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Description: ％ This program calculates Dilution of Precision with respect to a GPS *
％ receiver given its Cartesian ECEF position and the positions of four or *
％ more visible GPS satellites. It is a validation of the DOP algorithm and *
％ contains reference positions for which the DOP results are known. *
Platform: |
Size: 4603 |
Author: huguangfeng |
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Description: 大地坐标（llh）与ECEF直角坐标（xyz）间的转换
Platform: |
Size: 13551 |
Author: yh |
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Description: This diskette (version 1.0) contains demonstration programs and source codes in MATLAB (v.5.2) for algorithms listed in the textbook Global Positioning Systems, Inertial Navigation, and Integration, by M. S. Grewal, Lawrence Weill, and A. P. Andrews, published by John Wiley and Sons, 2000.
Contents: MATLAB (Version 5.2) Demonstrations & Scripts
Chapter4
ephemeris.m calculates the GPS satellite position in ECEF coordinates from its ephemeris parameters.
Chapter5
Klobuchar_fix.m calculates the ionospheric delay.
Chapter6 (shows the quaternion utilities)
Platform: |
Size: 12823 |
Author: gaoxu |
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Description: ％ This program calculates Dilution of Precision with respect to a GPS *
％ receiver given its Cartesian ECEF position and the positions of four or *
％ more visible GPS satellites. It is a validation of the DOP algorithm and *
％ contains reference positions for which the DOP results are known. *
- This program calculates Dilution of Precision with respect to a GPS* receiver given its Cartesian ECEF position and the positions of four or* more visible GPS satellites. It is a validation of the DOP algorithm and* contains reference positions for which the DOP results are known.*
Platform: |
Size: 4096 |
Author: huguangfeng |
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Description: 大地坐标（llh）与ECEF直角坐标（xyz）间的转换-Geodetic coordinates (llh) and the ECEF rectangular coordinates (xyz) to switch between
Platform: |
Size: 201728 |
Author: yh |
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Description: This diskette (version 1.0) contains demonstration programs and source codes in MATLAB (v.5.2) for algorithms listed in the textbook Global Positioning Systems, Inertial Navigation, and Integration, by M. S. Grewal, Lawrence Weill, and A. P. Andrews, published by John Wiley and Sons, 2000.
Contents: MATLAB (Version 5.2) Demonstrations & Scripts
Chapter4
ephemeris.m calculates the GPS satellite position in ECEF coordinates from its ephemeris parameters.
Chapter5
Klobuchar_fix.m calculates the ionospheric delay.
Chapter6 (shows the quaternion utilities) -This diskette (version 1.0) contains demonstration programs and source codes in MATLAB (v.5.2) for algorithms listed in the textbook Global Positioning Systems, Inertial Navigation, and Integration, by MS Grewal, Lawrence Weill, and AP Andrews, published by John Wiley and Sons, 2000.Contents: MATLAB (Version 5.2) Demonstrations
Platform: |
Size: 12288 |
Author: gaoxu |
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Description: 此matlab函数可以在ECEF和ECI坐标之中转换地点和速率信息。-This matlab function ECEF and ECI can convert the coordinates of the location and rate information.
Platform: |
Size: 2048 |
Author: 陈小摆 |
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Description: 地球坐标系ecef坐标与地理坐标系(bj54/wgs84)转换。-Ecef coordinate system and geographic coordinates (bj54/wgs84) conversion.
Platform: |
Size: 1024 |
Author: 赵思浩 |
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Description: Conversion from ECEF to LLA algorithm developed in matlab
Platform: |
Size: 1024 |
Author: libinha |
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Description: coordinatetransformation from local to ecef!
Platform: |
Size: 1024 |
Author: yang zhang |
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Description: Function convert the coordinates from ECEF to LLH
Platform: |
Size: 2048 |
Author: victor |
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Description:
Platform: |
Size: 1024 |
Author: victor |
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Description: ALM2POS computation for satellite position from almanac data file
[pos,R]=alm2pos(almanac,PRN,time) calculates the satellite position in the
Terrestial and in the Celestial reference frame for a desiderate satellite
vehicle (PRN) with almanac data (ALMANAC). The given time (TIME) can be a
scalar or also a vector. Colomn 1-3 of position (pos) are Terrestial
Coordinates (ECEF) colomn 4-6 of position are Celestial Coordinates (ECSF)
in m. Another output is the position vector of the satellite (R) in m.- ALM2POS computation for satellite position from almanac data file
[pos,R]=alm2pos(almanac,PRN,time) calculates the satellite position in the
Terrestial and in the Celestial reference frame for a desiderate satellite
vehicle (PRN) with almanac data (ALMANAC). The given time (TIME) can be a
scalar or also a vector. Colomn 1-3 of position (pos) are Terrestial
Coordinates (ECEF) colomn 4-6 of position are Celestial Coordinates (ECSF)
in m. Another output is the position vector of the satellite (R) in m.
Platform: |
Size: 2048 |
Author: Anuron |
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Description: Determine the target s ECEF position based on up to 4 sensor s measurements. The sensor has range, bearing, and elevation data. The measurements were used for Kalman filter processing.-Determine the target s ECEF position based on up to 4 sensor s measurements. The sensor has range, bearing, and elevation data. The measurements were used for Kalman filter processing.
Platform: |
Size: 3072 |
Author: David |
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Description: 地心地固（ECEF）坐标系下，基于广义最小二乘的雷达组网空间误差配准-Radar network based on generalized least square error of registration space
Platform: |
Size: 2048 |
Author: 梁苑 |
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Description: Convert WGS 84 (CTS, ECEF) Coordinates to ECI (CIS, Epoch J2000.0) Coordinates. This function has been vectorized for speed. The associated error in converting between coordinate frames is on the order of 1.2*10^-11 km when compared to STK ephemeris output.
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Size: 4096 |
Author: CYT |
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Description: 导航定位中的坐标转换,从LLA到ECEF的坐标转换-Navigation and positioning of the coordinate conversion from LLA to ECEF Coordinate Transformation
Platform: |
Size: 6144 |
Author: 三块钱 |
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Description: Convert geodetic coordinates to Earth-centered Earth-fixed (ECEF) coordinates-Convert [x y z] ECEF [m] vector to [lat lon alt] vector in [rad] and [m]
Platform: |
Size: 1024 |
Author: 杨磊 |
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Description: 最新delphi ECEF控件 ,支持到10.2 tokyo(The latest Delphi ECEF controls, support to 10.2 Tokyo)
Platform: |
Size: 77553664 |
Author: W586
|
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Description: 代码1用于将位置经纬高信息转换为地心地固坐标系下xyz信息；代码2是捷联惯导算法代码，用于将加速度计和陀螺仪输出的信息进行解算得到位置、速度和姿态信息。(Code 1 is used to convert the location of warp and weft information into XYZ information in a geocentric coordinate system; code 2 is a strapdown inertial navigation algorithm code, which is used to compute the information of accelerometers and gyroscopes to get position, speed and attitude information.)
Platform: |
Size: 11264 |
Author: 山大阿欢 |
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