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[Other resource] GPS_DOP DL : 0: ％ 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. *
Update : 2008-10-13 Size : 4.5kb Publisher : huguangfeng
[Other] llhandecefTrans DL : 0: 大地坐标（llh）与ECEF直角坐标（xyz）间的转换
Update : 2008-10-13 Size : 13.23kb Publisher : yh
[Other resource] GlobalPositioningSystemsInertialNavigationanditegr DL : 0: 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)
Update : 2008-10-13 Size : 12.52kb Publisher : gaoxu
[matlab] GPS_DOP DL : 0: ％ 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.*
Update : 2025-02-19 Size : 4kb Publisher : huguangfeng
[Other] llhandecefTrans DL : 1: 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
Update : 2025-02-19 Size : 197kb Publisher : yh
[matlab] GlobalPositioningSystemsInertialNavigationanditegr DL : 0: 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
Update : 2025-02-19 Size : 12kb Publisher : gaoxu
[GPS develop] ecef2eci DL : 0: 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.
Update : 2025-02-19 Size : 2kb Publisher : 陈小摆
[OpenGL program] transformation DL : 0: 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.
Update : 2025-02-19 Size : 1kb Publisher : 赵思浩
[matlab] ECEFtoLLA DL : 0: Conversion from ECEF to LLA algorithm developed in matlab
Update : 2025-02-19 Size : 1kb Publisher : libinha
[Internet-Network] lla2ecef DL : 0: coordinatetransformation from local to ecef!
Update : 2025-02-19 Size : 1kb Publisher : yang zhang
[Other] ecef2llh_iter DL : 0: Function convert the coordinates from ECEF to LLH
Update : 2025-02-19 Size : 2kb Publisher : victor
[Other] llh2ecef DL : 0: Update : 2025-02-19 Size : 1kb Publisher : victor
[GPS develop] alm2pos DL : 0: 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.
Update : 2025-02-19 Size : 2kb Publisher : Anuron
[matlab] global_6state_M DL : 0: 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.
Update : 2025-02-19 Size : 3kb Publisher : David
[matlab] ECEF_GLS DL : 1: 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
Update : 2025-02-19 Size : 2kb Publisher : 梁苑
[matlab] ECEFtoECI DL : 0: 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.
Update : 2025-02-19 Size : 4kb Publisher : CYT
[GPS develop] c DL : 0: 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
Update : 2025-02-19 Size : 6kb Publisher : 三块钱
[matlab] ecef2lla DL : 0: 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]
Update : 2025-02-19 Size : 1kb Publisher : 杨磊
[Other] DCEF DL : 0: 最新delphi ECEF控件 ,支持到10.2 tokyo(The latest Delphi ECEF controls, support to 10.2 Tokyo)
Update : 2025-02-19 Size : 73.96mb Publisher : W586
[matlab] ecef+sins DL : 0: 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.)
Update : 2025-02-19 Size : 11kb Publisher : 山大阿欢

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