速度匹配加机动辅助的滚转弹滚转角空中对准法

doi:10.3969/j.issn.1000-1093.2019.07.008

摘要/Abstract

摘要： 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。

关键词: 滚转弹, 速度匹配, 机动辅助, 卡尔曼滤波, 滚转角, 空中对准

Abstract: 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

Key words: rollingmissile, velocitymatching, maneuveringassistance, Kalmanfiltering, rollangle, airalignment

中图分类号:

V249.32⁺8

彭博，岑梦希. 速度匹配加机动辅助的滚转弹滚转角空中对准法[J]. 兵工学报, 2019, 40(7): 1390-1400.

PENG Bo, CEN Mengxi. 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.

参考文献

［1］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)
[2］苗劲松, 翟英存, 苟秋雄, 等. 基于卫星/地磁组合的弹箭滚转姿态解算方法[J]. 弹箭与制导学报, 2014,34(5):63-66.
MIAO J S, ZHAI Y C, GOU Q X, et al. Solving method for roll attitude of rocket based on global navigation satellite system/magnetic sensor[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2014,34(5):63-66.(in Chinese)
[3］闫爱天. 基于地磁传感器与MEMS陀螺仪组合姿态测量技术研究[D]. 南京:南京理工大学, 2016.
YAN A T. Research on combined attitude measurement technology based on geomagnetic sensor and MEMS gyroscope[D]. Nanjing: Nanjing University of Science and Technology, 2016.(in Chinese)
[4］田利伟, 陈国光, 孙汉琴, 等. 弹箭滚转姿态地磁测角仪的卡尔曼滤波算法[J]. 弹箭与制导学报, 2017, 37(1):139-143.
TIAN L W, CHEN G G, SUN H Q, et al.Kalman filtering algorithm of projectile rolling attitude geomagnetic goniometer[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2017,37(1): 139-143.(in Chinese)
[5］李兴隆, 姚文进, 朱立坤, 等. 捷联激光探测器组合GPS测量弹丸滚转角方法[J]. 兵工学报, 2016, 37(2):279-286.
LI X L, YAO W J, ZHU L K, et al.Projectile roll angle measurement method of a combination ofstrapdown laser detector and GPS measurement for semi-active laser terminal correction[J]. Acta Armamentarii, 2016,37(2):279-286.(in Chinese)
[6］佘浩平, 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)
[7］ WU Y X, PAN X F. Velocity/position integration formula (Ⅰ): application to in-flight coarse alignment[J]. IEEE Transactions on Aerospace and Electronic Systems, 2012,49(2):1006-1023.
[8］ WU Y X, PAN X F. Velocity/position integration formula(III): application to strapdown inertial navigation computation[J]. IEEE Transactions on Aerospace and Electronic Systems, 2013,49(2):1024-1034.
[9］杨登红. 旋转稳定弹GNSS/MIMU组合导航初始对准方法研究[D]. 北京:北京理工大学, 2015.
YANG D H. Research on initial alignment method of GNSS/IMU integrated navigation for spin-stabilized projectile[D]. Beijing: Beijing Institute of Technology, 2015.(in Chinese)

[10］杨莉. 基于GPS/SINS组合导航算法的优化设计与仿真[D]. 北京:中国科学院大学, 2015.
YANG L. Optimization design and simulation of integrated navigation algorithm based on GPS/SINS[D]. Beijing: University of Chinese Academy of Sciences, 2015.(in Chinese)
[11］ NOURELDIN A, KARAMAT T B, GEORGY J. Fundamentals of inertial navigation, satellite-based positioning and their integration[M]. Heidelberg, Baden-Württemberg, Germany: Springer-Verlag Berlin Heidelberg, 2013.
[12］ HU X M, LIU F, WENG H N. Observability analysis of MSINS/GPS complete integrated system [J]. Journal of Chinese Inertial Technology, 2011,19(1):38-45.
[13］董进龙, 莫波. 典型弹道下的火箭弹MEMS-INS/GNSS组合导航姿态误差可观性分析[J]. 兵工学报, 2014,35(6):850-856.
DONG J L, MO B. Observerbility analysis of rocket MEMS-INS/GNSS integrated navigation system attitude in classic trajectories [J]. Acta Armamentarii, 2014,35(6):850-856.(in Chinese)
[14］孔星炜, 董景新, 吉庆昌, 等. 一种基于PWCS的惯导系统可观测度分析方法[J]. 中国惯性技术学报, 2011,19(6):631-636.
KONG X W, DONG J X, JI Q C, et al. INS observable degree analysis method based on PWCS [J]. Journal of Chinese Inertial Technology, 2011,19(6):631-636.(in Chinese)
[15］ HONG S, MAN H L, RIOS J A, et al. Observability analysis of INS with a GPS multi-antenna system[J]. KSME International Journal, 2002,16(11):1367-1378.
[16］ RHEE I, ABDEL-HAFEZ M F, SPEYER J L. Observability of an integrated GPS/INS during maneuvers[J]. IEEE Transactions on Aerospace and Electronic Systems, 2004, 40(2):526- 535.

第40卷
第7期2019 年7月兵工学报ACTA
ARMAMENTARIIVol.40No.7Jul.2019

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