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Unformatted text preview: Space Systems Engineering I HW #2 1. A Mars probe is in a circular orbit around Earth with a radius of 25,000 km. The next step on the way to Mars is to thrust so the probe can enter an escape orbit. a. Determine the probe’s velocity in this circular orbit b. Determine the minimum velocity required to enter a parabolic trajectory at that radius c. Determine the difference in the specific kinetic energies of the two orbits d. Now compare this result to the specific mechanical energy of the original circular orbit. Which one has more specific kinetic energy? Are you surprised? Why or why not? 2. A spacecraft is in Earth orbit with a semi‐major axis of 7200 km, an eccentricity of 0.01, and true anomaly of 135 deg. a. What is the altitude of the spacecraft at this point? b. What is its velocity? c. How does this velocity compare with the velocity of a spacecraft at the same altitude in a circular orbit? 3. Initial data from a spacecraft indicates that the booster burned out at a perigee altitude of 160 km and speed of 7840 m/s. determine the speed and height at apogee, and the period. ...
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This note was uploaded on 04/26/2011 for the course MEM 373 taught by Professor Jinkang during the Spring '11 term at Drexel.
- Spring '11