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

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Works Cited [1] National Aeronautics and Space Administration, "Surveyor Program Results," NASA SP-184, Washington, DC, 1969. [2] Lanford, E. R., "Unique Abilities of Hopper Spacecraft to Enable National Objectives for Solar System Exploration," S.M. Thesis, Engineering Systems Division & Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, MA, 2011. [3] Cunio, P. M., et al., "Options in the Solar System for Planetary Surface Exploration via Hopping," 2011 IEEE Aerospace Conference, Big Sky, MT, 2011. [4] Cohanim, B. E., et al., "Small Lunar Exploration and Delivery System Concept," AIAA SPACE 2009 Conference & Exposition, Pasadena, CA, 2009. [5] X PRIZE Foundation, "About the Google Lunar X PRIZE," Google Lunar X PRIZE, 2011, URL: http:// www.googlelunarxprize.org/lunar/about-the-prize [cited 15 Feb. 2011]. [6] "Armadillo Aerospace Qualifies For Lunar Prize," AviationWeek.com, 16 Sep. 2009, URL: http:// www.aviationweek.com/aw/generic/story_channel.jsp?channel=space&id=news/ SCORPIUS091609.xml [cited 15 Feb. 2011]. [7] "Masten and Armadillo Claim Lunar Lander Prizes," NASA Office of the Chief Technologist, 2 Nov. 2009, URL: http://www.nasa.gov/offices/oct/early_stage_innovation/centennial_challenges/ cc_ll_feature_lvl2.html [cited 28 Mar. 2011]. [8] National Aeronautics and Space Administration, "GPN-2000-000215 - Lunar Landing Research Vehicle in Flight," GRIN: Great Images in NASA, 1964, URL: http://grin.hq.nasa.gov/ABSTRACTS/ GPN-2000-000215.html [cited 15 Feb. 2011]. [9] Matranga, G. J., Ottinger, C. W., Jarvis, C. R., and Gelzer, D. C., "Unconventional, Contrary, and Ugly: The Lunar Landing Research Vehicle," Monographs in Aerospace History #35, National Aeronautics and Space Administration, NASA SP-2004-4535, Washington, DC, 2005. 122
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Page 1:
Development of a Cold Gas Propulsio
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Abstract The TALARIS (Terrestrial A
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Table of Contents List of Figures .
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7 Ongoing and Future Work .........
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Figure 6-6. Identification of thrus
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Notation Acronyms and Abbreviations
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N newton Pa pascal psi pounds per s
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1 Introduction The TALARIS (Terrest
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the idea of hopping was born, and i
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However, as stated before, this doe
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Figure 2-3. Diagram of ACAT lander
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An alternate approach to resolving
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accurate conditions for testing GNC
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Ballistic hops tend to use less pro
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2.3.2 Comparison of Cold Gas and Mo
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Handling propellant There are sever
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and if the cold gas system was foun
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3 TALARIS CGSE Design Framework Aft
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Figure 3-1. Scaling of TALARIS terr
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(3) Providing attitude control Ther
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Figure 3-2 also shows the body coor
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4 Modeling and Flow Control Compone
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4.1.2 Rocket Propulsion Equations L
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variables in equation (4-8) deal wi
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equations. Equation (4-10) was then
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that of helium (0.227 MPa = 32.9 ps
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thruster solenoid valve, and chambe
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where
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discussed later in section 6.3.4, t
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The flight profile begins with maxi
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hop, any given valve or regulator o
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esponse time was an important perfo
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directly opens and closes the main
Page 73 and 74: If 1D isentropic flow is assumed, t
Page 75 and 76: 5 Single-Stream Component Testing A
Page 77 and 78: the solenoid valve, and a pressure
Page 79 and 80: As indicated in Figure 5-3, initial
Page 81 and 82: Figure 5-5. CGSE high side as const
Page 83 and 84: Figure 5-7 illustrates several aspe
Page 85 and 86: 6 Full Eight-Thruster Flight System
Page 87 and 88: Figure 6-2. TALARIS CGSE assembled
Page 89 and 90: stream tests revealed that changes
Page 91 and 92: Figure 6-5. Original CGSE control c
Page 93 and 94: other constraints. This was difficu
Page 95 and 96: variables (such as number of thrust
Page 97 and 98: One solution to this problem would
Page 99 and 100: One of the characterization tests w
Page 101 and 102: or more thrusters were firing toget
Page 103 and 104: Table 6-3. Valve timing metrics dur
Page 105 and 106: Figure 6-11. Redesigned CGSE contro
Page 107 and 108: The imaginary simplified thruster c
Page 109 and 110: traverse phase of a hop and involve
Page 111 and 112: Figure 7-3. GNC data from 3-DOF tes
Page 113 and 114: Tests on this vertical stand demons
Page 115 and 116: control the belay line can be put u
Page 117 and 118: accounting for changes in thrust le
Page 119 and 120: development under the supervision o
Page 121 and 122: documenting progress takes time whi
Page 123: were encountered, it was harder to
Page 127 and 128: [31] Canadian Centre for Occupation
Page 129 and 130:
[50] ISA - The Instrumentation, Sys
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