A 30,000 kg spacecraft is approaching the moon on a hyperbolic trajectory at an altitude of 1,000 km and a speed of 10 km/s. The spacecraft must be lowered into a circular parking orbit with altitude of 100 km. After three orbits at 100 km for system checks, the lander is deployed and conducts a maneuver to land on the surface of the moon at a position 180° from the impulse point. Determine the total required Δ? to conduct the transfer into the circular orbit, in km/s Determine the required propellant mass for that maneuver, in kg Determine the required Δ? to transfer to the landing trajectory Determine the total time required from the start of the initial transfer orbit until landing, in h
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A 30,000 kg spacecraft is approaching the moon on a hyperbolic trajectory at an altitude of 1,000 km and a speed of 10 km/s. The spacecraft must be lowered into a circular parking orbit with altitude of 100 km. After three orbits at 100 km for system checks, the lander is deployed and conducts a maneuver to land on the surface of the moon at a position 180° from the impulse point.
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Determine the total required Δ? to conduct the transfer into the circular orbit, in km/s
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Determine the required propellant mass for that maneuver, in kg
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Determine the required Δ? to transfer to the landing trajectory
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Determine the total time required from the start of the initial transfer orbit until
landing, in h
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