基于Hermite插值的制导炮弹姿态旋转矢量优化方法

doi:10.3969/j.issn.1000-1093.2018.10.020

兵工学报 ›› 2018, Vol. 39 ›› Issue (10): 2056-2065.doi: 10.3969/j.issn.1000-1093.2018.10.020

基于Hermite插值的制导炮弹姿态旋转矢量优化方法

邓志红¹，汪进文¹，尚剑宇¹，张翔^1，2

（1.北京理工大学自动化学院，北京 100081； 2.中国兵器工业集团有限公司西安电子工程研究所，陕西西安 710100）

收稿日期:2018-01-23 修回日期:2018-01-23 上线日期:2018-11-19
作者简介:邓志红（1974—），女，教授，博士生导师。E-mail：dzh_deng@bit.edu.cn；
汪进文（1994—），男，硕士研究生。E-mail：javedwjw@163.com
基金资助:
武器装备预先研究项目（7131457）

Optimization of Rotation Vector of Guided Projectile Attitude Based on Hermite Interpolation

DENG Zhi-hong¹, WANG Jin-wen¹, SHANG Jian-yu¹, ZHANG Xiang^1,2

(1.School of Automation, Beijing Institute of Technology, Beijing 100081, China; 2.Xi'an Electronic Engineering Research Institute, China North Industries Group Corporation Limited, Xi'an 710100, Shaanxi, China)

Received:2018-01-23 Revised:2018-01-23 Online:2018-11-19

摘要/Abstract

摘要： 在制导炮弹姿态解算过程中，角增量提取精度对姿态解算精度的影响显著，为此提出一种Hermite 插值二子样角增量提取算法。进一步优化Hermite插值公式的系数，得出优化Hermite插值二子样角增量提取算法。在锥动环境下，将该算法与Lagrange插值三子样角增量提取算法进行仿真和试验对比。结果表明：采用所提出的Hermite插值二子样角增量提取算法的姿态解算精度优于Lagrange插值，且优化Hermite插值更适用于制导炮弹姿态解算的实际情况；该算法不仅适用于制导炮弹高动态环境，而且在同样精度条件下，可降低姿态更新采样频率，降低了对导航计算机的要求。

关键词: 制导炮弹, 高动态锥动环境, 旋转矢量, 角增量提取, Hermite插值

Abstract: The angular incremental extraction accuracy has a significant effect on the attitude resolving accuracy in the attitude algorithm of guided projectiles. A Hermite interpolation-based extraction algorithm of two-sample angular increment is presented, and the coefficient of Hermite interpolation formula is optimized further. Then a Hermite interpolation algorithm for two-sample angular increment extraction is proposed. In the cone dynamic environment, the proposed algorithm is compared with the Lagrange interpolation three-sample angular increment extraction algorithm. The results show that the accuracy of attitude estimation using the proposed algorithm is better than that of Lagrange interpolation. The optimization of the Hermite interpolation is more suitable for the actual situation of guided projectile attitude algorithm. The algorithm not only adapts to the high dynamic environment of projectile, but also reduces the sampling frequency of attitude updating under the same precision condition and reduces the requirement of navigation computer. Key

Key words: guidedprojectile, highdynamicconedynamicenvironment, rotationvector, angularincrementextraction, Hermiteinterpolation

中图分类号:

TJ413⁺.6

邓志红，汪进文，尚剑宇，张翔. 基于Hermite插值的制导炮弹姿态旋转矢量优化方法[J]. 兵工学报, 2018, 39(10): 2056-2065.

DENG Zhi-hong, WANG Jin-wen, SHANG Jian-yu, ZHANG Xiang. Optimization of Rotation Vector of Guided Projectile Attitude Based on Hermite Interpolation[J]. Acta Armamentarii, 2018, 39(10): 2056-2065.

