six-axis monopropellant propulsion system for pico-satellites · 2016. 3. 28. · six-axis...
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Mariella Creaghan, Orland Lamce, and Cody Slater
14 October 2015
Six-Axis Monopropellant Propulsion
System for Pico-Satellites
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MQP Final Presentation- 2
MC, OL, CS 10/15/2015
Overview
• Background
• Spacecraft Capabilities
• Thruster System Design
• Ground Support Equipment
• Results
• Conclusion
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MQP Final Presentation- 3
MC, OL, CS 10/15/2015
A Wide Variety of Satellites
Size
International
Space Station
419,455 kg
Hubble Space
Telescope
11,110 kg
Voyager 1 & 2
733 kg
“Small” Satellites
< 500 kg
Images provided by nasa.gov
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MQP Final Presentation- 4
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Small Satellite Categories
Pico
(<1 Kg)
Nano
(1-10 kg)
Micro
(10-100 kg)
Mini
(100-500 kg)
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MQP Final Presentation- 5
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0
50
100
150
200
250
300
350
400
450
2009 2010 2011 2012 2013 2014 2015 2016 2017 2018 2019 2020
La
un
ch
C
ou
nt
Year
1 to 50 kg Satellite Launches
Projected Launches
Historical DataData from SpaceWorks 2014 Market Research Assessment
The Small Satellite Revolution
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MQP Final Presentation- 6
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Monopropellant
Thruster
Cold Gas
Thruster
Reaction
Wheels
Laboratory’s Approach to Propulsion
Exhaust Thrust
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MQP Final Presentation- 7
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Overview
• Background
• Spacecraft Capabilities
• Thruster System Design
• Ground Support Equipment
• Results
• Conclusion
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MQP Final Presentation- 8
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System Concept
Notional Thrust
Block
Dual Manifold
Central Feeds
Honeycomb
Mounting Shelf
Triad Valve
Arrangement
Cylindrical Fuel Tank
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MQP Final Presentation- 9
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Propellant Selection
Hydrogen peroxide provides most versatile, economic performance for immediate
space flight
Volumetric
Impulse
(kg*s/m^3)
Ground
Infrastructure Test Precautions Attainability Flight Proven
Nitrogen Gas 33,314 Moderate Minimal Easy Often Used
Hydrogen
Peroxide 215,298 Moderate Highly reactive Easy Popular in 1960s
Hydrazine 234,600 Extreme Carcinogenic Moderate Standard
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MQP Final Presentation- 10
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Picosatellite Propulsion Objectives
Goal: To create an adaptable and reliable propulsion system concept for use in a
wide range of picosatellite geometries.
• Acceleration ~ 1 m/s2
• Slew rate 32 °/s
• Response time < 1 second
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MQP Final Presentation- 11
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Overview
• Background
• Spacecraft Capabilities
• Thruster System Design
• Ground Support Equipment
• Results
• Conclusion
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MQP Final Presentation- 12
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1. Ensure the safety of all team members throughout each stage of testing
Objectives
2. Design, fabricate, assemble, and calibrate all manner of required ground support equipment
3. Proof test the integrated component and system performance for functionality 4. Perform empirical experiments to optimize the length of a catalyst bed with a specified geometry 5. Live-fire the complete system and characterize the resulting steady state performance
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MQP Final Presentation- 13
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• Increases reaction rate
• Pure silver catalyst
• Activation procedure
• Microchannel design
• Maximum surface area
• Length estimated with scaling
• Analytical model started
Catalyst Bed
ΔX
H2O2
H2O
O2
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MQP Final Presentation- 14
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Nozzle Configuration
AER = 10
Dt = 1.162 mm
L = 3.862 mm
α = 18° Chamber
.776 𝒈
𝒔 689,000 Pa
1219 K
D2 = 3.670 mm
Atmosphere
7,158 Pa
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MQP Final Presentation- 15
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Thruster Block Design
Thermocouple
Catalyst Bed
Nozzle
H2O2 Flow
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MQP Final Presentation- 16
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Catalyst Block Design
Flow
Catalyst Bed
Thermocouple
Pressure
Sensor
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MQP Final Presentation- 17
MC, OL, CS 10/15/2015
Overview
• Background
• Spacecraft Capabilities
• Thruster System Design
• Ground Support Equipment
• Results
• Conclusion
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MQP Final Presentation- 18
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System Layout
Syringe Pump
Relief
Valve
Pressure
Sensor Loading
Valves
Control
Valve Thrust
Block
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MQP Final Presentation- 19
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Thrust Stand
Exhaust Thrust Reaction Force
.21 m
x
y
Thrust Block
Torque Sensor
Counter Weight
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MQP Final Presentation- 20
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Overview
• Background
• Spacecraft Capabilities
• Thruster System Design
• Ground Support Equipment
• Results
• Conclusion
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• Safety Precautions
• Calibrated:
– In-line pressure sensor
– Torque sensor
• Leak Tested:
– Nitrogen gas
– Helium gas
– Water
• Valve Operation Test
System Check and Calibration
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MQP Final Presentation- 22
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Nitrogen Thrust Testing
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MQP Final Presentation- 23
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Catalyst Test
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MQP Final Presentation- 24
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Integrated HTP Thrust Test
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MQP Final Presentation- 25
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Overview
• Background
• Spacecraft Capabilities
• Thruster System Design
• Ground Support Equipment
• Results
• Conclusion
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MQP Final Presentation- 26
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1. Safety
2. System setup
3. System proof test
4. Catalyst experiments
5. Integrated system test
Conclusions
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MQP Final Presentation- 27
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• Catalyst bed exploration
• Interface of flow into catalyst
• Continuation of thrust characterization
• Long term system improvement
Future Work
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MQP Final Presentation- 28
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• Jesse Mills
• Adam Shabshelowitz
• Kurt Krueger
• Sean Crowley
• Mark Seaver
• Sharon Hardiman
Additional thanks to: Mike Shatz, Dennis Burianek, Marc Brunelle, John Howell, Prof. Gatsonis, Prof. Clancy, Professor Blandino, Jocelyn O’Brien, Gerald Johnson, Andy Kalil, Ted Bloomstein
Acknowledgements
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MQP Final Presentation- 29
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Questions?
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Backup Slides
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MQP Final Presentation- 31
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MQP Final Presentation- 32
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Torque Sensor Calibration
Omega TQ202 Reaction Torque Sensor
0-0.2 N-m range
y = 343.13x + 0.3231 R² = 0.9977
0
0.2
0.4
0.6
0.8
1
1.2
-0.001 -0.0005 0 0.0005 0.001 0.0015 0.002 0.0025
Ap
plied
Fo
rce (
N)
Output Voltage (V)
Calibration Curve
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MQP Final Presentation- 33
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Mounting Plate