Comparison Of Continuous Operation Cycles

To compare the continuous operation cycles Figure 3.4 is repeated as Figure 4.23. In Figure 4.23 weight ratio to LEO, that is the takeoff gross weight divided by the on-orbit weight, is represented for different engine cycles as a function of the net oxidizer to fuel ratio. These divide into two distinct groups. The rocket-derived propulsion represented by cycles: rocket, air augmented rocket and ram rocket. For the rocket-derived cycles the oxidizer-to-fuel ratio is essentially constant at a value of 6. As a ram rocket, the weight ratio of LEO decreases from 8.1 to 6.5. There is only a minimal payoff for the air augmented rocket as without burning the oxygen in the air, there is insufficient thrust boost to make a significant difference in weight h eg h eg

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