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弹箭与制导学报 >

2025 , Vol. 45 >Issue 2: 176 - 183

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.02.007

面向筒式发射空地导弹的多功能整流罩机构设计方法

  • 李泽阳 , 1, 2 ,
  • 赵国宏 , 3 ,
  • 庞喻 2 ,
  • 付小武 1, 2 ,
  • 余磊 1, 2 ,
  • 解忠良 4
展开
  • 1 陆空基信息感知与控制全国重点实验室, 陕西 西安 710065
  • 2 西安现代控制技术研究所, 陕西 西安 710065
  • 3 中国兵器工业试验测试研究院, 陕西 西安 710000
  • 4 西北工业大学工程力学与土木建筑学院, 陕西 西安 710072
赵国宏(1981—), 男, 副研究员。E-mail:

李泽阳(1993—), 男, 高级工程师, 博士。E-mail:

收稿日期: 2024-11-22

  网络出版日期: 2025-05-15

基金资助

广东省基础与应用研究基金(2024A1515010406)

广东省基础与应用研究基金(2022A1515010864)

航空发动机及燃气轮机基础科学中心项目(P2022-B-Ⅲ-003-001)

收起

Multifunctional Fairing Mechanism Design Method for the Tube-launched Air-to-ground Missile

  • LI Zeyang , 1, 2 ,
  • ZHAO Guohong , 3 ,
  • PANG Yu 2 ,
  • FU Xiaowu 1, 2 ,
  • YU Lei 1, 2 ,
  • XIE Zhongliang 4
Expand
  • 1 National Key Laboratory of Land & Air Based Information Perception and Control, Xi'an 710065, Shaanxi, China
  • 2 Xi'an Modern Control Technology Research Institute, Xi'an 710065, Shaanxi, China
  • 3 Norinco Group Testing and Research Institute, Xi'an 710000, Shaanxi, China
  • 4 School of Mechanics, Civil Engineering and Architecture, Northwestern Polytechnical University, Xi'an 710072, Shaanxi, China

Received date: 2024-11-22

  Online published: 2025-05-15

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摘要

对搭载于空基平台的筒装导弹, 装备传统平面密封膜的发射筒存在气动阻力大、破膜后飞溅物威胁飞行器安全的问题。针对该问题, 研究了椭球型整流罩长径比和飞行器巡航速度对其气动特性的影响规律, 建立了整流罩气动力矩和转动角度增量的关系;基于双臂扭簧模型设计了串列扭簧整流罩机构, 建立了整流罩适配器接触力关于接触点参数的解析模型, 辨识得到最优接触点及最小接触力。在此基础上, 提出一种具备低气动阻力、无破损张开、低接触力和可自动复位的多功能整流罩机构设计方法。虚拟样机分析表明, 适配器动态接触力为224.0 N, 机构自动复位时间为17.7 ms, 结果合理可行, 该方法对空基平台搭载的筒装导弹发射筒整流罩设计具有重要借鉴意义。

关键词： 多功能整流罩; 气动特性; 复位机构; 接触力; 数值仿真

本文引用格式

李泽阳 , 赵国宏 , 庞喻 , 付小武 , 余磊 , 解忠良 . 面向筒式发射空地导弹的多功能整流罩机构设计方法[J]. 弹箭与制导学报, 2025 , 45(2) : 176 -183 . DOI: 10.15892/j.cnki.djzdxb.2025.02.007

Abstract

For the tube-launched missiles carried on air based platforms, the launchers equipped with traditional flat sealing film lead to unavoidable issues that aerodynamic drag increases and broken fairing threatens the safety of aircraft. To address the problem, the influences of the aspect ratio of ellipsoidal fairing and aircraft cruising speed on its aerodynamic characteristics are studied. The relationship between fairing aerodynamic moment and increment of rotation angle is established. Based on the model of twins torsional spring, a fairing mechanism with tandem torsional springs is designed. The analytical model for the contact force of fairing adapter and its contact point parameters is established to obtain the optimal contact point and the minimum contact force. As a result, a multifunctional fairing mechanism is proposed which is capable of reducing aerodynamic drag, nondestructively opening, reducing contact force and automatically resetting itself. The analysis results of the virtual prototype indicate that the dynamic contact force of the adapter and the reset time are respectively 224.0 N and 17.7 ms, it verifies the rationality and feasibility of the mechanism. The proposed method has important reference significance for the design of launch tube fairing of tube-launched missiles equipped on aircraft platform.

Key words： multifunctional fairing; aerodynamic characteristic; resetting mechanism; contact force; numerical simulation

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