1) Double Strapdown Inertial
双捷联惯导
1.
Study on Redundancy Technique in Double Strapdown Inertial Integrated Navigation System;
双捷联惯导的冗余技术研究
2) SINS
[英][sin] [美][sɪn]
捷联惯导
1.
Research of SINS Moving Base Transfer Alignment Based on Hybrid Annealed Particle Filter;
基于混合退火粒子的捷联惯导动基座传递对准
2.
Design and simulation on SINS self-alignment for carrier born aircraft;
舰载机捷联惯导自对准方案设计与仿真
3.
Research on Measurement Error of the SINS s Accelerator;
捷联惯导的加速度计测量误差研究
3) strapdown inertial navigation system
捷联惯导
1.
The results indicate that this method can effectively achieve the initial alignment of the strapdown inertial navigation system and the method can not only satisfy the alignment precision,but also greatly reduce the alignment time compared with the traditional method.
文中提出一种基于线性最优控制理论的捷联惯导系统初始对准方法,并完成了理论分析、设计和仿真,结果表明该方法能够有效地完成捷联惯导系统的初始对准,相对于传统方法在满足对准精度的同时可以大大缩短对准的时间,即便是存在较大失准角(小于10°),仍可以在几秒钟内收敛。
2.
Using Eulerian angle information in rudder-control-loop is a general method in the strapdown inertial navigation system(SINS) of aerocraft.
在舵偏控制回路中使用欧拉角姿态信息,是现有飞行器捷联惯导系统普遍采用的方法。
3.
Based on error analysis, the influence of error sources on strapdown inertial navigation systems is discussed.
通过误差分析 ,讨论了各种误差源对捷联惯导系统的影响 。
4) strap-down inertial navigation
捷联惯导
1.
The angular velocity was computed using accelerometers instead of angular velocity gyroscopes in gyroscope-free strap-down inertial navigation system(GFSINS).
无陀螺捷联惯导系统采用加速度计来解算载体相对惯性系的角速度,从而代替角速度陀螺仪。
2.
The advanced simulation system platform RT-LAB and software MATLAB/Simulink are expounded,the Runge-Kutta integrator models is designed,and strap-down inertial navigation simulation models based on MATLAB/Simulink is built.
介绍了仿真软件MATLAB/Simulink及先进的仿真系统平台软件RT-Lab,设计了龙格-库塔积分模块,用于解决在使用定步长求解器及数字时钟情况下的积分精度不高的问题;建立了基于MATLAB/Simulink的捷联惯性导航仿真模型;并将系统分解成一系列功能相对独立的模块,如轨迹发生模块,捷联惯导解算模块;并进行了仿真验证,得到的姿态、速度、位置误差与理论值相符,证明了仿真模型建立正确、方法采用得当、有效。
3.
According to the require of data Acquisition and data Processor in the strap-down inertial navigation system,this paper presents a new hardware scheme of navigation computer system that uses high performance DSP as core and FPGA as mainly external I/O interface.
根据捷联惯导系统中数据采集和运算处理的要求,提出了以高性能DSP为核心,由FPGA构成主要外部输入输出接口的导航计算机硬件设计方案;设计了I/F转换电路;给出了各电路的硬件结构框图和各器件的特性、选择与应用。
5) strapdown inertial navigation
捷联惯导
1.
A New Calibration of Error Parameter in Laser Gyro Strapdown Inertial Navigation System;
一种新的激光陀螺捷联惯导系统的误差参数标定方法
2.
The application of high accuracy ADS1256 converter in Strapdown inertial navigation system;
高精度ADS1256转换器及其在捷联惯导系统中的运用
3.
Power spectrum analysis for laser gyro damping system of strapdown inertial navigation
激光陀螺捷联惯导系统减振功率谱分析
6) strapdown inertial guidance
捷联惯导
1.
In order to improve the precision of initial alignment of strapdown inertial guidance system,extractive alignment method was presented by using genetic algorithm on the basis of rough alignment.
针对捷联惯导系统初始对准的精度问题,提出了在粗对准的基础上采用遗传算法进行精对准的方法,结合初始对准的特点及要求,适当选择遗传算法的主要操作进行了仿真,并与卡尔曼滤波的结果进行了比较。
2.
Based on simplified basic equation,the SINS error model in flight is set up in order to study the measurement error of IMU in strapdown inertial guidance system of manpads missile,and the influence of the error on hit accuracy is analyzed.
为了全面深入地研究单兵导弹捷联惯导系统的IMU测量误差传播特性及其对命中精度的影响,在对惯导基本方程简化的基础上建立了捷联惯导系统误差模型。
补充资料：惯捷
1.熟练敏捷。
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