This preview shows page 1. Sign up to view the full content.
Unformatted text preview: . Calculate the: a) angular momentum per unit mass (h) in km 2 /s b) true anomaly of the launch point c) eccentricity of the orbit d) period of the orbit 4. A satellite is launched parallel to the earths surface with a speed of 8 km/s at an altitude of 640 km. Calculate the: a) eccentricity of the orbit b) altitude of the spacecraft at apogee c) period of the orbit 5. The following position data for an earth orbiter are given by: Altitude = 1700 km at a true anomaly of 130 Altitude = 500 km at a true anomaly of 50 0 Calculate the: a) eccentricity of the orbit b) specific angular momentum c) perigee altitude d) semimajor axis...
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