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

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Development of a Cold Gas Propulsion System for the TALARIS Hopper Sarah L. Nothnagel, Professor Jeffrey A. Hoffman, Brett J. Streetman (Draper) June 2011 SSL # 14-11 This work is based on the unaltered text of the thesis by Sarah L. Nothnagel submitted to the Department of Aeronautics and Astronautics in partial fulfillment of the requirements for the degree of Master of Science in Aeronautics and Astronautics at the Massachusetts Institute of Technology. 1
Page 1: Development of a Cold Gas Propulsio
Page 7: Acknowledgements This work was perf
Page 10 and 11: 4.1.4 Flow Equations ..............
Page 13 and 14: List of Figures Figure 1-1. Ultra-p
Page 15: List of Tables Table 2-1. Lunar lan
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
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The first step in calculating
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(4-29) were used as printed to conv
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• Neither the Joule-Thomson effec
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Figure 4-4. Results of the example
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flight profile. This meant that the
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fast response times on the order of
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The 44-1363-2122-408 regulator had
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Figure 4-7. Drawing of CGSE nozzle
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this would be achieved with the reg
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was controlled manually; later, mod
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5.2.3 High Side of CGSE As mentione
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5.3 Results Originally, it was plan
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were run with the apparatus set up
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In order to increase the amount of
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Figure 6-3 shows all three of the m
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However, a solenoid is an inductor,
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6.3.1 Thruster Identification To tr
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6.3.3 Thrust Output Characterizatio
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Thruster-seconds are something of a
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Table 6-1. Maximum thrust levels fo
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Table 6-2. Thruster directions as u
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of the thruster valves never shut c
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Figure 6-10. Redesigned CGSE contro
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closer to the valve timing performa
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7 Ongoing and Future Work There are
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Figure 7-2. CGSE 3-DOF horizontal t
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7.1.2 Vertical Test Stand For initi
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Therefore, the vertical test stand
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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
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[40] Hill, P. G. and Peterson, C. R
Page 130:
[61] Morrow, J., Nothnagel, S. L.,
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