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Description: 一篇确定捷联惯导初始姿态的专利文章，通过设置监控陀螺对其他三个陀螺进行测漂-A determined attitude SINS initial patent articles, by setting the monitor to the other three gyroscopes to measure gyro drift
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Size: 627712 |
Author: liwei |
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Description: 惯性测量组件Mti进行数据采集，利用陀螺和加速度计数据进行捷联姿态角解算，采用四元数更新算法，解算周期可调。-Inertial measurement components MTI data collection, the use of gyro and accelerometer data inertial attitude angle solver, using quaternion update algorithms, solvers adjustable cycle.
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Size: 123904 |
Author: Susan |
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Description: 针对三轴稳定卫星的姿态控制系统,在离散事件仿真平台OMNeT ++的
基础上,建立了一个以星敏感器和陀螺为敏感器,反作用飞轮为执行机构的闭环
控制仿真系统。采用双矢量定姿算法和P ID控制算法,对该卫星在对地定向模
式下的控制精度进行了仿真。仿真结果清晰地反映了星敏感器和反作用飞轮输
出延时对控制精度的影响。整个仿真系统符合面向对象和模块化的程序设计理
念,并实现了仿真程序的重用。-For the three-axis stabilized satellite attitude control system, discrete event simulation platform for OMNeT++ based on the establishment of a star tracker and gyro for the sensor, Reaction Wheel for the implementation of closed-loop control simulation system bodies. Dual-vector attitude determination algorithm and P ID control algorithm, the satellite-to-ground directional mode, the control precision of the simulation. The simulation results clearly reflect the star tracker and reaction flywheel output delay on the control precision effects. Consistent with the simulation system and modular object-oriented programming concepts, and realize the reuse of the simulation program.
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Size: 460800 |
Author: little |
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Description: coning_atti:基于角速率输入的1～5子样等效转动矢量姿态仿真程序。
coning_atti_imu_error：等效转动矢量法仿真程序，包含1～4子样的各种等效转动矢量法，以读文件形式读取IMU输出参数，IMU参数由wnbb_error事先生成。
wnbb_error:用来产生带IMU误差的标准圆锥运动Gyro输出参数。 -coning_atti: Based on the input angular rate of 1 to 5 sub-sample rotation vector attitude simulation program. coning_atti_imu_error: rotation vector method simulation program, including 1 to 4 sub-sample of the various rotation vector method to read file format to read the output parameters IMU, IMU parameters generated by the wnbb_error advance. wnbb_error: used to generate the error with a standard cone movement IMU Gyro output parameters.
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Size: 902144 |
Author: Kaksus |
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Description: 一、数据说明：
1：惯导系统为指北方位的捷连系统。初始经度为116.344695283度、纬度为39.975172度,高度h为30米。
初速度为v0=[0.000048637 0.000206947 0.007106781]，飞行高度不变。
2：jlfw中为600秒的数据，陀螺仪和加速度计采样周期分别为为1/80秒和1/80秒。
3：初始姿态角为[0.120992605 0.010445947 91.637207]（俯仰，横滚，航向,单位为度）,
jlfw中保存的为比力信息f_INSc(单位m/s^2)、陀螺仪角速率信息wib_INSc(单位rad/s)，排列顺序为 一~三行分别为东、北、天向信息.
4: 航向角以逆时针为正。
5:地球椭球长半径re=6378245 地球自转角速度wie=7.292115147e-5 重力加速度g=g0*(1+gk1*c33^2)*(1-2*h/re)/sqrt(1-gk2*c33^2)；
g0=9.7803267714 gk1=0.00193185138639 gk2=0.00669437999013 c33=sin(lat纬度) -First, data on:
1: inertial navigation system that links the north bit of the Czech system. Initial longitude 116.344695283 degrees latitude 39.975172, height h is 30 meters.
Initial speed of v0 = [0.000048637 0.000206947 0.007106781], the same altitude.
2: jlfw for 600 seconds of data, gyroscopes and accelerometers were sampling period of 1/80 sec and 1/80 seconds.
3: Initial attitude angle [0.120992605 0.010445947 91.637207] (pitch, roll, heading, in units of degrees),
jlfw than the power saved information f_INSc (unit m/s ^ 2), angular rate gyro information wib_INSc (units of rad/s), in the order of 1 ~ three lines were east, north, days to the information.
4: The heading angle is positive counterclockwise.
