一种滚转导弹飞行姿态的获取方法  

A Method to Get the Attitude of a Rolling Airframe Missile

作　　者：张成[1] 杨树兴[1] 

机构地区：[1]北京理工大学机电工程学院,北京100081

出　　处：《北京理工大学学报》2004年第6期481-485,共5页Transactions of Beijing Institute of Technology

基　　金：教育部跨世纪人才培养计划基金资助项目(100762021)

摘　　要：为了获取滚转导弹的飞行姿态,分析了基于两个侧向运动角速率陀螺和一个滚转角速率陀螺的滚转导弹飞行姿态遥测方案.通过算例讨论了各种误差对系统精度的影响,指出滚转角速率陀螺的测量精度是系统实现的关键.在给出的工程实例中,选用一个双轴液浮陀螺敏感导弹的侧向运动,节省了一个敏感元件.通过对实例中遥测数据的分析,发现该次飞行试验中导弹的角运动特征,为进一步的动力学分析提供了依据.该方案具有结构简单,成本低,易于实现等优点.To get the attitude information of a rolling airframe missile, a telemetry scheme based on two lateral rate gyros and a roll rate gyro is studied. Affects of the test errors on the accuracy of the system are analyzed through numerical calculations, and it is pointed out that the precision of the roll rate gyro is the linchpin of the system. In the given flight test, a two-axis liquid-floated gyroscope is adopted to replace the two lateral rate gyros. With the test data in the flight test analyzed, the angular motion characteristics of the rolling airframe missile are found, offering a basis for further dynamics analysis. This scheme is easy to realize, simple in its structure and low in cost.

关 键 词：滚转导弹 飞行姿态 遥测方法 

分 类 号：TJ760.62[兵器科学与技术—武器系统与运用工程]