Responsive Access Small Cargo Affordable Launch (RASCAL ...

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Coefficent of Drag Coefficient of Lift 0.08 0.07 0.06 0.05 0.04 0.03 0.02 0.01 0 0 0.5 1 1.5 2 2.5 Mach 3 3.5 4 4.5 5 Figure 6: Drag Variation as a Function of Mach Number 1.5 1 0.5 0 -15 -10 -5 0 5 10 15 20 25 -0.5 -1 Angle of Attack (deg) Figure 7: Lift Curve Slopes for 1st Stage of the RASCAL Design. Mach .8 Mach 1.2 Mach 2.0 Mach 2.4 Mach 3.0 Mach 4.0 10
Coefficient of Drag 0.6 0.5 0.4 0.3 0.2 0.1 0 0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 Coefficient of Lift Propulsion Design: Figure 8: Drag Polars for 1st Stage RASCAL Design. Mach .8 Mach 1.2 Mach 2.0 Mach 2.4 Mach 3.0 Mach 4.0 The design of the propulsion system for RASCAL involves four parts. The first part is the design of the turbofan engines. This will be conducted using historical data [4] as well as an airbreathing turbojet design tool, TBEAT [5]. The second part of the propulsion design involves the performance of the MIPCC engines. This will be evaluated via an AIAA paper written by Preston Carter and Vladimir Balepin [6]. The MIPCC design will then be combined with the TBEAT analysis to evaluate the performance of the first stage engines. The third part of the propulsion design will be the second stage hybrid design. This part will be design using historical data [7]. The final part of the propulsion design will be the design of the third stage solid propellant engine. This will again be designed from historical data [7]. The propulsion elements will then be combined to be used in the trajectory analysis. 11
Page 1 and 2: Responsive Access Small Cargo Affor
Page 3 and 4: List of Figures: Figure 1: Launch C
Page 5 and 6: Abstract: RASCAL is a Defense Depar
Page 7 and 8: Introduction: Due to the uncertaint
Page 9 and 10: This stage will then propel the veh
Page 11 and 12: stages which continue on to orbit.
Page 13 and 14: driving constraint) will then be fl
Page 15: Once the geometry is defined it mus
Page 19 and 20: These characteristics were then ana
Page 21 and 22: To analyze the effect of MIPCC an A
Page 23 and 24: 14. The new Isp of the MIPCC engine
Page 25 and 26: combination selected the overall we
Page 27 and 28: Table 5: POST Trajectory Constraint
Page 29 and 30: Thrust (lbs) 120000 100000 80000 60
Page 31 and 32: Gross Gross Weight Dry Dry Weight W
Page 33 and 34: Temperature (F) 1400 1300 1200 1100
Page 35 and 36: Operations: Number 1st Stages 5 Num
Page 37 and 38: Cost Estimation: The cost estimatio
Page 39 and 40: As this figure depicts the DDT&E fo
Page 41 and 42: profile of the cost charts is due t
Page 43 and 44: Each of these alternatives will be
Page 45 and 46: 1+2+3 1+3 4th Stage MMC 1st Lox Hyb
Page 47 and 48: The design alternatives were costed
Page 49 and 50: GT RASCAL: From this alternative an
Page 51 and 52: As this figure shows the GT RASCAL
Page 53 and 54: used in the GT RASCAL design is in
Page 55 and 56: Figure 39: GT RASCAL Mission Profil
Page 57 and 58: When the final cost numbers of the
Page 59 and 60: References: 1. Cyr, Kelley, “US L

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