Cold-gas Propulsion for Small Satellite Attitude Control, Station - - PowerPoint PPT Presentation
Cold-gas Propulsion for Small Satellite Attitude Control, Station Keeping, and Deorbit. John Furumo*, Nathan Walsh, Evan Greer, Daniel Wukelic, Dr. A. Zachary Trimble, Dr. Trevor Sorensen. 1 Agenda Small Satellite Background Information
Cold-gas Propulsion for Small Satellite Attitude Control, Station Keeping, and Deorbit. John Furumo*, Nathan Walsh, Evan Greer, Daniel Wukelic, Dr.
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▶ Small Satellite Background Information ▶ Project Objectives ▶ Cold-Gas System Analysis ▶ Satellite Dynamics ▶ Prototype ▶ Test Results ▶ Conclusion ▶ Future Work and Improvements
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▶ Small Satellite maneuvers
▶ 1 year operational lifetime ▶ < 25% total payload mass/volume ▶ Space-rated system ▶ HSFL’s HiakaSat
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Supplemental Slide 48
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Category Cold Gas Electric Mono Biprop Size 1.250 2.321 2.488 1.850 Performance 0.003 1.000 0.240 1.300 Feasibility 5.000 2.525 2.150 0.615 Total 6.253 5.846 4.878 3.765
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▶ Simplest satellite propulsion system ▶ Cheap to build (~$5k budget) ▶ Components and propellant gases readily available ▶ UH facilities are sufficient for fabrication and testing ▶ Propellants are safe to handle and test
▶ Propellant Type
▶ Propellant Storage
⚫ Limited by satellite volume
⚫ Limited by pressure vessel
⚫ Limited by spacecraft thermal control
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Cold Gas Propellant N2 CO2 NH3 N2O H2 He Xe Specific Impulse, theoretical, metric (s) 76.8 67.3 108.3 66.2 285.5 174.7 30.0 Propellant Mass (kg) 3.83 6.01 2.32 6.01 0.27 0.55 17.95 Delta-V (m/s) 57.66 79.42 49.37 78.10 15.32 18.74 105.56
Assumptions: Storage Volume = 10 Liters Storage Pressure = 4500 psi (~31MPa) Storage Temp = 0°C
Supplemental Slide 47
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▶ Trade-off between
thrust and time
▶ Set amount of ΔV
required for orbit maintenance, deorbit
▶ Variable amount of ΔV
for attitude control
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De Laval Nozzle Diagram [1]
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▶
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Thruster Force/Pressure Relation
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Thrust (N) 0.1 1 10 100 Propellant Mass Flow Rate (kg/s) 0.00015 0.00152 0.01515 0.15152 Thruster Pressure (psi) 3.77 37.67 376.73 3767.25 Total Burn Time (s) 11 hours 66.2 min 6.62 min 40 s
Assumptions: Nozzle Throat Diameter = 1/16” Nozzle Exit Velocity = 660 m/s Propellant = CO2 Propellant mass = 6.01 kg
Supplemental Slide 47
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tm θm Iv n F L 7.05 s 180° 2.08 kg*m2 2 1 N 0.2627 m (Enough ΔV for 563 maneuvers)
▶ Non-ACS thrust vs. time
▶ More accurate way to characterize ΔV requirement for
attitude control
▶ Consult faculty for supersonic flow considerations,
nozzle geometry
▶ Control scheme design ▶ Estimation of end-of-life performance
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Computational Fluid Dynamics Simulations
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model through a converging-diverging geometry
condition of 10 m/s
increases to approximately 100 m/s
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▶ Using tabulated data
⚫ A1/A* ≈15, A1/A2 =0.1112, and A2/A*=1.668 ⚫ Using A2/A*, M2≈0.375 ⚫ V2 ≈ 0.375(269.37) = 101 m/s
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▶ Change in
geometry
▶ Decrease in
throat area
▶ Input condition of
2 m/s
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▶ We wish to simulate the flow under an operating
pressure of 37.7 psi
▶ The turbulent flow physical model within Comsol only
supports flow, Ma < 0.3
▶ We will use the high mach number flow model
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▶ Errors have been encountered that suggest the
problem is not fully defined
▶ Attempts to look at the set up of other example
models have failed to solve the problem
▶ We will consult Comsol support to resolve issues of
this model
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Rotation Type Thrusters Used X-Negative 1,5 X-Positive 3,7 Y-Negative 1,3 2,4 1,2,3,4 Y-Positive 5,7 6,8 5,6,7,8 Z-Negative 4,6 Z-Positive 2,8
Maneuvers:
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Prototype Will Be Built For Testing Flight Model Concept Only
