基于弹道弯曲角速度单矢量的制导炮弹滚转角空中粗对准方法

杨启帆; 王江; 范世鹏; 白婵; 周永佳; 胡少勇

doi:10.12382/bgxb.2021.0707

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基于弹道弯曲角速度单矢量的制导炮弹滚转角空中粗对准方法

更新时间：2025-08-18

- 基于弹道弯曲角速度单矢量的制导炮弹滚转角空中粗对准方法
- In-flight Alignment Method of Guided Projectile Roll Angle Based on Trajectory Bending Angular Velocity Single Vector
- 兵工学报 2023年44卷第2期页码：417-427
- 作者机构：
  
  1. 北京理工大学宇航学院, 北京 100081
  2. 北京理工大学中国-阿联酋智能无人系统“一带一路”联合实验室, 北京 100081
  3. 西北工业集团有限公司, 陕西西安 710043
- 作者简介：
  
  *邮箱:fanshipeng@bit.edu.cn
- 基金信息：
  
  国家自然科学基金项目(61827901)
- DOI：10.12382/bgxb.2021.0707
  中图分类号：
- 收稿：2021-10-25，
  
  网络出版：2023-03-10，
  
  纸质出版：2023-02-28
- 稿件说明：
移动端阅览
杨启帆, 王江, 范世鹏, 等. 基于弹道弯曲角速度单矢量的制导炮弹滚转角空中粗对准方法[J]. 兵工学报, 2023,44(2):417-427.

Qifan YANG, Jiang WANG, Shipeng FAN, et al. In-flight Alignment Method of Guided Projectile Roll Angle Based on Trajectory Bending Angular Velocity Single Vector[J]. Acta Armamentarii, 2023, 44(2): 417-427.
杨启帆, 王江, 范世鹏, 等. 基于弹道弯曲角速度单矢量的制导炮弹滚转角空中粗对准方法[J]. 兵工学报, 2023,44(2):417-427. DOI： 10.12382/bgxb.2021.0707.

Qifan YANG, Jiang WANG, Shipeng FAN, et al. In-flight Alignment Method of Guided Projectile Roll Angle Based on Trajectory Bending Angular Velocity Single Vector[J]. Acta Armamentarii, 2023, 44(2): 417-427. DOI： 10.12382/bgxb.2021.0707.

摘要

制导炮弹内弹道呈现高转速、大过载的特点

其导航坐标系统滚转通道无法进行初始对准。针对以上难点问题

根据无控段飞行特性

提出一种基于弹道弯曲角速度矢量的滚转角空中粗对准方法。在无需卫星、机动辅助的条件下

利用重力引起的弹道弯曲角速度矢量作为基准

通过单矢量定姿实现滚转角对准。为消除低精度陀螺仪的零偏、轴偏角等误差的影响

分析了弹体姿态运动测量信息的频域特性

利用FIR带通滤波器提取角速率陀螺信息中弹体滚转频点处的有用分量

并采取对准起始时刻冻结弹体坐标系下的积分策略

平滑随机测量噪声

从而提高对准精度。通过数学仿真手段

探究了惯性陀螺误差对对准精度的影响。数学仿真结果表明:该方法仅利用低精度角速率陀螺即可实现在无控段快速粗对准滚转角

误差在1°左右;在飞行搭载试验中

滚转角对准误差可控制在2°以内。

Abstract

As the interior ballistics of guided projectiles feature high rotational speed and high overload

the initial alignment of roll angle can only be achieved in air. To solve this problem

a coarse roll angle alignment method based on trajectory bending angular velocity in free flight phase is proposed. Without satellite and maneuver assistance

using the trajectory bending angular velocity induced by gravity as reference

the roll angle is obtained by single vector attitude determination. Then

the frequency domain characteristics of the projectile attitude motion measurement is analyzed to reduce the impact of the zero bias

misalignment and other errors of the low accuracy gyroscope. A FIR bandpass filter is utilized to extract desired component of the angular rate measurement at the rolling frequency point. An integration strategy under the frozen projectile system at the beginning of alignment is adopted to suppress the random noise

thereby improving the performance of the alignment. The influence of inertial gyroscope error on alignment accuracy is explored by mathematical simulation. The simulation results show that through this method

fast coarse alignment of roll angle in free flight can be realized only using low precision angular rate gyroscope

and the error is about 1°. In the flight test

the roll angle alignment error can be controlled within 2°.

