A satellite of 1000 kg is travelling (CCW) with an angular velocity of Ӫ(t) = 0.0016t rod/s around the Earth while it is also moving away from the last atmospheric air surface(ignoring the vertical takeoff distance 100 km) as a function of ŕ(t) = 0.0028t m/s.
1. What is the acceleration of the satellite?
2. If the desired orbit is 6400 km away from the Earth’s surface how long the satellite will have to fly to reach there?
3. How many circular trips will be required to reach the orbit?
4. What will be its speed at that point?
5. How much energy will be required to reach the last atmospher

Question

A satellite of 1000 kg is travelling (CCW) with an angular velocity of Ӫ(t) = 0.0016t rod/s around the Earth while it is also moving away from the last atmospheric air surface(ignoring the vertical takeoff distance 100 km) as a function of ŕ(t) = 0.0028t m/s.
1. What is the acceleration of the satellite?
2. If the desired orbit is 6400 km away from the Earth’s surface how long the satellite will have to fly to reach there?
3. How many circular trips will be required to reach the orbit?
4. What will be its speed at that point?
5. How much energy will be required to reach the last atmospher

anonymous · Answer

5. How much energy will be required to reach the last atmospheric air surface if the mission is carried out by a rocket of 300 tons?