带单轴稳定的惯性导航系统

 根据平台式和捷联式惯性导航系统的主要特点,如何简化平台式系统的平台结构和减小捷联式系统对陀螺大动态范围的要求,降低成本并减小体积、重量和增加可靠性,是人们十分关心的事。为此,本文提出只沿飞行器横滚轴使用一个稳定回路的惯性导航系统。文中对该系统的原理构造及误差模型进行了叙述。以误差方程为基础,利用协方差分析方法,针对短程导弹假定的机动条件和飞行轨迹对其误差传播特性进行了模拟计算。在计算程序上采用了级数迭代算法。计算的结果对实际使用提供了参考。系统的基本工作特性近似于捷联式系统,但在很大程度上降低了对陀螺动态范围的要求,使得有可能实现既简单又可靠、成本低廉的短程飞行器使用的惯性导航与制导系统。

AN INERTIAL NAVIGATION SYSTEM WITH SINGLEE- AXILE-STABILIZATION

This paper deals with the principles, error model and simulation results of an inertial navigation system with singleaxile-stabilization. The error propagation characteristic is obtained by means of covariance analysis based on the developed error model. A series iteration technique is adopted for computation. An assumed tractory of &; short-range missile is used for simulating the error covariance propagation.The principle of operation of the present system is simpler than that of a pure strap-down system and lessens the requirements of the gyro dynamic range. As a result, it is possible to utilize a cheap gyro instead of an expensive one in the execution of the same navigation and guidance missions.