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

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The other new variables in equation (4-21) are the partial derivatives of specific enthalpy with respect to pressure and temperature. The Golkar model was written for a pressurant tank using helium gas, for which these derivatives were constant over the range of pressures and temperatures experienced [42]. However, these partial derivatives were not constant for nitrogen over the range of conditions expected in the TALARIS CGSE tanks. This difference is illustrated in Figure 4-1. Figure 4-1. Enthalpy relations for helium and nitrogen. (a) Helium specific enthalpy vs. pressure [42]. (b) Nitrogen specific enthalpy vs. pressure. (c) Helium specific enthalpy vs. temperature [42]. (d) Nitrogen specific enthalpy vs. temperature. In Figure 4-1(a), the plots of specific enthalpy vs. pressure for helium are all linear with the same slope regardless of temperature, which shows that
that of helium (0.227 MPa = 32.9 psi, 5.19 K) [43], and the thermodynamic state of the nitrogen in the TALARIS CGSE was found to approach the critical point at the end of a hop. This means that nitrogen in the TALARIS CGSE behaves less like an ideal gas and exhibits real gas behavior more strongly, so
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 17 and 18: Notation Acronyms and Abbreviations
Page 19 and 20: N newton Pa pascal psi pounds per s
Page 21 and 22: 1 Introduction The TALARIS (Terrest
Page 23 and 24: 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
Page 31 and 32: accurate conditions for testing GNC
Page 33 and 34: Ballistic hops tend to use less pro
Page 35 and 36: 2.3.2 Comparison of Cold Gas and Mo
Page 37 and 38: Handling propellant There are sever
Page 39 and 40: and if the cold gas system was foun
Page 41 and 42: 3 TALARIS CGSE Design Framework Aft
Page 43 and 44: Figure 3-1. Scaling of TALARIS terr
Page 45 and 46: (3) Providing attitude control Ther
Page 47 and 48: Figure 3-2 also shows the body coor
Page 49 and 50: 4 Modeling and Flow Control Compone
Page 51 and 52: 4.1.2 Rocket Propulsion Equations L
Page 53 and 54: variables in equation (4-8) deal wi
Page 55: equations. Equation (4-10) was then
Page 59 and 60: thruster solenoid valve, and chambe
Page 61 and 62: where
Page 63 and 64: discussed later in section 6.3.4, t
Page 65 and 66: The flight profile begins with maxi
Page 67 and 68: hop, any given valve or regulator o
Page 69 and 70: esponse time was an important perfo
Page 71 and 72: 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 and 124:
were encountered, it was harder to
Page 125 and 126:
[10] Bryant, K. M., Knight, C. J.,
Page 127 and 128:
[31] Canadian Centre for Occupation
Page 129 and 130:
[50] ISA - The Instrumentation, Sys
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Development of a Cold Gas Propulsion System for the ... - SSL - MIT

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