一类变后掠翼制导炮弹气动特性分析与弹道规划

doi:10.12305/j.issn.1001-506X.2025.11.29

摘要/Abstract

摘要：

针对提升制导炮弹射程需求，以一类变后掠翼制导炮弹为研究对象，分析其气动特性，并进行滑翔弹道规划设计，研究其增程效果。首先采用气动力工程算法针对不同气动外形进行弹丸气动特性分析，得出其气动参数随后掠角变化规律。然后根据气动参数随马赫数、攻角、后掠角的变化规律建立弹道优化模型，取攻角与后掠角作为双控制变量，采用高斯伪谱法对变后掠角制导炮弹进行弹道优化，并与固定后掠角状态进行对比分析。仿真结果表明，本文研究的一类变后掠翼制导炮弹在飞行过程中通过同时改变外形与飞行攻角可以使射程提升7%~55%，增程效果明显，对于提升制导炮弹射程具有重要意义。

关键词: 制导炮弹, 变后掠翼, 气动特性, 弹道规划

Abstract:

In response to the demand for increasing the range of guided projectiles, a kind of variable sweep wing guided projectile is taken as the object of the study, and the aerodynamic characteristics of a kind of variable sweep wing guided projectiles are analyzed, and gliding ballistic planning and design are carried out to study their range extending effects. Firstly, aerodynamic engineering algorithms are used to analyze the aerodynamic characteristics of projectiles with different aerodynamic shapes, and the law of aerodynamic parameters changing with the sweep angle is obtained. Then, based on the variation of aerodynamic parameters with Mach number, angle of attack, and sweep angle, a ballistic optimization model is established. With attack angle and sweep angle as the dual control variables, the gliding trajectory of the variable sweep angle guided projectile is optimized using Gaussian pseudo-spectral method and compared with the fixed sweep angle state. Simulation results show that during the flight, the range of a kind of variable sweep wing guided projectile proposed in this paper could be increased by 7% to 55% by simultaneously changing the shape and flight angle of attack during flight, and the range extension effect is significant, which is of great significance for improving the range of guided projectiles.

Key words: guided projectile, variable sweep wing, aerodynamic characteristic, ballistic planning

中图分类号:

TJ 765.2

王成, 李瑞, 马欣宇, 吉庆. 一类变后掠翼制导炮弹气动特性分析与弹道规划[J]. 系统工程与电子技术, 2025, 47(11): 3826-3833.

Cheng WANG, Rui LI, Xinyu MA, Qing JI. Analysis of aerodynamic characteristics and ballistic planning of a kind of variable sweep wing guided projectile[J]. Systems Engineering and Electronics, 2025, 47(11): 3826-3833.

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参数	初始值	末端值	过程约束
速度/(m/s)	300	≥200	—
高度/km	13	0	—
弹道倾角/(°)	0	—	−90~90
攻角/(°)	—	—	−8~ 8
后掠角/(°)	—	—	0~60

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