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Microthruster Test Platform Design Presentation II

Erik Mueller Michael White. Microthruster Test Platform Design Presentation II. Contents. Introduction Problem Solution Sensing Frame Testing Q&A Sources. Microthrusters. Microthrusters produce <1N of thrust ( mN range) Various propulsion systems (standard, mono, ion drive).

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Microthruster Test Platform Design Presentation II

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  1. Erik Mueller Michael White Microthruster Test PlatformDesign Presentation II

  2. Contents • Introduction • Problem • Solution • Sensing • Frame • Testing • Q&A • Sources

  3. Microthrusters • Microthrusters produce <1N of thrust (mN range) • Various propulsion systems (standard, mono, ion drive)

  4. The Problem • Thruster and forces involved are minute • Must be rugged and durable • Modular design preferable

  5. Our Solution • Sensing is done through direct thrust measurement using a strain gauge sensor. • Thruster assembly is suspended atop a pole • Secondary force measurement using indirect thrust plume measurement.

  6. System Overview

  7. System Overview Indirect Thrust Plume Pendulum Sensor FM Modulator Circuit Fire Control Strain Gauge Amplifier Circuit DAQ Lab View Software

  8. Structure

  9. Frame • Single pole for the thruster support, grooved bracket w/ clamping system. • Material likely to be aluminum • Easy to work with compared to steel • Strength is more than adequate for the forces involved

  10. Thrust Sensing - Detail

  11. Direct Force Measurement • Strain Gauge • Load Cell • Signal Amplification

  12. Indirect Thrust Measurement • Capacitive Plate System • Exhaust plume exerts force on a plate Induced Force Thruster

  13. Capacitive Pendulum • Uses electronic principle of capacitance • Needle point fulcrums eliminate frictional losses • Double pendulum plates eliminate mechanical noise

  14. Modified Pendulum: Quadruple Pendulum

  15. Signal Processing • Series of amplifiers and filters used to measure the change in signal

  16. Signal Processing • Alternatively, use an FM generator per plate • Compare frequency shifts to determine deflection. • Advantage – more resistant to noise and distortion • Disadvantage – potentially more complex

  17. Software

  18. Software • The signal processor will tie into a computer, along with the rocket ignition circuitry. • Both subsystems will be integrated into a single user-controlled program. We are considering Labview at this time.

  19. Software

  20. Software

  21. Testing

  22. Testing • One rocket test scheduled in the coming weeks to gauge ignition methods & rocket plume • Subsequent test once strain subsystem complete. • Currently creating and testing software with a load-cell.

  23. Testing

  24. Project Management

  25. Work Breakdown Structure • Week 5-6 Subsystem and structure prototype • Week 6-7 Electrical circuit schematics • Week 5-9 Software composition and test • Week 7-10 Final mechanical component fabrication & revision • Week 9-12 Assembly, testing, revisions if needed • More details on website

  26. Budget

  27. Questions?

  28. Works Cited • http://www.grc.nasa.gov • http://images.machinedesign.com • www.answers.com/topic/piezoelectricity • http://www.boeing.com/defense-space/space/bss/factsheets/xips/xips.html • Traceable calibration of the 3-axis thrust vector in the millinewton range, EB Hughes and S Oldfield, National Physical Laboratory • Direct Thrust Measurement of In-FEEP Clusters, IEPC-2005-235, K. Marhold and M. Tajmar, ARC Seibersdorf research GmbH • Rocket Thrust Measurement For an Estes B6-2 Model Rocket Engine, Peter Hyatt, Jeremy LeFevre, Russell Dibb, Bringham Young University • Thrust stand for ground tests of solid propellant microthrusters, S. Orieux and C. Rossi and D. Esteve, Review of Scientific Instruments, Volume73, Number 7, July 2002 • A Ground Test Rocket Thrust Measurement System, Mary Fran Desrochers, Gary W. Olsen, M. K. Hudson, Department of Applied Science and the Graduate Institute of Technology, University of Arkansas • MilliNewton Thrust Stand Calibration Using Electrostatic Fins, Allen H. Yan, Bradley C. Appel, Jacob G. Gedrimas, Purdue University

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