An analytical investigation of single-stage vehicles with multiple propulsion phases has been conducted with the phasing optimized to minimize a general cost function. Some results are presented for linearized sizing relationships which indicate that single-stage-to-orbit, dual-fuel rocket vehicles can have lower inert weight than similar single-fuel rocket vehicles and that the advantage of dual-fuel vehicles can be increased if a dual-fuel engine is developed. The results also indicate that the optimum split can vary considerably with the choice of cost function to be minimized.
Optimal dual-fuel propulsion for minimum inert weight or minimum fuel cost
Propulsion Conference ; 1973 ; Las Vegas, NV, US
1973-11-01
Aufsatz (Konferenz)
Keine Angabe
Englisch