关键词

Keywords

references

林德福 , 祁载康 . 低速旋转制导炮弹的滚转过渡过程分析 [J ] . 战术导弹技术 , 2005 ( 5 ): 53 - 55 .

LIN D F , QI Z K . Analysis of the roll dynamic of terminal guided projectile at low roll rate [J ] . Tatical Missile Technology , 2005 ( 5 ): 53 - 55 . (in Chinese)

范世鹏 . 双通道控制滚转导弹的控制技术研究 [D ] . 北京 : 北京理工大学 , 2015 .

FAN S P . Research on control technologies for self-spinning missiles with double-channel actuator [D ] . Beijing : Beijing Institute of Technology , 2015 . (in Chinese)

武庆雅 . 旋转弹药的惯性导航与解耦控制方法研究 [D ] . 北京 : 北京理工大学 , 2015 .

WU Q Y . Research on inertial navigation and decoupling control method for spinning ammunition [D ] . Beijing : Beijing Institute of Technology , 2015 . (in Chinese)

张莺莺 , 张晓明 , 薛羽阳 . 地磁旋转弹滚转角及角速率的估计方法 [J ] . 中国测试 , 2021 , 47 ( 4 ): 38 - 43 .

ZHANG Y Y , ZHANG X M , XUE Y Y . An estimation method of roll angle and rate of spinning projectile based on geomagnetic information [J ] . China Measurement & Testing Technology , 2021 , 47 ( 4 ): 38 - 43 . (in Chinese)

张小宇 , 刘宁 , 苏中 , 等 . 基于地磁的制导炮弹滚转信息测量方法研究 [J ] . 现代电子技术 , 2020 , 43 ( 20 ): 9 - 13 .

ZHANG X Y , LIU N , SU Z , et al. Geomagnetism-based measurement method of rolling information of rolling missile [J ] . Modern Electronics Technique , 2020 , 43 ( 20 ): 9 - 13 . (in Chinese)

张晓明 , 朱孟龙 , 张莺莺 . 改进的两轴磁传感器测量弹体滚转角方法 [J ] . 传感器与微系统 , 2021 , 40 ( 8 ): 9 - 12 .

ZHANG X M , ZHU M L , ZHANG Y Y . Improved method for measuring roll angle of projectile with two-axis magnetic sensor [J ] . Transducer and Microsystem Technologies , 2021 , 40 ( 8 ): 9 - 12 . (in Chinese)

GROVES P D . GNSS与惯性及多传感器组合导航系统原理 [M ] . 北京 : 国防工业出版社 , 2011 .

GROVES P D . Principle of GNSS and inertial and multi-sensor integrated navigation system [M ] . Beijing : National Defense Industry Press , 2011 . (in Chinese)

徐云 , 王宇 , 朱欣华 , 等 . 制导炮弹用MINS/GPS滚转角在线对准方法 [J ] . 探测与控制学报 , 2015 , 37 ( 6 ): 46 - 50 .

XU Y , WANG Y , ZHU X H , et al. Roll angle in flight alignment of MINS/GPS guided projectile [J ] . Journal of Detection & Control , 2015 , 37 ( 6 ): 46 - 50 . (in Chinese)

余浩平 , 杨树兴 , 倪慧 . GPS/INS组合制导弹药空中对准的初始滚转角估计新算法 [J ] . 兵工学报 , 2011 , 32 ( 10 ): 1265 - 1270 .

SHE H P , YANG S X , NI H . New algorithms to estimate initial roll angle for in-flight alignment of GPS/INS guided munitions [J ] . Acta Armamentarii , 2011 , 32 ( 10 ): 1265 - 1270 . (in Chinese)

WU Y X , PAN X F . Velocity/position integration formula Part I:application to in-flight coarse alignment [J ] . IEEE Transactions on Aerospace and Electronic Systems , 2013 , 49 ( 2 ): 1006 - 1023 . DOI: 10.1109/TAES.2013.6494395 http://doi.org/10.1109/TAES.2013.6494395 http://ieeexplore.ieee.org/document/6494395/ http://ieeexplore.ieee.org/document/6494395/

WU Y X , PAN X F . Velocity/position integration formula Part II:application to strapdown inertial navigation computation [J ] . IEEE Transactions on Aerospace and Electronic Systems , 2013 , 49 ( 2 ): 1024 - 1034 . DOI: 10.1109/TAES.2013.6494396 http://doi.org/10.1109/TAES.2013.6494396 http://ieeexplore.ieee.org/document/6494396/ http://ieeexplore.ieee.org/document/6494396/

