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no gyro inertia measuring combination 无陀螺惯性测量组合
In this paper the problem of calibrating the gyro static drift parameters of inertial measurement unit (IMU) is studied. 本文研究了捷联惯性组件中陀螺静态漂移参数的标定问题。
A new calibration technique was proposed for strapdown inertial measurement unit according to simplified model of ring laser gyro(RLG) and quartz accelerometer. 根据激光陀螺和石英加速度计的简化输出模型,推导并提出了一种新的激光陀螺惯性测量组合标定方法。
The inertial measurement unit, gyro, accelerometer and data interface unit etc are also introduced in detail, Finally, thispaper recommends system operation and flight test result. 详细介绍了惯性测量装置、陀螺仪、加速度表、数据接口单元等。最后介绍了系统工作和飞行试验结果。
A system which only uses accelerometers but has not gyro is called Gyroscope Free Strap-down Inertial Measure System (GFSIM). 无陀螺捷联惯性测量系统是把加速度计直接安装在载体上，舍弃陀螺仪的捷联惯性测量系统。
The closed-loop interference fiber optic gyroscopes and strapdown inertial measurement unit are introduced. 介绍了闭环方案的干涉型光纤陀螺仪和捷联惯性测量组合。
Abstract：Parameters calibration of output model of accelerometers in inertial measurement unit (IMU) is described. 摘要：研究了捷联惯导系统惯性测量组合中加速度计标度因数和安装误差的标定问题。
Gas-Driven Gyro Inertial Platform 气动陀螺惯性平台
The errors of Inertial Measurement Unit(IMU) affect the accuracy of the system a lot and also determine the impact point error of missiles directly. 弹上惯测组件(IMU)的误差是影响系统导航精度的重要因素,并直接决定导弹的落点偏差。
A new nine-accelerometer configuration of non-gyro inertial measurement unit(NGIMU) is presented,with its experiment system built. 提出了九加速度计无陀螺惯性测量组合(NGIMU)配置方案,并建立了其实验系统。
The errors of Inertial Measurement Unit (IMU) affect the accuracy of the system a lot and also determine the impact point error of missiles directly. 摘要弹上惯测组件(IMU)的误差是影响系统导航精度的重要因素，并直接决定导弹的落点偏差。
Non-gyro micro inertial measurement unit (NGIMU) uses only accelerometers replacing gyroscopes to compute the motion of a moving body. 摘要无陀螺惯性测量技术是利用加速度计代替传统的陀螺，构成无陀螺惯性测量组合(NGIMU)实现制导的。
Non-gyro inertial measurement unit (NGIMU) uses accelerometers instead of gyroscopes to compute the motion of a moving body. 无陀螺惯性测量技术是利用加速度计代替传统的陀螺,构成无陀螺惯性测量组合实现制导的。
In the 1990s, combined use of GPS and inertial measurement unit (IMU) was studied to determine the orientation parameters during the photo flights in aerial photography. 20世纪90年代以来,国际摄影测量界开始研究采用GPS/IMU组合导航系统(POS系统)来获取像片摄影时的空间方位,以完全取代摄影测量加密。
This paper puts a new information fusion way about an integrated navigation system composing of micro inertial measurement units,GPS,air data system and magnetometer. 针对微小型惯性测量单元、GPS、大地数据系统和磁强计组成的组合导航系统,提出一种新的信息融合方法。
The equations use this method show the system s inertial effect roundly,and the influence imposed on inertial measurement errors by the overloading and vibration compound envi. 该方法建立的方程全面反映了系统的惯量效应和过载振动复合作用对惯性器件的影响。
To decrease the cost of calibrating MEMS inertial measurement unit(IMU),this paper proposes an approach to calibrating MEMS IMU by means of machine vision technique. 为了降低MEMS惯性测量组合(IMU)的测试成本,提出一种借助于机器视觉技术标定MEMS惯性测量组合的方法。
The algorithm can meet the precision requirement in application,and is effective and feasible in error compensation of strapdown inertial measurement system. 该算法能够满足应用的精度要求,对捷联惯性测量系统的误差补偿有一定的有效性和可行性。
This non sequitur invalidates his argument. 他不根据前提推理因而论证无效。
To decrease the cost of calibrating MEMS inertial measurement unit(IMU), this paper proposes an approach to calibrating MEMS IMU by means of machine vision technique. 摘要为了降低MEMS惯性测量组合(IMU)的测试成本，提出一种借助于机器视觉技术标定MEMS惯性测量组合的方法。