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.

Velocity of satellite in elliptical orbit.

Tangential velocity components for the correct case of elliptical orbits. In above figure the satellite orbit corresponding to eccentricity e value of zero is a circular orbit. For a satellite the point which is closest from the earth is known as perigee. From initial position and velocity.

As the force is central angular momentum is conserved. The satellite s initial position and velocity vectors and at a given epoch. 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. 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.

The earth has an absolute surface value of g of 9 821 m s and has a radius of 6371 km. 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. We can start with the polar equation of an ellipse. And the remaining three satellite orbits are of elliptical corresponding to the eccentricity e values 0 5 0 75 and 0 9.

Its maximum and minimum velocities of satellites are 3 1 0 4 m s and 1 1 0 3 m s respectively. Determine the radius of curvature p of the orbit at a. Endgroup farcher apr 8 17 at 8 13. 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.

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. 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. Because kepler s equation has no general closed form solution for the eccentric anomaly e in terms of the mean.