摘要
星光/惯性组合制导方式集中了两种方式的优点,可在导弹飞出大气层后通过对导航星的观测校正陀螺仪误差系数。在研究了星光导航的特点和陀螺仪误差特性的基础上,提出了通过旋转弹体观测特定位置的导航星,利用星光导航系统分离陀螺仪漂移误差系数的方法。结果表明:利用导航恒星高精度基准可以分离陀螺仪漂移误差系数,准确地确定陀螺仪漂移误差模型,对于提高导弹的精度具有重要意义。
Stellar-inertial integrated guidance possesses the advantages of both the stellar guidance system and the inertial guidance system,and possesses the capacity of correcting the gyroscope error coefficient through observation on the navigation stars when a missile flies out of the atmosphere.Through observation on selected stars by rotating the missile,a method for separating the gyroscope drift error coefficient is proposed by the stellar navigation system,which based on studying of the characters of stellar navigation and gyroscope error.The result shows that gyroscope drift error coefficient can be separated with accurate standard of navigation stars,and obtaining the mode of gyroscope drift error is important to enhance the accuracy of missile.
出处
《飞行力学》
CSCD
北大核心
2010年第6期80-82,共3页
Flight Dynamics
关键词
星光导航
陀螺仪漂移
误差分离
stellar navigation
gyroscope drift
error separation