5: Earth ellipsoid long radius re = 6378245 Earth s rotation angular velocity wie = 7.292115147e-5 acceleration due to gravity g = g0* (1+ gk1* c33 ^ 2)* (1-2* h/re)/sqrt (1-gk2* c33 ^ 2)
g0 = 9.7803267714 gk1 = 0.00193185138639 gk2 = 0.00669437999013
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Size: 401408 |
Author: 袁刚平 |
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Description: 惯性导航的MATLAB算法，根据陀螺与加表的值计算姿态-MATLAB inertial navigation algorithm, based on gyro and attitude add value table
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Size: 2048 |
Author: 新一 |
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Description: 航天常用姿态确定敏感器组合，太阳敏感器+速率陀螺+轨道罗盘，具体数据含义请参考章仁为的<《卫星姿态控制》>-Spacecraft attitude determination sensors commonly used in combination, sun sensor+ rate gyro compass+ tracks, the meaning of specific data please refer to Chapter Ren' s < " Satellite Attitude Control" >
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Size: 13057024 |
Author: 云清 |
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Description: 用Matlab编写的轨迹发生器，输入初始的位置速度，姿态角，姿态变化等信息，模拟得到陀螺仪输出和加速度计的输出-Written with the Matlab path generator, enter the initial position, velocity, attitude, attitude changes and other information, the simulated gyro output and the output of the accelerometer
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Size: 3072 |
Author: zhihua |
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Description: 该程序包括了飞行器轨迹计算、陀螺和加速度计的采样输入、以及由四元素解算出的飞行器姿态、位置、速度-The program includes the aircraft trajectory calculation, the sampling gyro and accelerometer input, and the solution calculated by the four elements of aircraft attitude, position, velocity
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Size: 2048 |
Author: 苏钰 |
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Description: 关于ADIS16405的三轴陀螺姿态计算程序，用的是四阶龙格库塔法，单片机是STM32F103，对于ADIS16405的SPI采样是模拟方式，验证通过非常实用-About the ADIS16405 the axis gyro attitude calculation procedure, using a fourth order Runge-Kutta method，SCM is the STM32F103 analog mode, the sampling of for ADIS16405 the SPI is verified by practical
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Size: 491520 |
Author: 建刚 |
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Description: 通过IIC读取陀螺仪数据，在1602上显示，及用串口实时传送到电脑上位机。-Gyroscope data read by the IIC in the MCU, 1602, and transmitted in real time to a computer host computer using the serial.
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Size: 49152 |
Author: Tony Wong |
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Description: 求解陀螺仪的姿态角，采用四元素的四阶龙格库塔法求解，含姿态初始四元素的确定。-Solving gyro attitude angle, using the four elements of the fourth-order Runge-Kutta method to solve, including the initial four elements determined attitude.
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Size: 1024 |
Author: bojue |
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Description: 求解陀螺仪的姿态角，采用四元素的四阶龙格库塔法求解。-Solving gyro attitude angle, using the four elements of the fourth-order Runge-Kutta method to solve.
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Size: 1024 |
Author: bojue |
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Description: 平衡车，小车直立，算法控制，PID，陀螺仪姿态角控制-The balance of the car, the car upright, control algorithm, PID, the gyro attitude angle control
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Size: 105472 |
Author: 王春林 |
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Description: 四轴飞行器程序，含陀螺仪姿态角显示及其控制，稳定易懂，运用PID算法，卡尔曼滤波-Four axis aircraft program, display containing gyro attitude and attitude control, stable and easy to understand, the use of PID algorithm, Calman filter
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Size: 376832 |
Author: 王春林 |
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Description: 陀螺仪姿态解算 四元数
捷联矩阵的初始值计算初始四元数值
用毕卡法求解四元数更新矩阵，即捷联矩阵-Gyro attitude solution
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Size: 33792 |
Author: young |
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Description: TI公司MSP430系列单片机，MPU6050三轴陀螺仪姿态结算。包括卡尔曼滤波，四元数，平滑滤波。-MSP430 TI series microcontroller, MPU6050 three axis gyro attitude settlement. Including Calman filter, four yuan, smooth filter. MSP430 TI series microcontroller, MPU6050 three axis gyro attitude settlement. Including Calman filter, four yuan, smooth filter.
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Size: 480256 |
Author: 庄灿 |
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Description: 陀螺仪姿态解算- Gyro attitude calculation
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Size: 6358016 |
Author: sunxiangran |
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Description: 陀螺仪姿态解算,四元数,捷联矩阵的初始值计算初始四元数值(Gyro attitude algorithm, quaternion, the initial value of strapdown matrix numerical calculating the initial four yuan)
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Size: 32768 |
Author: 麦芒的生活
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Description: 本系统为两轮自平衡小车系统，由STM32单片机控制模块，陀螺仪姿态检测模块，电机驱动模块，电源供电模块等组成。陀螺仪MPU-6050模块负责采集平衡小车的角度信号以及角速度信号，并传给单片机；STM32单片机控制模块处理姿态角数据后，通过PID算法调节电机驱动电压，以控制两轮小车达到平衡；电机驱动模块负责接收单片机输出的控制信号，驱动两个直流电机的转速和方向，编码器将电机的速度和方向反馈给单片机控制器；电源模块负责各个模块的供电。通过系统的硬件软件设计、测试，证明了两轮自平衡小车能在±5 °范围内保持平衡。(This system is a two wheeled self balancing car system, which is composed of STM32 MCU control module, gyro attitude detection module, motor drive module, power supply module and so on. The gyroscope MPU-6050 module is responsible for collecting the balance of the car of the angle signal and angular velocity signal, and transmitted to the microcontroller; STM32 MCU control module processing attitude angle data, through the PID algorithm to adjust the driving voltage, to control the balance of the car balance; the motor drive module is responsible for receiving the control signal output of the microcontroller, drive two DC motor speed and the direction, speed and direction of the motor encoder feedback to the controller; the power supply module is responsible for each module. Through the system hardware and software design, test, proved that the two wheeled self balancing vehicle can keep balance in the range of 5 degrees.)
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Size: 3494912 |
Author: 李雨君
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