The LCR-100 Gyrocompass AHRS is a north finding attitude and heading reference system based on a state-of-the-art fibre-optic gyro and micro-electromechanical (MEMS) accelerometers.
LCR- 100罗经ahrs系统是寻北姿态航向参考系统，基于最先进的光纤陀螺和微机电(MEMS)加速度计。
The state equations of the system are established on the basis of the relation between attitude error quaternion and the gyro drift.
本文以姿态误差四元数与陀螺漂移误差之间的关系为基础，构建了系统状态方程；
The laser gyro inertial surveying and attitude reference system model with incomplete inertial sensors are first derived under the body dynamic constraint.
首次推导了非完整惯性传感器配置条件下，基于载体动态约束的激光陀螺惯性测量与姿态参考模型。
The relation between the navigation errors and the attitude errors of gyro was derived by use of spherical triangle.
本文采用球面三角形原理推导了导航定位误差与陀螺姿态误差的关系式。
The conic errors produced by frequency band narrow, quantization error, and installation error of gyro and low attitude update rate were analyzed.
研究了由陀螺频带不足、量化误差和安装误差，以及姿态更新率过低造成的圆锥误差。
At last, the hardware in the loop simulation system for three-axis stabilized satellite attitude control based on PC, with reaction wheel and gyro in the loop is designed.
最后，该文设计了一个基于PC机的三轴稳定卫星姿态控制硬件在回路仿真系统，将反作用飞轮、陀螺等实物接入仿真系统。
This kind of gyro calibration is to calculate the constant drifts of gyros using the telemetry data of the sun sensors and the rate integrating gyros through twice attitude maneuvers.
此种陀螺标定需进行两次姿态机动，利用太阳敏感器和速率积分陀螺遥测数据标定陀螺的常值漂移。
Based on the simulation of the gyro attitude errors resulted from above mentioned, a simplified error equation is established and the analysis in complex domain is made.
对由此产生的陀螺姿态角误差进行了仿真分析，并在此基础上建立起与之相应的简化误差方程，对简化误差方程进行了复域分析。
The attitude error performance of electrostatic gyro should be understood and the relevant error equations must be set up in order to ensure the navigation precision of ESGM.
为了保证静电监控器的导航定位精度，需要了解静电陀螺的姿态误差特性，建立相应的误差方程。
A larger high-frequency noise in the output signal of fiber optic gyro lowers the calculation accuracy of fiber optic gyro attitude system.
光纤陀螺输出信号中存在较大的高频噪声，这降低了光纤陀螺姿态系统的解算精度。
To get high accuracy of satellite attitude determination, a new approach of satellite attitude determination system, which combines the star-sensors with gyro, is presented in the article.
为了满足军用卫星姿态测量高精度的需要，提出了基于状态估计法的陀螺仪和星敏感器组成的卫星姿态测量系统的方案。
Accelerometer of platform is used to measure the attitude of carrier. Gravity component at two input axes of DTG is calculated. The Gyro drift model is made to compensate the azimuth.
通过安装在双轴平台上的加速度计测量载体姿态，并计算重力在陀螺两个测量轴的分量，建立了陀螺漂移模型，对方位漂移进行补偿。
Methods are put forward which are used for unorthodoxy placement gyro fault detection and isolation when the three gyros have trouble by the attitude signal.
提出了利用姿态角传感器在非正交配置的陀螺仪发生三个以上的故障时进行故障检测与隔离的方法。
This paper introduces the principle of fiber optic gyro, studies the attitude algorithm of fiber optic gyro ship attitude system, introduces the quaternion algorithm and rotation vector algorithm.
对四元数法和等效转动矢量法的滚转弹姿态解算精度进行比较，并通过打击机动目标的仿真试验验证了姿态解算精度对制导精度的影响。
Based on the principle of the stabilized theory and gyro attitude measurement theory, a mathematic model was established.
从稳定和测姿原理上建立了系统的数学模型，归纳出陀螺安装三种不同方法。
Utilizing celestial observations from star trackers, a 6-state extended Kalman filter is adopted to correct the satellites attitude error as well as gyro bias error.
利用星敏感器测量所得的恒星星光方向信息，采用六状态变量推广卡尔曼滤波，得到卫星姿态误差和陀螺漂移误差信息并进行相应的修正。
Utilizing celestial observations from star trackers, a 6-state extended Kalman filter is adopted to correct the satellites attitude error as well as gyro bias error.
利用星敏感器测量所得的恒星星光方向信息，采用六状态变量推广卡尔曼滤波，得到卫星姿态误差和陀螺漂移误差信息并进行相应的修正。
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