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Microthruster Test Platform Design Presentation II PowerPoint PPT Presentation


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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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Erik Mueller

Michael White

Microthruster Test PlatformDesign 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)


The Problem

  • Thruster and forces involved are minute

  • Must be rugged and durable

  • Modular design preferable


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.


System Overview


System Overview

Indirect Thrust Plume Pendulum Sensor

FM Modulator

Circuit

Fire Control

Strain Gauge

Amplifier Circuit

DAQ

Lab View

Software


Structure


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


Thrust Sensing - Detail


Direct Force Measurement

  • Strain Gauge

  • Load Cell

  • Signal Amplification


Indirect Thrust Measurement

  • Capacitive Plate System

  • Exhaust plume exerts force on a plate

Induced Force

Thruster


Capacitive Pendulum

  • Uses electronic principle of capacitance

  • Needle point fulcrums eliminate frictional losses

  • Double pendulum plates eliminate mechanical noise


Modified Pendulum: Quadruple Pendulum


Signal Processing

  • Series of amplifiers and filters used to measure the change in signal


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


Software


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.


Software


Software


Testing


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.


Testing


Project Management


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


Budget


Questions?


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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