Question

What should be done if a satellite in an elliptic orbit with an aphelion of 6R and a perihelion of 2R, where R = 6400 km, needs to be transferred to a circular orbit of radius 6R? [G = 6.67 x 10^{-11} SI units and M = 6 × 10^{24}kg]

• A. Decrease the velocity of the satellite by 0.95 km/s using appropriate mechanisms.
• B. Increase the velocity of the satellite by 0.95 km/s using suitable rockets.
• C. Decrease the altitude of the satellite by 6400 km using appropriate thrusters.
• D. Increase the altitude of the satellite by 6400 km through suitable adjustments.

Answer 1

Answer: (B)

Increase the velocity of the satellite by 0.95 km/s using suitable rockets.

Answer 2

To transfer a satellite from an elliptical orbit to a circular orbit, the velocity of the satellite needs to be adjusted. The required change in velocity, calculated using orbital mechanics principles, is approximately 0.95 km/s. Since the circular orbit requires a higher velocity than the elliptical orbit at its aphelion, the velocity needs to be increased.