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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14. The new Isp of the MIPCC engine can then be calculated from the fuel flow rate<br />
(TBEAT Isp) and Equation 1.<br />
I<br />
sp<br />
T<br />
= (1)<br />
* *<br />
g(<br />
m fuel + m MIPCC )<br />
The result of this translation is a MIPCC thrust and Isp as a function of flight Mach and<br />
altitude. It should be noted that the percentage of LOX in the MIPCC flow is determined<br />
by oxidation limits of the F-100 turbofans. Therefore an upper limit of 23% of the total<br />
flow of incoming air was set. This percentage of LOX by weight was used since that<br />
approximated the amount of oxygen in standard air.<br />
Percentage of SLS Fuel Flow Rate<br />
0.2<br />
0.18<br />
0.16<br />
0.14<br />
0.12<br />
0.1<br />
0.08<br />
0.06<br />
0.04<br />
0.02<br />
Water Flow Rate<br />
y = 0.1006x 3 - 0.4262x 2 + 0.5975x - 0.264<br />
y = 0.0731x - 0.1185<br />
y = 0.07x - 0.1799<br />
y = 0.043x - 0.0989<br />
LOX Flow Rate<br />
0<br />
0 0.5 1 1.5 2 2.5 3 3.5 4 4.5<br />
Actual Flight Mach<br />
Figure 14: MIPCC Propellant Consumption Curve Fits as a Function of SLS Fuel Flow Rate [6].<br />
17
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