▶ For 1-axis control testing ▶ 4 Thrusters to control spin in both directions ▶ Nozzle designed for ambient atmospheric application ▶ All parts are COTS other than nozzles ▶ Manually controlled components
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▶ Full Features ▶ Space worthy components ▶ Differences from prototype
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Model: PX300 Series [2] Range: 0 to 1000 Psi Accuracy: 0.25% Full Scale Excitation: 10 Vdc (5 to 15 Vdc Limits) Output: 3mV/V ratiometric 30mV ±1mV @ 10V Model: G17M0142F21000# [3] Range: 0 to 1000 Psi Accuracy: +/-0.5% Full Scale Output: 4 to 20 mA at 12 to 30VDC Power Required: 9 to 36VDC
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Ninja Carbon Fiber Tank [4] Size: 90 cubic inch Max Tank Pressure: 4500 psi Output Pressure: 800~850 psi Cylinder Weight: 3.3 pounds
http://www.paintballrevolution.com/pureenergy70ci4500psiultrapaintballtank-1-1-1-1-1-1-1-1.aspx http://www.ultimatepaintball.com/p-9515-ninja-carbon-fiber-n2-paintball-tank-90ci4500psi-grey.aspx?CAWELAID=1513094504&catargetid=1391382590&ca gpspn=pla&gclid=CNaozPKA_7MCFSFyQgodNEsA1Q (pic used in CDR)
Luxfer D Air Tank [5] Service Pressure 2015 psi Oxygen Capacity 14.7 cu ft Outside Diameter 4.4” Empty Weight 5.0 lbs Internal Volume 172 cu in Thread Size 0.750-16 UNF-2B
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Mega Regulator Dual Stage [6] · Dual Stage Regulator · Adjustable from 0-950 PSI · Tank Thread 5/8(.625)inch -18 UNF PR-57 Series Pressure Regulator [7] · 316L stainless steel construction · 20µ filter · Inlet pressure maximum 10,000 psi · Outlet pressure ranges are 0–10,00 psi · Operating temperatures: −40° F to +150° F
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Solenoid Actuated Thruster Valve (Single Seat) [9] Operating Pressure: 500 psig Response time: 15 ms maximum Power Consumption: 27 Watts Engine Thrust Rating: 40 N Weight: 0.23 kg Type: Stainless Steel Model No. SVS03 [10] Operating Pressure: 1750 psi Response Time: < 10 ms Operating Voltage: 28 ± 4 VDC Engine Thrust: 5 N Weight: 0.110 Kg Type: Stainless Steel
▶ Completely custom ▶ Throat diameter: 1/16” ▶ Exit diameter: 1” ▶ Area expansion ratio: ~257 ▶ Converging-diverging profile TBD
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[1] Brown, Charles D. “Fig. 2.1 Rocket Nozzle”, Spacecraft Propulsion, 1st Edition. AIAA Press, 1996. [2]http://www.omega.com/pptst/px300.html [3]http://www.drillspot.com/products/1330697/Pressure_Transducer_G17M0142F21000_Pressure_Transducer ?s=1&catargetid=1623454804&gclid=CJv5ydui_bMCFQhyQgod73oA1A [4] http://www.ultimatepaintball.com/p-9515-ninja-carbon-fiber-n2-paintball-tank-90ci4500psi-grey.aspx?CA WELAID=1513094504&catargetid=1391382590&cagpspn=pla&gclid=CNaozPKA_7MCFSFyQgodNEsA1Q [5]http://lakecourt.com/pc_product_detail.asp?key=4A2113A89C1541758F7D665427ACFE6E [6] http://www.sakworldpaintball.com/meredustadta.html [7] http://www.circle-seal.com/products/pressure_regulators/pr57/index.html [8] University of Toronto, “Physics: The Properties of Permafrost” Mentorship Program. Available online. Link: http://www.physics.utoronto.ca/~exploration/UofT-mentorship/Physics_CO2.html [9] http://www.moog.com/products/propulsion-controls/spacecraft/components/thruster-valves/solenoid-act uated-thruster-valve-single-seat-/ [10] http://www.ampacispcheltenham.eu/pages/prsolenoid8.htm
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Supplemental Slide - Old Delta-V Budget
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Supplemental Slide - Propulsion System Size Estimates
Cold Gas Electronic Mono Biprop Solid Performance low med high high very high Thrust .001-3.5N 8-2000mN .19-3780N .009-110kN 25-81kN Specific Impulse 45-73s 500-3000s 200-235s 274-466s 290-304s
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Supplemental Slide - Propulsion System Performance
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Supplemental Slide - Cold Gas Propellants
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Supplemental Slide - New Delta-V Budget
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Supplemental Slide – System Delta-V
Itotal (N·s): Total propellant mass consumed times the average specific impulse Isp (s): Specific impulse is the thrust generated per unit mass flow rate of propellant
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Supplemental Slide – Propellant Choice
Vexit: Exit velocity of exhaust (m/s) k: Specific heat capacity ratio of gas R: Universal gas constant (8.314 J/kmol·K) Mprop: Molar mass of gas (kg/kmol)