Problem considered involves transferring between pair of coplanar orbits defined by their semilatera recta, eccentricities, and arguments of perigee; determination of that trajectory which results in orbital transfer with minimum fuel expenditure is required; rocket and its environment are defined; solution of problem involves minimization of functional that is function of only boundary values of state variables, i.e., position, velocity, mass, and time; IBM 7094 computer program incorporating quasi-linearization process was used to generate optimal transfers between numerous pairs of arbitrary coplanar orbits.
Quasilinearization determination of optimum finite-thrust orbital transfers
AIAA J
AIAA Journal ; 5 , n 4
1967
9 pages
Article (Journal)
English
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