1) differential homing
比差导航
2) navigation error
导航误差
1.
First,ground static deviation information of GPS/GLONASS orientation system is get and is regarded as modification error of shut down point parameters while real-timely navigating,then the impact deviation is gained by calculating trajectory,that is navigation error caused by ground static deviation is get.
首先获取了GPS/GLONASS定位信息接收系统的地面静态偏差信息,将地面静态偏差作为实时导航的关机点参数修正误差,接着解算弹道求落点偏差,得到了地面静态偏差引起导航误差的大小。
2.
The simulation result shows that: if single-axle rotating modulation is used,the error caused by bias of gyros/accelerators can be compensated effectively,while navigation error caused by the initial position/velocity/attitude error can not be compensated.
捷联惯性导航系统的旋转调制技术是一种自校正方法,它能在不使用外部信息的条件下,自动补偿陀螺漂移和加速度计零偏引起的系统导航误差。
3.
It is also proposed that the closed track is propitious to eliminate the majority of navigation error.
仿真结果说明这种方法能够有效提高导航系统精度,从仿真曲线还得到了闭合航路能够大幅度消除导航误差的结论。
3) proportional navigation
比例导航
1.
Aiming at the scenario of the 3-axes stable proportional navigation,control and guide using in space-interceptors,with the analysis of three traditional operate modes of the fluid propulsion engine known as stable thrust,variant thrust and impulse thrust,the operate modes of the space-interceptor are analyzed.
针对空间拦截器采用三轴稳定的比例导航制导方案,以液体轨控发动机为动力,以液体发动机通常采用的定推力、变推力和脉冲推力3种工作方式为例,对拦截器推进装置工作方式进行了分析,为确定拦截器液体发动机类型和总体技术分析提供参考。
4) navigation ratio
导航比
5) GNE Gross Navigational Error
总导航误差
6) Effective navigation ratio
有效导航比
1.
Based on Linear Quadratic Gaussian(LQG) theory,a LQG optimal guidance law with time-variable effective navigation ratio is studied.
研究了基于线性二次型高斯(LQG)的中远程空空导弹最优制导规律,给出了有效导航比可变的LQG最优制导规律的简化形式,对有效导航比和比例系数进行了适当简化。
补充资料：奥米加导航系统(见飞机双曲线导航系统)
奥米加导航系统(见飞机双曲线导航系统)
Omega navigation system
Aomiiia daohang Xitong奥米加导航系统(omeg。。avigationsystem)见飞机双曲线导航系统。
说明：补充资料仅用于学习参考，请勿用于其它任何用途。
参考词条