We calculate the transfer time from the inner to the outer elliptic planetary orbits of a space vehicle for the four feasible configurations and for the circular case. We find that the least time of transfer tT corresponds to the second configuration.
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In this part we investigate all the four feasible configurations for the generalized Hohmann type transfer. We assign the minimized characteristic velocity (Δv1+Δv2)Min by the application of ordinary infinitesimal calculus optimum conditions. By some algebraic manipulations, we determine the independent variables (x)Min. In addition, we considered the analysis relevant to the two parameters x, y relevant to the two impulses at points A, B. It is demonstrated that the elliptic Hohmann type transfer is the most economic one by this new representation.
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We optimize the Hohmann type bi-impulsive transfer between inclined elliptic orbits having a common center of attraction, for the four feasible configurations. Our criterion for optimization is the characteristic velocity ΔvT = Δv1 + Δv2 which is a measure of fuel consumption. We assigned the optimum value of our variable x (ratio between velocity after initial impulse and velocity before initial impulse) by a numerical solution of an algebraic eight degree equation. We have a single plane change angle α. We present terse new formulae constituting a new alternative approach for tackling the problem. The derivations of formulae of our treatment are simple, straightforward and exceptionally clear. This is advantageous. By this semi-analytic analysis we avoid many complexities and ambiguity that appear in previous work.
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