In the present work, we discuss and assess the performances of Earth cylindrical shadow model (ECSM) and Earth shadow conical model (ESCM), with application to the Indian Remote Sensing (IRS), Low Earth orbiting (LEO) satellites; Cartosat-2A, Meghatropics-1, Resourcesat-2 and Oceansat-2. Both models are very simple and efficient for the prediction of eclipse states of any Earth orbiting eclipsing satellite at a given epoch. The advantage of using ESCM over ECSM is that first one predicts both states of eclipse penumbra and umbra while the later one predicts only one which, in reality, is not true. The ESCM model can be effectively useful for the precise orbit prediction and satellite operation to utilize the power properly. Earth’s equatorial radius Sun vector Sun unit vector Spacecraft ( S / C ) position vector Dot product between S / C position vector and Sun unit vector Projection vector of S / C position vector onto Sun unit vector Vector originating at the shadow axis, pointing to S / C at the projected S / C location Magnitude of the vector q ⃗ Coordinates of a point on the surface of the spherical Earth in ECI frame Components of S / C position vector r s / c ⃗ from the geo-center Vector joining Sun-edge 1 to S / C Vector joining Sun-edge 2 to S / C Components of the vector b ⃗ Components of the vector c ⃗ Vector representing the line from geo-center to Sun-edge 1 Vector representing the line from geo-center to Sun-edge 2 Unit vector which lies in the plane and perpendicular to Sun vector Vector normal to the plane Radius of the photosphere Distance between Sun and S / C Distance between Sun and point of intersection of Line 1 Distance between Sun and point of intersection of Line 2 Difference operator 
Eclipse prediction methods for LEO satellites with cylindrical and cone geometries: A comparative study of ECSM and ESCM to IRS satellites