Spacecraft and Aircraft Dynamics - Lecture 5 - Illinois Institute of ...
Spacecraft and Aircraft Dynamics - Lecture 5 - Illinois Institute of ...
Spacecraft and Aircraft Dynamics - Lecture 5 - Illinois Institute of ...
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Hyperbolic Kepler’s EquationTo solve for position, we redefine mean motion, n, <strong>and</strong> mean anomaly, M, to getDefinition 1 (Hyperbolic Kepler’s Equation).M =√ µ−a3t = esinh(H)−HNewton Iteration for Hyperbolic Anomaly:with H 1 = M.H k+1 = H k + M −esinh(H k)+H kecosh(H k )−1M. Peet <strong>Lecture</strong> 5: <strong>Spacecraft</strong> <strong>Dynamics</strong> 13 / 26
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