ORBITAL TRANSFER WITH MINIMUM FUEL
NAVAL POSTGRADUATE SCHOOL MONTEREY CA
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An extension is made of the problem of scheduling the direction p of constant momentum thrust of a rocket, which loses mass at a constant rate, so that it transfers to a known earth satellite orbit in minimum time T after launching. A numerical solution was obtained, using rectangular coordinates, for the case of fixed launching conditions. The method is extended to solve the problem of orbital transfer of such a rocket with minimum fuel consumption.
- Unmanned Spacecraft