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Team 2 Careful Harry
Glenda Alvarenga
J.J. Busse
Emily Eggers
Adam Kemp
Gabrielle Massone
Dalton Smith
Corey Wilson
DynamoCritical Design Review
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 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
Requirements Flow Down
Shall design and build a BalloonSat to study the potential of high altitude kinetic power generation
Level 0.0
Structure capable of carrying payload to
30km and back
Level 1.0
Kinetic Energy Generator shall
convert mechanical energy into electrical
Level 1.0
C&DH system capable of monitoring
all sensors and recording data
Level 1.0
Capable of recording image/video and data
on environmental variables
Level 1.0
Schedule and budget to maintain time and
cost constraints
Level 1.0
Design Overview
Dynamo Structure
Top-Down 2 Dimensional View
Dynamo Structure
Corner Perspective 3 Dimensional
View
Kinetic Energy Generator
Design Overview
• Changes: Elimination of parabolic
motion of magnet, magnets now
inside coil.
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. 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 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
Arduino System
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
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
Functional Block Diagram
Team Organization
Gabrielle MassoneTeam Leader
C&DH, Systems
Glenda AlvarengaPower and Data Collection
Adam KempPower Generation
Emily EggersBusiness Management
Power and Data Collection
Corey WilsonStructural Design
Dalton SmithStructural Design
J.J. BusseC&DH, Science
Budget
Total Weight: 659.9 gTotal Cost: $157.5
Date Schedule
9/27/2011 Turn in order form for mechanical components
9/29/2011 Team Meeting (4-6pm)
10/3-7/2011 Assemble satellite structure, Kinetic Energy
Generator, and HW 05 heater
10/3/2011 Complete Design Document Revisions A/B and CDR
10/4/2011 Design Document Revisions A/B due 7:00 am, CDR Presentation
10/3-7/2011 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 completed
10/25/2011 Pre-launch inspection
10/27/2011 In-class mission simulation test; Team Meeting (4-6pm)
11/1/2011 Launch Readiness Review (LRR) presentation due at 7:00 am
11/1/2011 Design Document Revision C due at 7:00 am
11/3/2011 Team Meeting (4-6pm)
11/4/2011 Final Dynamo satellite weigh-in and turn-in
11/5/2011 Launch Day (4:45am-TBD)
11/5-28/2011 Data analysis and compilation
11/29/2011 Final team presentation and report
12/3/2011 Integrated Technology and Learning Laboratory (ITLL) Design
Expo
12/6/2011 Hardware Turn-in in class
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• 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
• 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…
