鸭舵式双旋弹舵翼非线性控制力建模与分析

doi:10.12382/bgxb.2023.0402

摘要/Abstract

摘要：

鸭舵式双旋弹通过调节前体滚转角方位进行弹道修正,建立准确的舵翼控制力模型是深入研究其弹道特性和进行弹道设计的关键。综合考虑弹体和各片舵翼之间的干扰作用,在非滚转系中利用傅里叶级数对前体纵向对称面相对复攻角平面方位改变产生的周期性效应进行变换,建立适用于该类炮弹大攻角飞行的精确舵翼控制力工程计算模型,从原理上显示其与四片舵翼结构参数、复攻角幅值和相位以及前体滚转角方位间的关系。通过计算流体力学数值方法对不同前体滚转角和复攻角下的舵翼控制力进行仿真分析。研究结果表明:受一对减旋舵和操纵舵的法向力共同影响,舵翼控制力的大小和方向变化均呈现出强非线性特征,在大攻角条件下尤其突出;在任意复攻角和前体滚转角情况下,所建模型能够准确描述鸭舵式双旋弹的舵翼控制力及各因素对它的影响,为该类炮弹的前体结构设计、弹道特性分析和弹道设计等提供了理论依据与参考。

关键词: 鸭舵式双旋弹, 舵翼控制力, 非线性, 数值计算

Abstract:

A dual-spin projectile with canards is ballistically corrected by adjusting the orientation of the forebody roll angle, and establishing an accurate rudder control force model is the key to an in-depth study of its ballistic characteristics and ballistic design. Taking the interference between projectile and each canard into account, the Fourier series is used in the non-rolling frame to transform the periodic effect arising from the change in the orientation of longitudinal symmetry plane of forebody with respect to the plane of complex attack angle, and an accurate rudder control force model is established for this type of projectile flying at large attack angles. The relationships among the structural parameters of canards, the amplitude and phase of complex attack angle and the orientation of forebody roll angle are revealed. The computational fluid dynamics (CFD) numerical method is used to simulate and analyze the rudder control force at different forebody roll angles and complex attack angles. The results show that the rudder control force has strong non-linearity in magnitude and direction, especially at large attack angles, due to the combined influence of the normal forces of a pair of despinning rudder and steering rudder. The proposed model can accurately describe the rudder non-linear control force of dual-spin projectile with canards and the influence of various factors on it, which provides a theoretical basis for the forebody structure design, ballistic characteristics analysis and ballistic design of the projectile.

Key words: dual-spin projectile with canards, rudder control force, non-linearity, numerical calculation

中图分类号:

TJ011.⁺3

赵新新, 史金光, 王中原, 张宁. 鸭舵式双旋弹舵翼非线性控制力建模与分析[J]. 兵工学报, 2024, 45(8): 2607-2616.

ZHAO Xinxin, SHI Jinguang, WANG Zhongyuan, ZHANG Ning. Modeling and Analysis of Rudder Nonlinear Control Force for Dual-spin Projectile with Canards[J]. Acta Armamentarii, 2024, 45(8): 2607-2616.

图/表 8

图1 鸭舵式双旋弹结构

Fig.1 The configuration of dual-spin projectile with canards

图2 前、后体绕流区的网格

Fig.2 Grid of flow area around forebody/afterbody

表1 收敛性验证

Table 1 Verification of convergence

N/10⁶	Δt/μs	C_F_x/10^-3	C_F_y/10^-2	C_F_z/10^-3
3.7	5	-5.97	5.41	-9.25
	1	-6.02	5.36	-9.18
5.8	5	-6.17	5.27	-9.07
	1	-6.19	5.24	-9.09
8.4	5	-6.20	5.18	-9.13
	1	-6.20	5.19	-9.13

图3 舵翼控制力系数变化

Fig.3 Variation curves of rudder control force coefficient

图4 舵翼控制力系数的CA和ϕ变化

Fig.4 CA and ϕ of rudder control force coefficient

表2 傅里叶系数

Table 2 Fourier coefficients

系数	a_w_,_j_,0	a_w_,_j_,1	b_w_,_j_,1	a_w_,_j_,2	b_w_,_j_,2
F_1,1	1.820	0.044	-0.006	0.003	-0.071
F_1,2	-0.771	-0.199	0.015	0.078	0.039
F_2,0	-0.067	-0.024	-0.002	0	-0.001
F_2,1	1.694	0.211	0.027	0.006	0.013
F_2,2	-0.751	-0.301	-0.020	-0.095	-0.041

图5 舵翼控制力系数在OyAzA面内投影的变化

Fig.5 Projection of rudder control force coefficient on OyAzA plane

图6 不同控制方位下的复扰动攻角运动

Fig.6 Motion curves of complex disturbance attack angle under different control directions

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