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...
View Full Document
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.
- Spring '08