Six-Axis Monopropellant Propulsion System for Pico-Satellites

Transcription

1 Six-Axis Monopropellant Propulsion System for Pico-Satellites Mariella Creaghan, Orland Lamce, and Cody Slater 14 October 2015

2 Overview Background Spacecraft Capabilities Thruster System Design Ground Support Equipment Results Conclusion MQP Final Presentation- 2

3 A Wide Variety of Satellites Size International Space Station 419,455 kg Hubble Space Telescope 11,110 kg Voyager 1 & kg Small Satellites < 500 kg Images provided by nasa.gov MQP Final Presentation- 3

4 Small Satellite Categories Pico (<1 Kg) Nano (1-10 kg) Micro ( kg) Mini ( kg) MQP Final Presentation- 4

5 Launch Count The Small Satellite Revolution 1 to 50 kg Satellite Launches Data from SpaceWorks 2014 Market Research Assessment Year Projected Launches Historical Data MQP Final Presentation- 5

6 Laboratory s Approach to Propulsion Cold Gas Thruster Monopropellant Thruster Thrust Exhaust Reaction Wheels MQP Final Presentation- 6

7 Overview Background Spacecraft Capabilities Thruster System Design Ground Support Equipment Results Conclusion MQP Final Presentation- 7

8 System Concept Cylindrical Fuel Tank Dual Manifold Central Feeds Notional Thrust Block Honeycomb Mounting Shelf Triad Valve Arrangement MQP Final Presentation- 8

9 Propellant Selection 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 Hydrogen peroxide provides most versatile, economic performance for immediate space flight MQP Final Presentation- 9

10 Picosatellite Propulsion Objectives Acceleration ~ 1 m/s 2 Slew rate 32 /s Response time < 1 second Goal: To create an adaptable and reliable propulsion system concept for use in a wide range of picosatellite geometries. MQP Final Presentation- 10

11 Overview Background Spacecraft Capabilities Thruster System Design Ground Support Equipment Results Conclusion MQP Final Presentation- 11

12 Objectives Ensure Design, Proof Perform Live-fire test the fabricate, empirical the the safety complete integrated of assemble, experiments all system team component and members and to calibrate optimize characterize and throughout system all the manner length the each resulting of of a required performance catalyst steady stage state bed of ground testing performance with functionality support a specified equipment geometry MQP Final Presentation- 12

13 Catalyst Bed Increases reaction rate Pure silver catalyst Activation procedure Microchannel design Maximum surface area Length estimated with scaling Analytical model started H 2 O H 2 O 2 ΔX O 2 MQP Final Presentation- 13

14 Nozzle Configuration AER = 10 Atmosphere 7,158 Pa Chamber.776 g s 689,000 Pa 1219 K α = 18 D t = mm D 2 = mm L = mm MQP Final Presentation- 14

15 Thruster Block Design Catalyst Bed H 2 O 2 Flow Thermocouple Nozzle MQP Final Presentation- 15

16 Catalyst Block Design Pressure Sensor Catalyst Bed Flow Thermocouple MQP Final Presentation- 16

17 Overview Background Spacecraft Capabilities Thruster System Design Ground Support Equipment Results Conclusion MQP Final Presentation- 17

18 System Layout Thrust Block Control Valve Pressure Sensor Relief Valve Loading Valves Syringe Pump MQP Final Presentation- 18

19 Thrust Stand.21 m Torque Sensor Counter Weight Thrust Block y Reaction Force Exhaust Thrust x MQP Final Presentation- 19

20 Overview Background Spacecraft Capabilities Thruster System Design Ground Support Equipment Results Conclusion MQP Final Presentation- 20

21 System Check and Calibration Safety Precautions Calibrated: In-line pressure sensor Torque sensor Leak Tested: Nitrogen gas Helium gas Water Valve Operation Test MQP Final Presentation- 21

22 MQP Final Presentation- 22 Nitrogen Thrust Testing

23 MQP Final Presentation- 23 Catalyst Test

24 MQP Final Presentation- 24 Integrated HTP Thrust Test

25 Overview Background Spacecraft Capabilities Thruster System Design Ground Support Equipment Results Conclusion MQP Final Presentation- 25

26 Conclusions 1. Safety 2. System setup 3. System proof test 4. Catalyst experiments 5. Integrated system test MQP Final Presentation- 26

27 Future Work Catalyst bed exploration Interface of flow into catalyst Continuation of thrust characterization Long term system improvement MQP Final Presentation- 27

28 Acknowledgements 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 MQP Final Presentation- 28

29 MQP Final Presentation- 29 Questions?

30 MQP Final Presentation- 30 Backup Slides

31 MQP Final Presentation- 31

32 Applied Force (N) Torque Sensor Calibration 1.2 Calibration Curve y = x R² = Omega TQ202 Reaction Torque Sensor N-m range Output Voltage (V) MQP Final Presentation- 32

33 MQP Final Presentation- 33 Mounting Plate