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Dynamo Critical Design Review. Team 2 Careful Harry Glenda Alvarenga J.J. Busse Emily Eggers Adam Kemp Gabrielle Massone Dalton Smith Corey Wilson. Mission Overview.

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dynamo critical design review

DynamoCritical Design Review

Team 2 Careful Harry

Glenda Alvarenga

J.J. Busse

Emily Eggers

Adam Kemp

Gabrielle Massone

Dalton Smith

Corey Wilson

mission overview
Mission Overview
  • To investigate small scale, high altitude kinetic power generation and assess its applications to present and future spacecraft
  • Hope to prove turbulence of flight can be harnessed as a viable energy source in an otherwise inhospitable environment
  • Hypothesis: greater turbulence and motion during flight will generate greater amounts of power.
mission overview1
Mission Overview
  • Why?
    • Provide alternative power source for present and future spacecraft
    • Determine which variables (altitude, acceleration, air currents, etc…) produce most turbulence and power
    • Indirectly study physical stresses of a spacecraft during launch, flight, recovery, etc…
    • Possible influence on future spacecraft structures
dynamo structure

Dynamo Structure

Top-Down 2 Dimensional View

dynamo structure1

Dynamo Structure

Corner Perspective 3 Dimensional View

kinetic energy generator design overview

Kinetic Energy GeneratorDesign Overview

Changes: Elimination of parabolic motion of magnet, magnets now inside coil.

k e g continued
K.E.G. Continued
  • Inside the coil there shall be a rectangular compartment fitted to the size of 4 disk magnets stacked to form cylinder
  • Sideways motion will cause the magnets to roll within compartment along coil, causing magnetic flux & inducing an electromotive force (voltage) in coil.
k e g continued1
K.E.G. Continued
  • Estimated .4 volts or .2 amps will be generated with 100 mph wind (45 m/s) and 24 gauge copper wire for the material of the coil.
  • 100 mph winds are typically generated within the jet stream, between 7500 – 15000 m
arduino system
Arduino System
  • Arduino Uno
    • 9V battery through Voltage regulator
    • Source code written in open source Arduino compiler
  • AttoPilot Current/Voltage Sensor
  • Triple Axis Accelerometer
  • Both Analog sensors – 10-bit ADC in chip allows for 1024 steps of accuracy in digital data values
camera
Camera
  • Canon SD780 (A780)
  • Take pictures at 10 second intervals for the majority of the trip (about 80 minutes out of 90)
  • Programmed to take video clips at 3 separate times.
    • During launch
    • During the anticipated burst of the balloon
    • During anticipated landing
  • In bottom corner of the satellite with lens pointed outward
  • Wired to a switch on the outside of our BalloonSat for easy activation
  • 2GB SD card to store the images and video clips
  • Images and Video viewed on Corey’s on-site laptop after landing
slide15
HOBO
  • Record internal/external temperature and relative humidity.
  • Located in one of the corners of the BalloonSat.
  • Boxcar program on Corey’s Windows XP laptop.
    • HOBO programmed to start collecting data at launch
    • Upon retrieval, data will be directly uploaded to Corey’s laptop
budget
Budget

Total Weight: 659.9 g

Total Cost: $157.5

slide19

Date Schedule9/27/2011 Turn in order form for mechanical components9/29/2011 Team Meeting (4-6pm)10/3-7/2011 Assemble satellite structure, Kinetic Energy Generator, and HW 05 heater10/3/2011                 Complete Design Document Revisions A/B and CDR10/4/2011   Design Document Revisions A/B due 7:00 am, CDR Presentation10/3-7/2011   Structure Testing (whip, kick, and drop tests)10/6/2011   Team Meeting (4-6pm)10/10-14/2011            Generator motion tests (vibration and sway tests)10/13/2011                 Team Meeting (4-6pm)10/20/2011                  Team Meeting (4-6pm)10/24/2011                  Complete testing; final satellite and generator completed10/25/2011                 Pre-launch inspection10/27/2011                 In-class mission simulation test; Team Meeting (4-6pm)11/1/2011                    Launch Readiness Review (LRR) presentation due at 7:00 am11/1/2011                    Design Document Revision C due at 7:00 am11/3/2011                    Team Meeting (4-6pm)11/4/2011                   Final Dynamo satellite weigh-in and turn-in11/5/2011                   Launch Day (4:45am-TBD)11/5-28/2011               Data analysis and compilation11/29/2011                  Final team presentation and report12/3/2011                   Integrated Technology and Learning Laboratory (ITLL) Design Expo12/6/2011                    Hardware Turn-in in class

test plan
Test Plan
  • Structural and Comprehensive
    • Impact Test (10/6/2011)
    • Whip Test (10/7/2011)
    • Cold Test (by 10/23/2011)
  • Generator
    • Vibration Tests (10/13/2011)
    • Oscillation Tests (10/14/2011)
    • Electrical Circuitry (Throughout)
  • Technical Testing
    • Arduino System (by 10/14/2011)
      • Source Code (debugging, etc…)
      • Accelerometer tests
      • Voltage Sensor tests
      • Verify Data collection
    • Camera (by 10/20/2011)
    • HOBO (by 10/20/2011)
expected results
Expected Results
  • Expect the generator to work
    • Calculated continuous .2 A, .4 V at 1G
  • Most power generated during periods of greatest turbulence
    • Launch, landing
    • Jet Stream
    • Burst
  • Correlation between altitude, acceleration, and power generation
  • Possible correlations between temperature and power generation
    • Temperature = by-product of altitude
biggest worries
Biggest Worries
  • Generator doesn’t work
  • Generator works, but doesn’t produce enough voltage and current for the sensor to see measurable changes over time
  • Arduino programming/assembly glitches
  • General technical malfunctions in programming, circuitry/wiring, etc…
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