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

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Figure 6-6. Identification of thrusters by number and letter. Body coordinate axes also shown [38]. ..... 90 Figure 6-7. Static test stand for CGSE flight system characterization. ........................................................ 91 Figure 6-8. CGSE thrust decrease with gas usage. ...................................................................................... 93 Figure 6-9. Valve timing metrics [59]. ....................................................................................................... 100 Figure 6-10. Redesigned CGSE control circuit for a single thruster solenoid valve. ................................. 102 Figure 6-11. Redesigned CGSE control circuit for thruster solenoid valve with hardline dump. ............. 103 Figure 6-12. Simplified diagram of a commanded 40 ms thruster pulse and its actual results. .............. 104 Figure 6-13. Simplified diagram of adjusted command to produce impulse of a 40 ms square pulse. ... 105 Figure 7-1. CGSE 1-DOF horizontal traverse testing on wheels. ............................................................... 107 Figure 7-2. CGSE 3-DOF horizontal traverse and roll testing on air bearing. ............................................ 108 Figure 7-3. GNC data from 3-DOF test of TALARIS hopper, with 45° roll and horizontal traverse. .......... 109 Figure 7-4. TALARIS hopper in vertical test stand, allowing both altitude and attitude control testing. . 110 Figure 7-5. Yaw disturbance rejection demonstrating 1-DOF attitude control of TALARIS hopper. ........ 111 Figure 7-6. Full 6-DOF flight testing of TALARIS hopper. .......................................................................... 112 12
List of Tables Table 2-1. Lunar lander testbed vehicles using divided propulsion architecture. ...................................... 28 Table 4-1. Maximum modeled
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 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 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
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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
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5 Single-Stream Component Testing A
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the solenoid valve, and a pressure
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As indicated in Figure 5-3, initial
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Figure 5-5. CGSE high side as const
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Figure 5-7 illustrates several aspe
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6 Full Eight-Thruster Flight System
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Figure 6-2. TALARIS CGSE assembled
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stream tests revealed that changes
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Figure 6-5. Original CGSE control c
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other constraints. This was difficu
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variables (such as number of thrust
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One solution to this problem would
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One of the characterization tests w
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or more thrusters were firing toget
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Table 6-3. Valve timing metrics dur
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Figure 6-11. Redesigned CGSE contro
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The imaginary simplified thruster c
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traverse phase of a hop and involve
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Figure 7-3. GNC data from 3-DOF tes
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Tests on this vertical stand demons
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control the belay line can be put u
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accounting for changes in thrust le
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development under the supervision o
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documenting progress takes time whi
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were encountered, it was harder to
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[10] Bryant, K. M., Knight, C. J.,
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[31] Canadian Centre for Occupation
Page 129 and 130:
[50] ISA - The Instrumentation, Sys
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