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453 HW_3

453 HW_3 - Calculate the a angular momentum per unit mass(h...

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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
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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 earth’s 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...
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• Spring '08
• Mazzoleni,A
• Kepler's laws of planetary motion, Astrodynamics, Space Flight Department of Mechanical and Aerospace Engineering

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