Responsive Access Small Cargo Affordable Launch (RASCAL ...
Responsive Access Small Cargo Affordable Launch (RASCAL ...
Responsive Access Small Cargo Affordable Launch (RASCAL ...
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Coefficient of Drag<br />
0.6<br />
0.5<br />
0.4<br />
0.3<br />
0.2<br />
0.1<br />
0<br />
0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6<br />
Coefficient of Lift<br />
Propulsion Design:<br />
Figure 8: Drag Polars for 1st Stage <strong>RASCAL</strong> Design.<br />
Mach .8<br />
Mach 1.2<br />
Mach 2.0<br />
Mach 2.4<br />
Mach 3.0<br />
Mach 4.0<br />
The design of the propulsion system for <strong>RASCAL</strong> involves four parts. The first<br />
part is the design of the turbofan engines. This will be conducted using historical data [4]<br />
as well as an airbreathing turbojet design tool, TBEAT [5]. The second part of the<br />
propulsion design involves the performance of the MIPCC engines. This will be<br />
evaluated via an AIAA paper written by Preston Carter and Vladimir Balepin [6]. The<br />
MIPCC design will then be combined with the TBEAT analysis to evaluate the<br />
performance of the first stage engines. The third part of the propulsion design will be the<br />
second stage hybrid design. This part will be design using historical data [7]. The final<br />
part of the propulsion design will be the design of the third stage solid propellant engine.<br />
This will again be designed from historical data [7]. The propulsion elements will then<br />
be combined to be used in the trajectory analysis.<br />
11
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