彭博 , 岑梦希 . 速度匹配加机动辅助的制导炮弹滚转角空中对准法 [J ] . 兵工学报 , 2019 , 40 ( 7 ): 1390 - 1400 . DOI: 10.3969/j.issn.1000-1093.2019.07.008 http://doi.org/10.3969/j.issn.1000-1093.2019.07.008 针对卫星与惯性速度匹配法对滚转角的空中对准精度不高这一问题，提出一种卫星与惯性速度匹配加机动辅助的方法。在卫星与惯性组合制导方式下，以可观测性分析为基础，机动辅助采取纵向比例导引加重力补偿制导律形式，结合卡尔曼滤波完成滚转角的空中对准，并分析机动辅助策略在不同导航比、重力补偿系数下对滚转角对准效果的影响，以及弹体名义转速拉偏、惯性组件误差拉偏对机动辅助策略的影响。仿真结果表明：在考虑卫星定速及惯性组件误差情况下，该方法能够在全弹道内实现滚转角的精对准,误差在2°以内，收敛时间10 s；可通过调节重力补偿系数改变对准的速度、精度，导航比用来保证制导稳定。卫星与惯性速度匹配加机动辅助的方法相比于卫星与惯性速度匹配法，对准效果更好；在弹体名义转速以及惯性组件误差存在拉偏情况下，对准效果受影响较小，抗干扰性较强。

PENG B , CEN M X . An air alignment method for the roll angle of rolling missiles with velocity matching and maneuvering assistance [J ] . Acta Armamentarii , 2019 , 40 ( 7 ): 1390 - 1400 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2019.07.008 http://doi.org/10.3969/j.issn.1000-1093.2019.07.008 A method of satellite/inertial velocity matching and maneuvering assistance is proposed to solve the problem of low accuracy of aligning the roll angle by a satellite/inertial velocity matching method. In the satellite/inertial integrated guidance mode, on the basis of observability analysis, a longitudinal proportional guidance law with gravity compensation is used in the maneuvering assistance, and Kalman filter is used to complete the air alignment of roll angle. The influences of maneuvering assistance strategy on the aligning effect of roll angle are analyzed in the case of different navigation ratios and gravity compensation coefficients, and the influences of nominal rotating speed deviation and inertial system error deviation on maneuvering assistance strategy are also analyzed. Simulated results show that the proposed method can be used to realize the precision alignment of roll angle in the whole trajectory with the error of less than 2° and the convergence time of 10 s under the condition of satellite and inertial system errors, and the speed and precision of alignment can be changed by adjusting the gravity compensation coefficient. The navigation ratio is used to ensure the stability of guidance loop. Moreover, under the condition that the deviations exist in the nominal rotating speed and the inertial system errors, the alignment effect is less affected and the anti-interference ability is stronger. Key

马昆 , 戴居峰 , 聂晓慧 , 等 . 一种适用于MEMS惯组的低维传递对准方法 [J ] . 导航与控制 , 2021 , 20 ( 1 ): 51 - 57 ,69.

MA K , DAI J F , NIE X H , et al. A low dimension transfer alignment method used on MEMS inertial sensor [J ] . Navigation and Control , 2021 , 20 ( 1 ): 51 - 57 ,69. (in Chinese)

王思远 , 刘海桥 , 罗世彬 . 基于高精度MEMS-INS的双轴旋转调制技术 [J ] . 传感器与微系统 , 2021 , 40 ( 2 ): 8 - 11 .

WANG S Y , LIU H Q , LUO S B . Dual-axis rotation modulation technology based on high precision MEMS-INS [J ] . Transducer and Microsystem Technologies , 2021 , 40 ( 2 ): 8 - 11 . (in Chinese)

王慧 , 管守奎 , 程涵 . 基于惯性系原理的动基座粗对准及其性能影响因素分析 [J ] . 测绘地理信息 , 2021 , 46 ( 5 ): 31 - 36 .

WANG H , GUAN S K , CHENG H . Moving base coarse alignment based on principle of inertial system and analysis of its performance influence factors [J ] . Journal of Geomatics , 2021 , 46 ( 5 ): 31 - 36 . (in Chinese)

钱杏芳 , 林瑞雄 , 赵亚男 . 导弹飞行力学 [M ] . 北京 : 北京理工大学出版社 , 2000 .

