Development of a Cold Gas Propulsion System for the ... - SSL - MIT

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Notation Acronyms and Abbreviations ACAT Advanced Concept Architecture Test ACS Attitude Control System ALHAT Autonomous Landing and Hazard Avoidance Technology CGSE Cold Gas Spacecraft Emulator CGTA Cold Gas Test Article CNC Computer Numerical Control COTS Commercial Off-The-Shelf DAQ Data Acquisition (device or system) DOF Degree(s) Of Freedom EDF Electric Ducted Fan EDL Entry, Descent, and Landing GLXP Google Lunar X PRIZE GNC Guidance, Navigation, and Control HTV Hover Test Vehicle ID Inner Diameter ILN International Lunar Network IMU Inertial Measurement Unit ISRU In-Situ Resource Utilization KKV Kinetic Kill Vehicle LAN Local Area Network LEAP Lightweight Exo-Atmospheric Projectile LEAPFROG Lunar Entry and Approach Platform For Research On Ground LED Light-Emitting Diode LLRV Lunar Landing Research Vehicle LLTV Lunar Landing Training Vehicle MIT Massachusetts Institute of Technology MMH Monomethylhydrazine MOSFET Metal-Oxide-Semiconductor Field-Effect Transistor NASA National Aeronautics and Space Administration 15
Page 1: Development of a Cold Gas Propulsio
Page 5: Abstract The TALARIS (Terrestrial A
Page 9 and 10: Table of Contents List of Figures .
Page 11: 7 Ongoing and Future Work .........
Page 14 and 15: Figure 6-6. Identification of thrus
Page 18 and 19: NI National Instruments NIST Nation
Page 20 and 21: N newton Pa pascal psi pounds per s
Page 22 and 23: designed to use the same propulsion
Page 24 and 25: 2 Propulsion System Architecture Al
Page 26 and 27: propulsion tasks will be grouped an
Page 28 and 29: Figure 2-4. NASA robotic lunar land
Page 30 and 31: System Table 2-1. Lunar lander test
Page 32 and 33: 2.3 Confirming the Decision to Use
Page 34 and 35: from the higher specific impulse wh
Page 36 and 37: ut also on a per-volume basis. This
Page 38 and 39: Hydrogen peroxide at the concentrat
Page 40 and 41: Helium (He) Helium was considered b
Page 42 and 43: (2) The CGSE shall propel the hoppe
Page 44 and 45: (1) Lifting the hopper’s lunar we
Page 46 and 47: simplicity of control, it was decid
Page 48 and 49: Figure 3-3. CGSE system schematic [
Page 50 and 51: 4.1.1 Flight Profiles Hopper flight
Page 52 and 53: 4.1.2 Rocket Propulsion Equations L
Page 54 and 55: equations. Equation (4-10) was then
Page 56 and 57: The other new variables in equation
Page 58 and 59: The Joule-Thomson coefficient
Page 60 and 61: The first step in calculating
Page 62 and 63: (4-29) were used as printed to conv
Page 64 and 65: • Neither the Joule-Thomson effec
Page 66 and 67:
Figure 4-4. Results of the example
Page 68 and 69:
flight profile. This meant that the
Page 70 and 71:
fast response times on the order of
Page 72 and 73:
The 44-1363-2122-408 regulator had
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Figure 4-7. Drawing of CGSE nozzle
Page 76 and 77:
this would be achieved with the reg
Page 78 and 79:
was controlled manually; later, mod
Page 80 and 81:
5.2.3 High Side of CGSE As mentione
Page 82 and 83:
5.3 Results Originally, it was plan
Page 84 and 85:
were run with the apparatus set up
Page 86 and 87:
In order to increase the amount of
Page 88 and 89:
Figure 6-3 shows all three of the m
Page 90 and 91:
However, a solenoid is an inductor,
Page 92 and 93:
6.3.1 Thruster Identification To tr
Page 94 and 95:
6.3.3 Thrust Output Characterizatio
Page 96 and 97:
Thruster-seconds are something of a
Page 98 and 99:
Table 6-1. Maximum thrust levels fo
Page 100 and 101:
Table 6-2. Thruster directions as u
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of the thruster valves never shut c
Page 104 and 105:
Figure 6-10. Redesigned CGSE contro
Page 106 and 107:
closer to the valve timing performa
Page 108 and 109:
7 Ongoing and Future Work There are
Page 110 and 111:
Figure 7-2. CGSE 3-DOF horizontal t
Page 112 and 113:
7.1.2 Vertical Test Stand For initi
Page 114 and 115:
Therefore, the vertical test stand
Page 116 and 117:
and adjustments made to account for
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the gains in propellant carrying ca
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8 Conclusion The TALARIS CGSE is an
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would not have been sufficient on i
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Works Cited [1] National Aeronautic
Page 126 and 127:
[20] Fiorini, P., Hayati, S., Hever
Page 128 and 129:
[40] Hill, P. G. and Peterson, C. R
Page 130:
[61] Morrow, J., Nothnagel, S. L.,
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