Hohmann Transfer Orbit · IPhO 2014 #2

Physics · mechanics

Problem

A spacecraft orbits Earth in a circular orbit of radius r1=7000  kmr_1 = 7000\;\text{km}. It needs to transfer to a circular orbit of radius r2=42000  kmr_2 = 42000\;\text{km} (geostationary orbit). Using a Hohmann transfer (two engine burns), find (a) the semi-major axis of the transfer ellipse, (b) the total Δv\Delta v required. Use GME=3.986×1014  m3/s2GM_E = 3.986 \times 10^{14}\;\text{m}^3/\text{s}^2.

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