POD of Low earth orbiting satellites with Extended Kalman Filter (EKF) based Reduced dynamic precise orbit determination (RPOD) algorithm, using ionospheric error free dual frequency code, carrier, single frequency code and carrier phase based combinations have been developed. Estimated state parameters are maximum of 44, the six orbital parameters (3D position and velocity), LEO satellite receiver clock bias, Drag coefficient (Cd), Solar Radiation Pressure coefficient (Cr), Residual accelerations in Radial, Tangent and Normal (RTN) directions in case of dual frequency code measurements, while in case of dual frequency carrier phase measurements and single frequency ionospheric error free combination (GRAPHIC), apart from the above state parameters, line of sight integer ambiguities are also estimated which can be upto 32 (number of GPS satellites). Complete range modelling is done to remove all the line of sight errors in the code and carrier phase GPS measurements to get back the true geometric range. Estimation and propagation done in Earth Centered Earth Fixed (ECEF) frame, after accounting for Pole corrections, Centrifugal and Coriolis accelerations. This is done in order to reduce the computational burden, ECEF to ECI frame conversion errors, usage of on-board resources. Harris-Priester model is used for drag modelling instead of more computationally intense MSIS model, reduced 40*40 order instead of higher order used in Geo-potential modelling. Empirical formulation for Solar Radiation Pressure (SRP) instead of component wise modelling is used in order to optimize the processing time, reduce the computational load. All these reduced modelling efforts are compensated by radial, tangential and normal (R, T, N) directions acceleration estimation.The developed algorithm is validated using data of several low earth orbiting satellites., viz., ISRO-missions of CARTO-2D,2E,2F, MICRO-01, HYSIS, MICRO-R and other foreign missions viz., CHAMP, GRACE, COSMIC satellites.