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

2. 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.

3. 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

4. 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

5. Design Overview

6. Dynamo Structure Top-Down 2 Dimensional View

8. Dynamo Structure Corner Perspective 3 Dimensional View

10. Kinetic Energy Generator Design Overview Changes: Elimination of parabolic motion of magnet, magnets now inside coil.

11. 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.

12. 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

13. 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

14. 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

15. 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

16. Functional Block Diagram

17. Team Organization Gabrielle Massone Team Leader C&DH, Systems Glenda Alvarenga Power and Data Collection Adam Kemp Power Generation Emily Eggers Business Management Power and Data Collection Corey Wilson Structural Design Dalton Smith Structural Design J.J. Busse C&DH, Science

18. Budget Total Weight: 659.9 g Total Cost: $157.5

19. Date Schedule 9/27/2011Turn in order form for mechanical components 9/29/2011Team Meeting (4-6pm) 10/3-7/2011Assemble 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

20. 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)

21. 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

22. 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…