453 HW_3 - . Calculate the: a) angular momentum per unit...

Info iconThis preview shows page 1. Sign up to view the full content.

View Full Document Right Arrow Icon
MAE 453: Introduction to Space Flight Spring 2010 Department of Mechanical and Aerospace Engineering North Carolina State University Homework 3: Circular and Elliptical Orbits DUE DATE: 2/17/10 1. A satellite is in a circular, orbit with an altitude of 350 km. Calculate the: a) speed of the satellite b) period of the orbit 2. The altitude of a satellite in an elliptical orbit around the earth is 1600 km at apogee and 600 km at perigee. Determine the: a) eccentricity of the orbit b) velocities at perigee and apogee c) period of the orbit 3. A satellite is launched into earth orbit at an altitude of 640 km with a speed of 9.2 km/s and a flight path angle of 10
Background image of page 1
This is the end of the preview. Sign up to access the rest of the document.

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.

Ask a homework question - tutors are online