[1]贾 昂,王旭刚,李广才.变体制导炮弹气动特性分析及弹道仿真[J].弹道学报,2022,34(04):74-82.[doi:10.12115/j.issn.1004-499X(2022)04-011]
 JIA Ang,WANG Xugang,LI Guangcai.Aerodynamic Characteristics Analysis and Ballistic Simulationof Morphing Guided Projectile[J].Journal Of Ballistics,2022,34(04):74-82.[doi:10.12115/j.issn.1004-499X(2022)04-011]
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变体制导炮弹气动特性分析及弹道仿真()
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《弹道学报》[ISSN:1004-499X/CN:32-1343/TJ]

卷:
34
期数:
2022年04期
页码:
74-82
栏目:
出版日期:
2022-12-31

文章信息/Info

Title:
Aerodynamic Characteristics Analysis and Ballistic Simulationof Morphing Guided Projectile
文章编号:
1004-499X(2022)04-0074-09
作者:
贾 昂1王旭刚1李广才2
1.南京理工大学 能源与动力工程学院,江苏 南京 210094; 2.淮海工业集团有限公司,山西 长治 046000
Author(s):
JIA Ang1WANG Xugang1LI Guangcai2
1.School of Energy and Power Engineering,Nanjing University of Science and Technology,Nanjing 210094,China; 2.Huaihai Industrial Group CO.,LTD,Changzhi 046000,China
关键词:
变体制导炮弹 弹道优化 气动特性 弹道仿真 变后掠翼
Keywords:
morphing guided projectile ballistic optimization ballistic calculation variable-sweep wing
分类号:
TJ301
DOI:
10.12115/j.issn.1004-499X(2022)04-011
文献标志码:
A
摘要:
为使制导炮弹在不同飞行状态均保持较优的气动外形,提高飞行效率,增加射程,设计了一种变体制导炮弹,并开展气动参数计算、气动特性分析和弹道仿真等研究。首先根据设计指标确定变体制导炮弹的气动布局,通过迭代优化确定弹翼、鸭舵、尾翼的具体参数,并描述其控制方式和弹道特点; 随后利用工程化算法计算变体制导炮弹的气动数据,分析升力系数、阻力系数和静稳定度等参数与弹翼外形变化之间的关系; 最后根据气动特性分析的结果为所设计的变体制导炮弹制定变体方案,采用hp-自适应伪谱法,分别对变体制导炮弹和固定外形制导炮弹以射程最大为目标进行弹道优化。结果表明:所设计的变体制导炮弹满足设计指标,具有良好的气动特性和操纵性,弹道计算结果表明通过引入变体飞行技术可以使射程提升10%~22.5%,研究结果可以为今后变体制导炮弹的研究提供参考。
Abstract:
In order to maintain a better aerodynamic shape of the guided projectile in different flight states,improve the flight efficiency and increase the range,a morphing guided projectile was designed. The aerodynamic parameters calculation,aerodynamic characteristics analysis,ballistic simulation were carried out. Firstly,the aerodynamic layout of the morphing guided projectile was determined according to the design parameters,and the specific shape parameters of the wing,canard and tail fin of projectile were determined through iterative optimization,the control modes and ballistic characteristics of the morphing guided projectile were described. Then the aerodynamic data of the morphing guided projectile was calculated by using engineering algorithms,the relationship between lift coefficient,drag coefficient,static stability and the change of the projectile wing shape was analyzed. Finally,a morphing scheme was developed for the designed morphing guided projectile based on the results of aerodynamic characteristics analysis. Hp-adaptive pseudo-spectrum method was used to optimize the ballistics of the morphing guided projectile and the fixed-profile guided projectile with the goal of maximum range. The results show that the designed morphing guided projectile meets the design parameters and has good aerodynamic characteristics and maneuverability,and the ballistic calculation results show that the range can be increased by 10% to 22.5% by introducing the morphing flight technology.

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备注/Memo

备注/Memo:
收稿日期:2022-05-25
基金项目:中央高校基本科研业务费专项资金资助(30919011401)
作者简介:贾昂(1998-),男,硕士研究生,研究方向为弹箭飞行控制。E-mail:jiaang6@163.com。
通信作者:王旭刚(1979-),男,研究员,博士生导师,研究方向为飞行器制导控制。E-mail:wxgnets@163.com。
更新日期/Last Update: 2022-12-30