Given a satellite with a proposed orbital altitude of 325 km, determine: the required orbital velocity...

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Given a satellite with a proposed orbital altitude of 325 km, determine: the required orbital velocity to maintain the circular orbit • the required A v to change the vehicle's potential energy (raise it to the orbital altitude) Problem 2 Given a vehicle with an Isp = 360 s and a mass ratio of 12, determine the A v capability of the vehicle if the gravity loss is neglected. Recalculate the A v for the vehicle including the gravity loss. For this portion, assume that the vehicle trajectory is angled 60 degrees from horizontal and the flight duration is 140 seconds. Problem 3 For the vehicle described in the second part of problem 2, determine the maximum orbital altitude the vehicle could reach if it was launched from Cape Canaveral (latitude: 28.5 degrees N). If the launch site were moved further south to Miami (latitude: 26 degrees N), what would the maximum orbital altitude be? Problem 4 A vehicle with an Isp 335 s and a propellant mass fraction of 0.95 is being considered for a mission that has a AV requirement of 7290.0 m/s. The initial mass for the entire vehicle (inert + propellant + payload) is 6000.0 kg. Determine the payload that this vehicle can carry for this mission. Problem 5 Using the specifications for the previous problem, determine the payload mass if the vehicle is designed to have two stages. Each stage has the same specific impulse and propellant mass fractions as the original design. Assume the two stages also have the same weight and that the sum of stage 1 + stage 2 + payload initial mass of the vehicle. Given a satellite with a proposed orbital altitude of 325 km, determine: the required orbital velocity to maintain the circular orbit • the required A v to change the vehicle's potential energy (raise it to the orbital altitude) Problem 2 Given a vehicle with an Isp = 360 s and a mass ratio of 12, determine the A v capability of the vehicle if the gravity loss is neglected. Recalculate the A v for the vehicle including the gravity loss. For this portion, assume that the vehicle trajectory is angled 60 degrees from horizontal and the flight duration is 140 seconds. Problem 3 For the vehicle described in the second part of problem 2, determine the maximum orbital altitude the vehicle could reach if it was launched from Cape Canaveral (latitude: 28.5 degrees N). If the launch site were moved further south to Miami (latitude: 26 degrees N), what would the maximum orbital altitude be? Problem 4 A vehicle with an Isp 335 s and a propellant mass fraction of 0.95 is being considered for a mission that has a AV requirement of 7290.0 m/s. The initial mass for the entire vehicle (inert + propellant + payload) is 6000.0 kg. Determine the payload that this vehicle can carry for this mission. Problem 5 Using the specifications for the previous problem, determine the payload mass if the vehicle is designed to have two stages. Each stage has the same specific impulse and propellant mass fractions as the original design. Assume the two stages also have the same weight and that the sum of stage 1 + stage 2 + payload initial mass of the vehicle.

Answer rating: 100% (QA)

Problem 1 Orbital velocity for a circular orbit is given by v sqrtfracGMr where G gravitational constant M mass of the Earth and r orbital radius Given r 325 mathrmkm and M approx 5971024 mathrmkg we ... View the full answer