453 HW_4 - T the time required to fly from P to B To do...

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MAE 453: Introduction to Space Flight Spring 2010 Department of Mechanical and Aerospace Engineering North Carolina State University Homework 4: Hyperbolic Trajectories and Orbital Position as a Function of Time DUE DATE: 3/1/10 1. A space vehicle has a velocity of 10 km/s in the direction shown when it is 10,000 km from the center of the earth. Calculate the: a) radial and azimuthal velocity components b) angular momentum per unit mass c) eccentricity of the orbit d) true anomaly at this location 2. A spacecraft in a 500 km altitude circular orbit is given a delta-v equal to one-half its orbital speed. Use the energy equation to calculate the hyperbolic excess velocity. 3. If the eccentricity of the elliptical orbit is 0.5, calculate, in terms of the period
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Unformatted text preview: T , the time required to fly from P to B . To do this, find the: a) true anomaly at location B b) value of the eccentric anomaly at location B c) value of the mean anomaly at location B d) time after periapsis 4. An earth-orbiting satellite has a period of 15.743 hours and a perigee radius of 12,756 km. At time t = 10 hours after perigee passage, determine the: a) semimajor axis of the orbit b) apogee radius and the eccentricity of the orbit c) mean anomaly and then the eccentric anomaly at this time d) true anomaly and radius at this location e) speed of the spacecraft at this location f) specific angular moment and the radial component of velocity...
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This note was uploaded on 05/19/2010 for the course MAE 453 taught by Professor Mazzoleni,a during the Spring '08 term at N.C. State.

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