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弹箭与制导学报 >

2025 , Vol. 45 >Issue 2: 208 - 214

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.02.011

导弹弹射对折叠舵展开过程影响研究

  • 贾骏恺 ,
  • 张广军 ,
  • 杨海洋 ,
  • 钟山 ,
  • 刘广
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  • 上海机电工程研究所, 上海 201109
杨海洋(1991—), 男, 工程师, 博士。E-mail:

贾骏恺(1997—), 男, 工程师, 硕士。E-mail:

收稿日期: 2025-02-20

  网络出版日期: 2025-05-15

收起

Research on the Influence of Missile Ejection on the Deployment Process of Folding Rudder

  • JIA Junkai ,
  • ZHANG Guangjun ,
  • YANG Haiyang ,
  • ZHONG Shan ,
  • LIU Guang
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  • Shanghai Electro-mechanical Engineering Institute, Shanghai 201109, China

Received date: 2025-02-20

  Online published: 2025-05-15

Fold

摘要

为深入研究导弹空中弹射工况对折叠舵展开过程的影响, 针对一种无机械限位结构的扭杆式折叠舵, 首先采用ADAMS分析其动力学响应。然后通过高速摄影对折叠舵地面展开试验进行观测, 获得折叠舵真实的结构动力性能, 并根据实验结果修正动力学仿真的模型参数。考虑空中弹射工况下弹体姿态变化对折叠舵展开过程的影响, 通过地面弹射试验测量得到弹射装置对弹体的弹射力, 采用CFD仿真计算舵面在机腹复杂流场环境下展开过程中受到的时变气动力, 建立了包含弹射装置弹射力及气动阻力的折叠舵展开动力学模型, 分析了不同外舵解锁时刻及气动力拉偏工况下的舵面展开失败风险。最后根据仿真结果给出了外舵解锁时刻的合理设计范围, 为折叠舵的工程设计和应用提供了参考。

关键词： 折叠舵; 弹射工况; 动力学仿真

本文引用格式

贾骏恺 , 张广军 , 杨海洋 , 钟山 , 刘广 . 导弹弹射对折叠舵展开过程影响研究[J]. 弹箭与制导学报, 2025 , 45(2) : 208 -214 . DOI: 10.15892/j.cnki.djzdxb.2025.02.011

Abstract

In order to study the influence of the missile ejection condition in initial phaseon the deploying process of folding rudders, ADAMS is used to analyze the dynamic response of a torsion bar folding rudders without mechanical limit structure. The actual structural dynamic performance of the folding rudders is obtained through the observation of the folding rudders deploying test on the ground by mean of high-speed photography, and the model parameters of the dynamic simulation are modified according to the experimental results. Considering the impact of missile body attitude variations during aerial ejection on the folding rudders deploying process, the ejection force of the ejection device on the missile is measured by the ejection test on the ground, and CFD simulation is used to calculate the time-varying aerodynamic force experienced by the control surface of the rudders when they are deployed under the complex flow field of the plane belly, a dynamic deployment model for the rudders is established, which involving both ejection device force and aerodynamic resistance. The failure risks of folding rudders deployingt process are analyzed under multiple external folding rudder unlock time conditions and aerodynamic force deviations. Based on simulation results, a reasonable design range for external folding rudder unlock time is proposed. This work provides valuable reference for the engineering design and application of folding rudder.

Key words： folding rudder; ejection condition; dynamic simulation

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