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Microthruster Test Rig Design: A Comprehensive Review and Development Overview

This presentation reviews the design and development of a microthruster test rig, essential for measuring thrust in the millinewton range. It discusses critical design elements including vacuum testing requirements, sensing solutions utilizing capacitive measurements, and structural considerations for durability. The proposed rig features a single-pole suspension system, a vacuum chamber for testing, and integrated signal processing software. Our approach aims at creating a user-controlled interface for efficient monitoring and testing of various micropropulsion systems.

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Microthruster Test Rig Design: A Comprehensive Review and Development Overview

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  1. Erik Mueller Michael White Microthruster Test RigDesign Review Presentation

  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 • Testing must be done in a vacuum • Must be rugged and durable

  5. Our Solution • Sensing is done through direct thrust measurement • Thruster assembly is suspended via a single pole • Entire device is a vacuum chamber

  6. Overview

  7. Overview Pendulum Mount Thruster Mount

  8. Thrust Sensing - Detail

  9. Indirect Thrust Measurement • Exhaust plume exerts force on a plate Induced Force Thruster

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

  11. Modified Pendulum: Quadruple Pendulum

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

  13. Software

  14. Software • The signal processor will tie into a computer, along with the rocket ignition circuitry and vacuum monitoring sensors. • All three subsystems will be integrated into a single user-controlled program. We are considering Labview at this time.

  15. Structure

  16. Frame • Currently still in the conceptual phase • Strong contender is the suspension design, via a single pole from above • Material likely to be aluminum • Easy to work with compared to steel • Strength is more than adequate for the forces involved

  17. Testing

  18. Testing • Currently no concrete plans are in place • Planning to use a set of small conventional chemical thrusters (Estes model rocket engines)

  19. Questions?

  20. 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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