QIAN X F , LIN R X , ZHAO Y N . Missile flight mechanics [M ] . Beijing : Beijing Institute of Technology Press , 2000 . (in Chinese)

陈琦 , 陈坚强 , 袁先旭 , 等 . 方形截面弹俯仰振荡对滚转特性的影响 [J ] . 力学学报 , 2016 , 48 ( 6 ): 1281 - 1289 . DOI: 10.6052/0459-1879-16-132 http://doi.org/10.6052/0459-1879-16-132 飞行器在大气环境中飞行时，经常受阵风等的干扰，引发非指令的自激振荡，威胁飞行安全.通过建立刚体六自由度运动方程和N-S方程的松耦合求解技术，研究强迫俯仰振荡过程对滚转特性的影响.针对背风区涡流形态及横侧向气动特性复杂的方形截面飞行器，数值模拟研究了其不同攻角下的静态滚转气动特性、自由滚转运动特性，以及俯仰振荡时不同振荡速率对滚转气动和运动特性的影响.结果表明，此飞行器在静态时临界攻角约为13°，当攻角小于临界攻角时，滚转方向是静不稳定的，诱发快速滚转运动；当攻角大于临界攻角时，滚转方向是静稳定，其滚转运动是收敛的.研究发现，俯仰振荡一般会降低飞行器滚转方向静稳定或静不稳定的量值，增强滚转方向的动态稳定性.在俯仰振荡的影响下，即使滚转方向是静不稳定的，如果俯仰振荡的频率足够大，飞行器的滚转运动也可能是收敛的.

CHEN Q , CHEN J Q , YUAN X X , et al. Numerical study of the effect of forced pitching oscillation on rolling characteristics of vehicle [J ] . Acta Mechanica Sinica , 2016 , 48 ( 6 ): 1281 - 1289 . (in Chinese)

范世鹏 , 林德福 , 祁载康 , 等 . 采用脉宽调制式舵机的滚转导弹自动驾驶仪设计与研究 [J ] . 兵工学报 , 2014 , 35 ( 10 ): 1612 - 1618 . DOI: 10.3969/j.issn.1000-1093.2014.10.014 http://doi.org/10.3969/j.issn.1000-1093.2014.10.014 滚转导弹广泛采用脉宽调制(PWM)模式控制继电式操纵机构，因此研究PWM模式在滚转导弹控制中的应用。给出了两回路驾驶仪设计增益与弹体振荡频率、阻尼之间的关系；重点分析低频PWM所带来的控制耦合效应特性，讨论了耦合大小与弹体时间常数、自旋频率之间的等量关系。通过频谱分析，得到通道耦合干扰的频谱特性。制导与控制指令经PWM后频谱保持不变，但引入了与自旋频率、调制频率和弹体振荡频率相关的高频干扰。为消除控制耦合的影响，根据以上结论，提出这类导弹自动驾驶仪频带设计的一般准则，对这类导弹控制系统的总体设计有参考意义。数学仿真和半实物仿真结果表明，合理设计自旋频率、调制频率和驾驶仪频率，可以有效抑制控制耦合，提高制导精度。

FAN S P , LIN D F , QI Z K , et al. Design and research of rolling missile autopilot with pulse width modulation actuator [J ] . Acta Armamentarii , 2014 , 35 ( 10 ): 1612 - 1618 . (in Chinese)

张玉莲 , 储海荣 , 张宏巍 , 等 . MEMS陀螺随机误差特性研究及补偿 [J ] . 中国光学 , 2016 , 9 ( 4 ): 501 - 510 .

ZHANG Y L , CHU H R , ZHANG H W , et al. Characterists and compensation method of MEMS gyroscope random error [J ] . Chinese Optics , 2016 , 9 ( 4 ): 501 - 510 . (in Chinese) DOI: 10.3788/co. http://doi.org/10.3788/co. http://www.opticsjournal.net/Journals/joao.htm http://www.opticsjournal.net/Journals/joao.htm

郭敏 , 高俊浩 . 基于窗函数法设计FIR滤波器技术研究 [J ] . 数字通信世界 , 2020 ( 9 ): 6 - 8 ,35.

GUO M , GAO J H . Research on FIR filter technology based on window function method [J ] . Digital Communication World , 2020 ( 9 ): 6 - 8 ,35. (in Chinese)

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