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
Helium (He) Helium was considered because of its high specific impulse; as previously mentioned in section 2.3.2, it has an
3 TALARIS CGSE Design Framework After the major architecture decisions had been made for the TALARIS spacecraft emulator propulsion system, the next step was detailed design. The goal of this development process was not to develop a radically new propulsion system, which would have been extremely difficult given the limited budget and relatively short deadlines of the TALARIS project; cold gas propulsion technology is mature enough that there is little room for drastic improvement. Rather, the aim of the process described in this thesis was to make specific choices that most effectively satisfied the particular needs of the TALARIS project while working within the generally well-established framework of cold gas propulsion system design. 3.1 CGSE Requirements Definition The architecture definition process had placed some constraints on the design problem, such as the decision that the spacecraft emulator propulsion system would be a cold gas propulsion system, as well as a set of functional requirements. But in order to have definite targets to which to design the TALARIS CGSE, the process of requirements definition had to be carried further forward. The requirements already determined were used to derive quantifiable performance requirements. 3.1.1 Functional Requirements The decisions to (1) divide the TALARIS propulsion tasks into weight relief and spacecraft emulation, each performed by a separate system, and (2) design for the performance of a hover hop led to three main functional requirements for the TALARIS spacecraft emulator propulsion system. They were: (1) The CGSE shall lift the TALARIS hopper’s lunar weight, defined as 1/6 of its Earth weight. Though the long-term goals for the TALARIS project include simulation of operations on a range of target bodies, the short deadlines for the GLXP made simulation of lunar operations the top priority. Furthermore, a CGSE capable of lifting the TALARIS hopper under lunar gravity could also function for many other targets with even lower gravities, including Saturn’s moon Titan 2 or a variety of asteroids, if EDF output could be increased to provide a higher fraction of weight relief. If later operations on a body with higher gravity than the Moon, such as Mars, were desired, upgrades would be necessary unless the CGSE far exceeded its design goals. However, it was essential to set initial numerical design targets for the CGSE, and designing for lunar gravity was selected for the requirement. 2 Titan has a surface gravity of 0.138
- 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 if the cold gas system was foun
- 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 and 56: equations. Equation (4-10) was then
- 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
Helium (He)<br />
Helium was considered because <strong>of</strong> its high specific impulse; as previously mentioned in section 2.3.2, it<br />
has an
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