Development of a Cold Gas Propulsion System for the ... - SSL - MIT
Development of a Cold Gas Propulsion System for the ... - SSL - MIT Development of a Cold Gas Propulsion System for the ... - SSL - MIT
equations. Equation (4-10) was then used to calculate the initial gas density. However, pressure, temperature, and density were all subject to change as gas flowed out of the CGSE. These changes were modeled with a set of differential equations based on a model originally written by Alessandro Golkar, a student who had worked on TALARIS in the fall 2008 and spring 2009 design classes. The Golkar model was not written for TALARIS, but rather for the pressurant gas tank of a liquid propellant rocket. However, the pressurant tank experienced temperature and pressure ranges very similar to those of the TALARIS CGSE, so the thermodynamics of both cases were comparable in many ways. A full derivation of this model is available in [42], but a condensed outline of it is also presented here. The Golkar model was based on the Redlich-Kwong equation of state, which is a more complex but often more accurate way of describing real gas behavior than using the compressibility factor
equations. Equation (4-10) was then used to calculate the initial gas density. However, pressure, temperature, and density were all subject to change as gas flowed out of the CGSE. These changes were modeled with a set of differential equations based on a model originally written by Alessandro Golkar, a student who had worked on TALARIS in the fall 2008 and spring 2009 design classes. The Golkar model was not written for TALARIS, but rather for the pressurant gas tank of a liquid propellant rocket. However, the pressurant tank experienced temperature and pressure ranges very similar to those of the TALARIS CGSE, so the thermodynamics of both cases were comparable in many ways. A full derivation of this model is available in [42], but a condensed outline of it is also presented here. The Golkar model was based on the Redlich-Kwong equation of state, which is a more complex but often more accurate way of describing real gas behavior than using the compressibility factor
- 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: variables in equation (4-8) deal wi
- Page 57 and 58: that of helium (0.227 MPa = 32.9 ps
- 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
equations. Equation (4-10) was <strong>the</strong>n used to calculate <strong>the</strong> initial gas density. However, pressure,<br />
temperature, and density were all subject to change as gas flowed out <strong>of</strong> <strong>the</strong> CGSE. These changes were<br />
modeled with a set <strong>of</strong> differential equations based on a model originally written by Alessandro Golkar, a<br />
student who had worked on TALARIS in <strong>the</strong> fall 2008 and spring 2009 design classes. The Golkar model<br />
was not written <strong>for</strong> TALARIS, but ra<strong>the</strong>r <strong>for</strong> <strong>the</strong> pressurant gas tank <strong>of</strong> a liquid propellant rocket.<br />
However, <strong>the</strong> pressurant tank experienced temperature and pressure ranges very similar to those <strong>of</strong> <strong>the</strong><br />
TALARIS CGSE, so <strong>the</strong> <strong>the</strong>rmodynamics <strong>of</strong> both cases were comparable in many ways. A full derivation <strong>of</strong><br />
this model is available in [42], but a condensed outline <strong>of</strong> it is also presented here.<br />
The Golkar model was based on <strong>the</strong> Redlich-Kwong equation <strong>of</strong> state, which is a more complex but <strong>of</strong>ten<br />
more accurate way <strong>of</strong> describing real gas behavior than using <strong>the</strong> compressibility factor
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