摘要
翼张时间直接影响制导火箭弹的精确制导和快速机动能力。为了评估翼张机构性能参数对制导火箭弹翼张时间的影响程度,本文首先建立了制导火箭弹翼张机构的刚柔耦合动力学模型,然后采用单因素分析法筛选了翼张机构的主要性能参数,最后采用响应面法(RSM)研究了主要性能参数及其交互作用对制导火箭弹翼张时间的影响规律。结果表明:转动摩擦力矩、弹体飞行速度、弹簧力是影响制导火箭弹翼张时间的主要性能参数,且转动摩擦力矩对翼张时间的影响最大;交互项弹体飞行速度和转动摩擦力矩交互作用、弹簧力和转动摩擦力矩交互作用会导致翼张时间超出设计规定值;该制导火箭弹翼张机构的弹翼转动摩擦力矩应不大于2.5 N·m。本文的研究结果可以为制导火箭弹翼张机构的设计和优化提供参考依据。
The wing opening time of guided rocket directly affects the precision guidance and fast maneuvering ability of guided rocket.In order to evaluate the effect of the performance parameters of the wing stretching mechanism on the wing opening time,the rigid-flexible coupling dynamics model of the wing stretching mechanism of guided rocket was established.Then,the main performance parameters of the wing stretching mechanism of guided rocket are screened by single factor analysis method.Finally,the effect of the main performance parameters and their interaction on the wing opening time was studied by using response surface method(RSM).The results show that the rotational friction moment,projectile velocity and spring force are the main performance parameters affecting the wing opening time of guided rocket,and the rotational friction moment has the greatest effect on the wing opening time.The interaction between projectile velocity and rotational friction moment,spring force and rotational friction moment will lead to wing opening time beyond the specified value.The rotational friction moment of the wing stretching mechanism of the guided rocket should not be higher than 2.5 N·m.The research results of this paper can provide a reference for the design and optimization of wing stretching mechanism of guided rocket.
作者
靳凯毅
韩晶
饶永红
宋卓异
李春燕
JIN Kaiyi;HAN Jing;RAO Yonghong;SONG Zhuoyi;LI Chunyan(School of Mechanical and Electrical Engineering,North University of China,Taiyuan 030051,China;Unit 32382 of PLA,Beijing 100072,China;Air Ammunition Research Institute Co.,Ltd.,Norinco Group,Harbin 150030,China;Technology Research Institute,Shanxi North Machinery Manufacture Co.,Ltd.,Taiyuan 030009,China)
出处
《中北大学学报（自然科学版）》
CAS
2023年第3期222-228,共7页
Journal of North University of China(Natural Science Edition)
基金
山西省研究生教育创新项目(2022Y598)。
关键词
弹翼张开时间
动力学仿真
响应面法
刚柔耦合动力学模型
wing opening time
dynamics simulation
response surface method
rigid-flexible coupling dynamics model
作者简介
靳凯毅(1997-),男,硕士生,主要从事制导火箭弹飞行控制系统性能与可靠性研究。
