Velocity Of Satellite In Elliptical Orbit

Its maximum and minimum velocities of satellites are 3 1 0 4 m s and 1 1 0 3 m s respectively.

Velocity of satellite in elliptical orbit. An orbit equation defines the path of an orbiting body around central body relative to without specifying position as a function of time if the eccentricity is less than 1 then the equation of motion describes an elliptical orbit. A satellite in a low orbit or low part of an elliptical orbit moves more quickly with respect to the surface of the planet than a satellite in a higher orbit or a high part of an elliptical orbit due to the stronger gravitational attraction closer to the planet. As the force is central angular momentum is conserved. A satellite moves in elliptical orbit about a planet.

The earth has an absolute surface value of g of 9 821 m s and has a radius of 6371 km. R a 1 e2 1 ecos 1 the velocity of an object in polar coordinates is v v rrˆ v ˆ 2 r rˆ r ˆ 3 differentiating 1 we get r dr d 4 ae 1 e2 sin 1 ecos 2 5. 16 000 km a 13 860 km 1 8000 km problem 2 126. For a satellite the point which is closest from the earth is known as perigee.

And the remaining three satellite orbits are of elliptical corresponding to the eccentricity e values 0 5 0 75 and 0 9. The satellite s initial position and velocity vectors and at a given epoch. Begingroup photon at positions a and b the velocity of the satellite is at right angles to the straight line joining the centre of the earth to the satellite. 2 126 an earth satellite which moves in the elliptical equatorial orbit shown has a velocity v in space of 17 970 km h when it passes the end of the semi minor axis at a.

From initial position and velocity. In above figure the satellite orbit corresponding to eccentricity e value of zero is a circular orbit. When the satellite is in the part of its orbit closest to the earth it moves faster because the earth s gravitational pull is stronger. An elliptical orbit also called an eccentric orbit is in the shape of an ellipse in an elliptical orbit the satellite s velocity changes depending on where it is in its orbital path.

Because kepler s equation has no general closed form solution for the eccentric anomaly e in terms of the mean. Tangential velocity components for the correct case of elliptical orbits. We can start with the polar equation of an ellipse.