一种基于压敏传感器的制导炮弹寻地新方法
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摘要
为提高制导炮弹寻地精度,根据压敏传感器测量高旋弹体的方法,提出了一种基于压敏传感器制导炮弹寻地的新方法。从理论上分析了炮弹寻地的原理;进行了实验方案设计及其电路设计,解决了提高测量精度的问题;飞行试验验证表明,该方法可实现炮弹寻地和转速的精确测量。实验结果表明,该方法完全可用于制导炮弹寻地和转速测量,不仅具有灵敏度高、精度高、受外部因素影响小等特点,而且电路具有结构简单、体积小、性能优良等优点,可广泛应用于旋转炮弹的姿态控制和制导系统。
In order to improve the ground-seeking accuracy of guided projectile( GP),a new groundseeking method based on pressure sensor was proposed by using pressure sensor to measure the high-spin projectile body. The ground-seeking principle of GP was analyzed theoretically. The test scheme and its circuit were designed to improve measurement precision. The accurate measurement of ground-seeking and rotational rate can be achieved through flight-test verification. The experimental results show that the proposed method can be used for GP ground-seeking and rotational rate measurement,and it has high sensitivity and high precision,and the effect of external factors is small. The circuit has some advantages such as simple structure,small volume and good performance. The method can be widely used for attitude control and guidance system of rotating projectile.
In order to improve the ground-seeking accuracy of guided projectile( GP),a new groundseeking method based on pressure sensor was proposed by using pressure sensor to measure the high-spin projectile body. The ground-seeking principle of GP was analyzed theoretically. The test scheme and its circuit were designed to improve measurement precision. The accurate measurement of ground-seeking and rotational rate can be achieved through flight-test verification. The experimental results show that the proposed method can be used for GP ground-seeking and rotational rate measurement,and it has high sensitivity and high precision,and the effect of external factors is small. The circuit has some advantages such as simple structure,small volume and good performance. The method can be widely used for attitude control and guidance system of rotating projectile.
引文
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[2]张锐.地磁传感器在自旋导弹惯测组合中应用研究[J].航天控制,2008,26(2):41-46.ZHANG Rui.Application of geomagnetic sensors in the inertial measurement combination of spin missiles[J].Aerospace Control,2008,26(2):41-46.(in Chinese)
[3]吉训生,王寿荣.MEMS陀螺仪随机漂移误差研究[J].宇航学报,2006,27(4):640-642.JI Xunsheng,WANG Shourong.MEMS gyroscope random drift error study[J].Journal of Astronautics,2006,27(4):640-642.(in Chinese)
[4]李伟忠,孙鹏.战术导弹用MEMS陀螺仪研制进展及关键技术[J].导航与控制,2017,16(3):98-104.LI Weizhong,SUN Peng.Development and key technology of MEMS gyroscope for tactical missile[J].Navigation and Control,2017,16(3):98-104.(in Chinese)
[5]徐平,王伟,林德福.导引头隔离度对末制导炮弹制导控制的影响[J].弹道学报,2012,24(1):17-21.XU Ping,WANG Wei,LIN Defu.Influence of the isolation degree of seeker on guidance control of terminal guided projectiles[J].Journal of Ballistics,2012,24(1):17-21.(in Chinese)
[6]汪渤,彭兴泉,于增慧,等.末制导炮弹用位标器陀螺[J].中国惯性技术学报,1997(2):20-23.WANG Bo,PENG Xingquan,YU Zenghui,et al.Target seeker gyro for guided shell[J].China Inertial Technology Journal,1997(2):20-23.(in Chinese)
[7]刘志德,王勇,陈家斌,等.智能炮弹姿态测量新方法[J].计算机仿真,2010,27(6):49-52.LIU Zhide,WANG Yong,CHEN Jiabin,et al.New method for measuring the attitude of intelligent projectile[J].Computer Simulation,2010,27(6):49-52.(in Chinese)
[8]张文渊,夏群利,刘大卫.多约束制导律与导引头隔离度制导匹配性研究[J].兵工学报,2015,36(8):1473-1480.ZHANG Wenyuan,XIA Qunli,LIU Dawei.Research on guidance matching of guidance law with multiple constraints and seeker disturbance rejection rate[J].Acta Armamentarii,2015,36(8):1473-1480.(in Chinese)
[9]FRARY D J.Guided-weapon control systems[J].Electronics&Power,2010,27(7/8):538-540.
[10]牛春峰,刘世平,王中原.基于陀螺/GPS测量数据的制导炮弹滚转角空中定标原理[J].弹道学报,2011,23(3):34-36.NIU Chunfeng,LIU Shiping,WANG Zhongyuan.Inflight alignment for roll angle of guided projectile based on gyro/GPS measurement data[J].Journal of Ballistics,2011,23(3):34-36.(in Chinese)