参考文献

［1］刘佳乐. 高动态环境下弹体姿态测量技术研究与实现[D]. 南京：南京理工大学, 2017.
LIU Jia-le. Research and implementation of projectile attitude measurement in high dynamic environment[D]. Nanjing: Nanjing University of Science and Technology, 2017.(in Chinese)
[2］邓志红, 付梦印, 张继伟, 等. 惯性器件与惯性导航系统[M]. 北京:科学出版社, 2012.
DENG Zhi-hong, FU Meng-yin, ZHANG Ji-wei, et al. Inertial devices and inertial navigation system[M]. Beijing: Science Press, 2012. (in Chinese)
[3］秦永元. 惯性导航[M]. 北京:科学出版社, 2014.
QIN Yong-yuan. Inertial navigation[M]. Beijing: Science Press, 2014. (in Chinese)
[4］戚九民, 陈国光, 田晓丽, 等. 高动态和角速率输入下捷联算法比较研究[J]. 应用基础与工程科学学报, 2005(增刊1):101-107.
QI Jiu-min, CHEN Guo-guang, TIAN Xiao-li, et al. A comparative study on high dynamic and angular velocity input ［J］. Journal of Basic Science and Engineering, 2005(S1):101-107. (in Chinese)
[5］王俊璞, 金志华. 基于角增量提取的旋转矢量算法研究[J]. 导航与控制, 2009, 8(3):1-5,10.
WANG Jun-pu, JIN Zhi-hua. Rotation vector attitude algorithms based on the integration of angular rate[J]. Navigation and Control, 2009, 8(3):1-5,10. (in Chinese)
[6］ Chu H R, Zhang Y, Jia H G. Three-sample rotation vector algorithm with angular rate input[C]∥Proceedings of International Conference on Mechanic Automation & Control Engineering. Inner Mongolia, China:IEEE, 2011:5469-5472.
[7］焦留芳, 许晖, 石秀华, 等. 基于角增量提取改进算法的旋转矢量法[J]. 鱼雷技术, 2010, 18(1):53-56.
JIAO Liu-fang,XU Hui,SHI Xiu-hua,et al. An orientation vector algorithm based on improving angle increment extraction[J]. Torpedo Technology, 2010, 18(1):53-56. (in Chinese)
[8］程海彬, 鲁浩, 任宏光. 陀螺角速率输入下的姿态算法比较[J]. 航空兵器, 2007(1):18-21.
CHENG Hai-bin, LU Hao, REN Hong-guang. Compare of attitude algorithms for gyro rate input[J]. Aero Weaponry, 2007(1):18-21. (in Chinese)
[9］李庆扬, 关治, 白峰杉. 数值计算原理[M]. 北京:清华大学出版社, 2000.
LI Qing-yang, GUAN Zhi, BAI Feng-shan. Numerical calculation principle[M]. Beijing: Tsinghua University Press, 2000. (in Chinese)

[10］吴新元. 一个高精度数值积分公式[J]. 计算物理, 1988, 2(4): 95-99.
WU Xin-yuan. A high-precision numerical integration formula [J]. Computational Physics, 1988, 2(4):95-99. (in Chinese)
[11］刘彬清, 任亚娣. Newton-Cotes数值求积公式的渐近性[J]. 上海大学学报:自然科学版, 2002, 8(6):503-506.
LIU Bin-qing, REN Ya-di. The asymptotic behavior of the integrative formula for the value of Newton-Cotes[J]. Journal of Shanghai University:Natural Science Edition, 2002, 8(6):503-506. (in Chinese)
[12］ Lee J G, Mark J G, Tazartes D A, et al. Extension of strapdown attitude algorithm for high-frequency base motion[J]. Journal of Guidance, Control & Dynamics, 1990, 13(4):738-743.
[13］ Miller R B. A new strapdown attitude algorithm[J]. Journal of Guidance, Control & Dynamics, 1983, 6(4):287-291.
[14］林鹭, 黄旭东. 拉格朗日插值多项式的一种并行算法[J]. 厦门大学学报:自然科学版, 2004, 43(5):592-595.
LIN Lu,HUANG Xu-dong. A parallel algorithm for the interpolation polynomial of Lagrange [J]. Journal of Xiamen University:Natural Science, 2004, 43(5):592-595. (in Chinese)
[15］龙爱芳, 胡军浩. 基于Hermite插值的高精度数值积分公式[J]. 华侨大学学报:自然科学版, 2013, 34(3):349-352.
LONG Ai-fang, HU Jun-hao. A high precision numerical integration formula based on Hermite interpolation[J]. Journal of Overseas Chinese University: Natural Science, 2013, 34(3):349-352. (in Chinese)

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ARMAMENTARIIVol.39No.10Oct.2018

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[13]	1:繆玲娟;2:林丽. 减小动态误差的捷联系统姿态算法研究[J]. 兵工学报, 2000, 21(3): 229-232.
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基于Hermite插值的制导炮弹姿态旋转矢量优化方法

Optimization of Rotation Vector of Guided Projectile Attitude Based on Hermite Interpolation

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