| 李波,张旭,陈强洪,赵平,董严,曾飞.旋转尾翼火箭测试平台平衡滚速分析与弹道设计[J].装备环境工程,2021,18(3):70-76. LI Bo,ZHANG Xu,CHEN Qiang-hong,ZHAO Ping,DONG Yan,ZENG Fei.The Balancing Rotating Speed Analyses and Trajectory Design of Rolling Tail Rocker Projectile[J].Equipment Environmental Engineering,2021,18(3):70-76. |
| 旋转尾翼火箭测试平台平衡滚速分析与弹道设计 |
| The Balancing Rotating Speed Analyses and Trajectory Design of Rolling Tail Rocker Projectile |
| 投稿时间：2021-02-03 修订日期：2021-02-15 |
| DOI：10.7643/issn.1672-9242.2021.03.012 |
| 中文关键词: 旋转尾翼 火箭测试平台 动力学模型 平衡滚速 弹道设计 |
| 英文关键词:rotating tail rocket projectile flight dynamics model balancing rotating speed trajectory design |
| 基金项目: |
|
|
| Author | Institution |
| LI Bo | Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang 621999, China |
| ZHANG Xu | Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang 621999, China |
| CHEN Qiang-hong | Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang 621999, China |
| ZHAO Ping | Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang 621999, China |
| DONG Yan | Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang 621999, China |
| ZENG Fei | Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang 621999, China |
|
| 摘要点击次数: |
| 全文下载次数: |
| 中文摘要: |
| 目的 分析旋转尾翼对火箭测试平台平衡滚速的影响，基于旋转尾翼式火箭测试平台开展飞行弹道设计。方法 以旋转尾翼火箭测试平台为例，分析旋转尾翼、箭体和滚动轴承间的受力，建立旋转尾翼火箭测试平台箭体和尾翼滚转通道动力学模型，分析旋转尾翼不对称性、不同摩擦力系数时旋转尾翼对平台箭体平衡滚速的影响关系，并以倾斜有轨发射旋转尾翼火箭测试平台为例，开展弹道设计与仿真。结果 采用旋转尾翼设计，当滚转等效舵偏较大时，能够降低固定尾翼平台平衡滚转。随着滚转等效舵偏的增加，箭体的平衡滚速不会持续增加，箭体的平衡滚转速度将稳定在4.4 rad/s左右。旋转尾翼轴承摩擦力系数显著影响旋转尾翼对箭体平衡滚速的抑制作用。经过弹道设计仿真，箭体的平衡滚速为4.01 rad/s，满足试验载荷对转速的需求。结论 旋转尾翼能够有效抑制箭体的平衡滚速，基准弹道设计满足飞行试验要求。 |
| 英文摘要: |
| In order to analyze the effect of rotating tail roll speed on the rockets balance, trajectory design is launched based on the rocket projectile. In this paper, rotating tail rocket as an example, the rotating tail, the projectile and the rolling bearing force are analysed, rotating tail the rockets play body and tail roll channel dynamics model are established, and the influence of rotating tail, with asymmetry, and different coefficients of friction, on the rockets play body balance between the rolling speeds. And rocket projectile with inclined rail launch rotary tail as an example, trajectory design and scale aeromodelling are launched. Larger rolling as simulation. The simulation results show that the rotational tail design can reduce the balanced roll of the fixed tail body from 4.64 rad/s to 4.16 rad/s. With the increase of the equivalent rudder deviation, the balanced roll speed of the projectile body will not increase continuously, but will be stable at about 4.4 rad/s. The friction coefficient of the rotating tail fin bearing has a great influence on the restraining effect of the rotating tail fin on the balanced rolling speed of the projectile body. The balance roll speed of the projectile body is 4.01 rad/s, which meets the requirement of the experimental load for the speed after trajectory design and simulation. The rotating tail can effectively restrain the balanced rolling speed of the projectile body, and the standard trajectory design meets the requirements of flight test. |
| 查看全文 查看/发表评论 下载PDF阅读器 |
| 关闭 |
|
|
|
