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

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[20] Fiorini, P., Hayati, S., Heverly, M., and Gensler, J., "A Hopping Robot for Planetary Exploration," Proceedings of 1999 IEEE Aerospace Conference, Vol. 2, Snowmass, CO, 1999, pp. 153-158. [21] Yoshimitsu, T., Kubota, T., Nakatani, I., Adachi, T., and Saito, H., "Micro-hopping robot for asteroid exploration," Acta Astronautica, Vol. 52, No. 2-6, Jan.-Mar. 2003, pp. 441-446. [22] Montminy, S., Dupuis, E., and Champliand, H., "Mechanical design of a hopper robot for planetary exploration using SMA as a unique source of power," Acta Astronautica, Vol. 62, No. 6-7, Mar.-Apr. 2008, pp. 438-452. [23] Chiaverini, M. J. and Kuo, K. K. (eds.), Fundamentals of Hybrid Rocket Combustion and Propulsion, American Institute of Aeronautics and Astronautics, Reston, VA, 2007. [24] Brown, C. D., Spacecraft Propulsion, American Institute of Aeronautics and Astronautics, Washington, DC, 1996. [25] "16.898 Critical Design Review: Earth-Based Prototype of a Lunar Hopper," Class Report, Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, MA, 2008 (unpublished; archived in TALARIS SVN file repository). [26] Golkar, A., et al., "TALARIS 1g Hopper Demonstrator Design Document," 16.83/89 Class Final Report, Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, MA, 2009 (unpublished; archived in TALARIS SVN file repository). [27] Humble, R. W., Henry, G. N., and Larson, W. J. (eds.), Space Propulsion Analysis and Design, Revised ed., McGraw-Hill, New York, 1995. [28] Sutton, G. P. and Biblarz, O., Rocket Propulsion Elements, 7th ed., John Wiley & Sons, New York, 2001. [29] Wernimont, E. J. and Mullens, P., "Capabilities of Hydrogen Peroxide Catalyst Beds," 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Huntsville, AL, 2000. [30] Solvay Chemicals, "Safety and Handling of Hydrogen Peroxide," Solvay Chemicals, Inc., 2006, URL: http://www.solvaychemicals.us/static/wma/pdf/6/6/0/4/HH-2323.pdf [cited 7 Mar. 2011]. 124
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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 .........
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Figure 6-6. Identification of thrus
Page 17 and 18:
Notation Acronyms and Abbreviations
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N newton Pa pascal psi pounds per s
Page 21 and 22:
1 Introduction The TALARIS (Terrest
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the idea of hopping was born, and i
Page 25 and 26:
However, as stated before, this doe
Page 27 and 28:
Figure 2-3. Diagram of ACAT lander
Page 29 and 30:
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
Page 55 and 56:
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
Page 61 and 62:
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
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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 and 124: were encountered, it was harder to
Page 125: [10] Bryant, K. M., Knight, C. J.,
Page 129 and 130:
[50] ISA - The Instrumentation, Sys
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