1) inertial guidance system,inertial navigation system
惯性导航系统<火>
2) inertial navigation system
惯导系统;惯性导航系统
3) Inertial navigation system(INS)
惯性导航系统
1.
On the basis of the analysis of aviation aircraft load celetid navigation system(CNS)/inertial navigation system(INS)integrated navigation system at home and abroad,the technical performance of CNS/INS integrated navigation system from working environment,integrated patterns and navigation solution is analyzed and it is pointed out that CNS-INS integrated navigation system is more applicable to .
综述了天文—惯性组合导航在高空飞行器中的应用和发展概况,在分析了国内外装载天文导航系统(CNS)/惯性导航系统(INS)的航空飞行器基础上,从工作环境、组合模式、导航解算等方面分析了CNS/INS的技术性能,指出CNSI-NS组合导航更适用于执行长航时、高空飞行的航空飞机,能够满足航空飞行器对高精度导航系统的需要。
2.
A new fusion algorithm of the measurements from global positioning system(GPS) and inertial navigation system(INS)is presented to compensate the weaknesses of current integrated navigation system.
为了弥补现有组合导航算法的不足,提出了一种新的GPS量测数据和惯性导航系统(INS)数据的融合算法。
4) inertial navigation system
惯性导航系统
1.
Simulation and optimization of heat-transfer route of isolator in a certain type of Inertial navigation system;
某型号惯性导航系统内减振器导热路径优化仿真(英文)
2.
Study on algorithm of compensating the gyro drift for Inertial Navigation System;
惯性导航系统陀螺漂移补偿算法研究
3.
Research of unscented Kalman filter in initial alignment of inertial navigation systems;
UKF方法在惯性导航系统初始对准中的应用研究
5) inertial navigation systems
惯性导航系统
1.
Gyro-free inertial navigation systems(GF INS) come into being as a research hotspot since 1990s.
推导了加速度计的数学模型和刚体的运动模型,研究了采用6个加速度计设计无陀螺惯性导航系统的原理,设计了其安装配置方案和相应的导航参数解算算法,通过仿真试验验证了以加速度计为主要惯性元件构建惯性导航系统是可行的,并证明了6个加速度计是构建基于加速度计的无陀螺惯性导航系统的最小配置。
2.
The ground coordinates of 40 ground control points are available and used as check data for the results analysis under different accuracy level for global positioning system and inertial navigation systems(GPS/INS).
最后选用40个地面检测点,通过其在全球定位和惯性导航系统(GPS/INS)不同精度条件下地面点位变化来分析最终的模拟结果。
6) INS
惯性导航系统
1.
Analysis for Capability of INS Error-Correction Based on GPS Attitude Determination System;
GPS姿态测量系统对惯性导航系统误差修正能力分析
2.
In an INS,the stability of the output of the accelerometer is affinitive with the temperature,and the tempera- ture stability directly determines whether INS can work immediately and stably or not.
在惯性导航系统(INS)工作过程中。
3.
A simulation model of INS s errors based on the Matla b/Simulink is introduced in this paper.
利用静基座下惯性导航系统的误差方程,应用Matlab／Simulink建立了惯导误差仿真模型。
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