Unformatted text preview: Solve problem 6.27 page 384 of textbook (current edition). The problem is about Further study: Further reading on plane changes with simultaneous change in eccentricity would be useful and illustrate the one-impulse transfer cases further. Optional problem 1 (on escape speed): Given an elliptical orbit of eccentricity e and semi-major axis a , compute the minimum Δ V necessary to escape the central body (having grav. param. equal to μ ) when the one-impulse maneuver is performed at true anomaly θ , in the velocity vector direction. For which true anomaly value is this Δ V minimum? Optional problem 2 (on tangential vs. normal maneuver): Solve problem 6.28 page 384 of textbook (current edition). 1...
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- Winter '10
- Kepler's laws of planetary motion, plane change, Current Edition, ∆V Solve problem