鸣,等.隔转鸭舵式弹道修正弹气动力工程模型与辨识[J].兵工学报,2014,35(10):1542-1548.CHENG J,YU J Y,WANG X M,et al. Engineering modeling andidentification of aerodynamics of trajectory correction projectile withdecoupled canards[J]. Acta Armamentarii,2014,35(10):1542-1548.(in Chinese)
[10] MADSEN K,NIELSEN H B,TINGLEFF O. Methods for nonli-near least squares problems[J]. Society for Industrial&AppliedMathematics,2004,2012(1):1409-1415.
[11]徐敏,安效民.飞行器空气动力特性分析与计算方法[M].西安:西北工业大学出版社,2012.XU M,AN X M. Aerodynamics analysis and calculation methodof air vehicles[M]. Xi'an:Northwest Polytechnical UniversityPress,2012.(in Chinese)