pureouchies4717
- 98
- 0
i solved it. thanks to all who responded
Last edited:
The discussion centers on calculating the velocity required for a communication satellite to transition from a 300 km orbit to a geosynchronous orbit at 35,900 km above Earth. The correct velocity at the lower circular orbit, calculated using the formula v = √(GM/(Re+h)), is determined to be 7730 m/s. Participants confirm that energy conservation principles dictate the need for increased kinetic energy to match the elliptical orbit's energy at the transition point.
PREREQUISITESAerospace engineers, physics students, satellite communication professionals, and anyone interested in orbital mechanics and satellite dynamics.
Can you show how you got that answer?nick727kcin said:a.)Consider a 1000 kg communication satellite that needs to be boosted from an orbit 300 km above the Earth to a geosynchronous orbit 35,900 km above the earth. Find the velocity v_1 on the lower circular orbit.
this came out to be: 7730m/s
nick727kcin said:thanks for responding guys, and i got that answer by using this formula:
v= (sq. root) GM/(Re+h)
part a is definitely right, though