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Responsive Access Small Cargo Affordable Launch (RASCAL ...

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Each of these alternatives will be closed in the performance aspects of the DSM (all<br />

except cost, operations, and economics). Unless noted all alternatives represent one<br />

change off of the baseline at a time.<br />

Alternative 1:<br />

The first alternative will be to change the second stage oxidizer from hydrogen<br />

peroxide to liquid oxygen. The advantage of making this change is that the Isp of the<br />

second stage will increase to 340 seconds vs. the 310 seconds for the hydrogen peroxide.<br />

A disadvantage to this change is that the second stage will become larger. This is due to<br />

the fact that the HTPB/LOX combination operates at a lower O/F ratio (1.9 vs. 6.5). This<br />

smaller mixture ratio results in a larger rocket. This alternative configuration was closed<br />

in the internal iteration loop of the DSM and this alternative resulted in the overall<br />

payload capacity of the baseline <strong>RASCAL</strong> design increasing from 52 lbs to 75 lbs.<br />

Alternative 2:<br />

The second alternative involves changing the baseline first stage structural<br />

material from standard aluminum to a metal matrix composite. This MMC will not only<br />

make the design much lighter, it will also eliminate the need for a thermal protection<br />

system (up to 1500 F). This is due to the fact that the reuse temperature of the MMC is<br />

higher than the temperatures encountered by the first stage. The disadvantage to the<br />

MMC is that it is an immature technology, and must be developed and tested far more<br />

that the typical aluminum structure. This will cause the DDT&E of the design to increase<br />

dramatically over the baseline. This alternative configuration was closed in the internal<br />

iteration loop of the DSM and this alternative resulted in the overall payload capacity of<br />

the baseline <strong>RASCAL</strong> design increasing from 52 lbs to 110 lbs.<br />

Alternative 3:<br />

The third alternative involves changing the trajectory of the upper stages so that<br />

the second and third stages put the payload into a transfer orbit (80 nmi by 270 nmi<br />

orbit). A fourth stage solid motor is then added to the upper stage to circularize the<br />

37

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