{

DynamoCareful Harry

Glenda AlvarengaJ.J. BusseEmily EggersAdam KempGabrielle MassoneDalton SmithCorey Wilson

To Investigate High Altitude Power Generation from the motion of Dynamo using a Kinetic Energy Generator

(K.E.G.) Expected to prove Kinetic Energy Generation is a viable source of power in spacecraft

Mission Overview

Dimensions changed to fulfill weight requirement (23x23x9cm)

Rebuilt new structure with improved insulation

Design Overview

Design Overview

Arduino configured with K.E.G

Design Overview

Canon SD780 Camera

HOBO Data Logger

Design Overview

Heater and Batteries

Functional Block Diagram

{Following Launch, Nov 6, 2011

Results and Failure Analysis

Operated and logged data successfully for 96.7 minutes (roughly 86 minutes of flight)

Stopped at 26,500 ft (entering troposphere)

Noticeable spike in acceleration the instant before

Power cord likely became dislodged upon parachute deployment in lower atmosphere

Altitude correlates, and power found disconnected upon recovery

Analysis: Arduino

Original AttoPilot Voltage Sensor failed before launch

Subsequent transformers, resistors, and circuits routed through Arduino failed to collect data during flight

Lack of appropriate resistors last-minuteAnalysis: Voltage Sensor

Analysis: Accelerometer

6 270 534 798 1062132615901854211823822646291031743438370239664230449447585022528655500

100

200

300

400

500

600

700

800

X Y Z

Time Since Arduino Power-On (seconds)

Accele

rati

on

(each v

alu

e p

ast

base

line =

1%

off

9.8

m/s

^2)

PreLaunch Launch

Burst

Spike be-fore Power Loss

Did not operate during Flight due to Sensor Failure

Mission Simulation Emulated accelerations between 0 - 1

G Successfully produced voltage!

Analysis: K.E.G.

Analysis: Voltage Graph

0 0.1 0.2 0.25 0.3 0.4 0.5 0.6 0.7 0.75 0.8 0.9 10

2

4

6

8

10

12

0 0

4.16

6.12

2.66

9.28

8.64

10.3610.66

11.16

10.110.42

7.16

Average Voltage over 5 Trials

Fraction of G (9.8 m/s^2)

Volt

age (

mil

livolt

s)

HOBO gathered data throughout flight External temperature probe found

disconnected upon recovery Likely caused by movement of other

dislodged objects Recorded Internal Temperatures below -

28° C Did not meet RFP requirement (-10° C)

Analysis: HOBO

HOBO Internal Temp

Lowest Temperatur

e

Temperature dropped to -28° C Heater disconnected from power Cause: Additional, un-insulated hole added

for camera upon camera switch failure Extreme external temps, beyond tested

values Fix: Seal hole, reinforce heater to battery

connections, add insulation Testing: cold test indicates temperatures

above -10° C However, difficult to emulate -70° C

External

Analysis: Insulation & Heater

Camera successfully ran for most of flight

Took images periodically and saved on SD card

Retained power through half of troposphere

Analysis: Camera

Camera Image

8:26:20 (approx.) camera failure Altitude: about 15,225 ft

Correlated EOSS and photo time stamps Dislodged upon recovery Causes of Failure

Impact (disproved by drop/shake testing) Cold (disproved by cold testing) Power button hit when dislodged (Most

Probable, and Repeatable) Fix: Secure Better Within Box, Insulate

Analysis: Camera

Components dislodged Batteries disconnected, loss of power Only half of payload collected data K.E.G. didn’t function during flight

Failure Summary

Conclusion

Despite some failures, mission still successful

Accelerometer data and KEG ground testing suggests kinetic energy could be a viable source of energy

Would required more refined, sensitive generator

Biggest obstacle is lack of noticeable acceleration during majority of ascent

{Appendices

Secure components better More extensive testing, earlier More research into appropriate parts Receive components earlier to extend

testing time Add more insulation, or reorganize

structure to improve thermal properties

Lessons Learned

Ready For Flight

Secure all components more precisely with electrical tape, Velcro and hot glue

Connect camera to proper switch, and seal exposed hole

New batteries and securing of switches before flight

Hobo programmed to start at new flight time for data collection

Thicker copper wire (12 gauge) and more coils on K.E.G. for higher voltage generation

Refined voltage sensor compatible with Arduino Uno

Store Dynamo in cool, dry place with batteries disconnected until flight time

No perishable objects inside

Final Mass: 830 g Final Budget: $213.78

Mass and Weight Budget

{

Compliance Matrix# Requirement Fulfillment

1.01 Our experiment shall use the motion of the BalloonSat to generate electricity and charge a battery.

Successful construction and testing of generator.

1.02 After the BalloonSat lands it shall still be in working order.

Successful kick and drop tests.

1.03 The flight string interface shall be a PVC tube that runs through the BalloonSat and shall not pull through the BalloonSat or interfere with the string. We shall use washers on both sides of the tube and pins that dissipate the pressure onto the washer, preventing the string from being pulled through.

Successful whip tests and integration of flight tube through center of structure.

1.04 The BalloonSat shall remain above -10° C internally during the entire flight.

Successful cold tests and construction of heater.

1.05 The total weight shall remain less than or equal to 850 grams.

Total weight was less than 850 grams.

1.06 We shall acquire the ascent and descent rates of the BalloonSat.

Accelerometer measures changes in flight velocities.

1.07 Our design shall include a HOBO H08-004-02.

Successful integration and data collection during cold test.

1.08 Our design shall include an external temperature cable.

External cable is connected to HOBO.

1.09 Our design shall allow for a Canon SD780.

Successful integration of camera in the corner of Dynamo.

1.10 BalloonSat shall include an active heater system weighing 100 grams with batteries.

Successful construction and test of heater.

1.11 BalloonSat shall be made of foam core.

Successful construction of structure using foam core.

1.12 Our budget shall include a parts list, including spare parts.

Budget is complete and maintains a surplus.

1.13 The design shall allow for and present on the outside of the satellite contact information for the Careful, Harry! team as well as an American flag.

Successful placement of USA flag and contact information on exterior.

1.14 All units presented in the design, construction, and use of the satellite shall be expressed only in the metric system.

Metric system was used for all calculations and dimensions

1.15 The satellite shall be fully constructed and prepared for launch and recovery no later than November 5, 2011, and at least one team member shall agree to participate in the retrieval of the satellite.

Successful construction and test of entire satellite and components.

1.16 Nobody, at any time, or in any phase of this project, shall be injured in any way.

No one was injured during construction and testing.

1.17 All hardware and other materials used are a part of the Gateway to Space program, and shall return to Professor Koehler at the end of the semester in full working order and absolutely no damages.

All material is in working order with no damages.

1.18 All purchases using Professor Koehler's CU Visa for parts shall be recorded in extreme detail on the budget, and all receipts from any purchase made shall be kept and turned in to Professor Koehler within 48 hours of the purchase. Furthermore, a copy of the Gateway order form, HW 04, shall be provided alongside every purchase that is made. These purchases shall only be made after an appointment with Professor Koehler.

Successful recording of purchases, and submission of all receipts for payment and/or reimbursement.

1.19 The satellite design shall not allow for any living organism to be included on the payload.

Payload does not include any living organisms.

1.20 The design of the satellite shall include a visual indicator on the outside of the craft that confirms the payload is fully functional and running.

Switches, button, and flashing LED light indicate proper function.

Message To Next Semester

Choose a challenging yet feasible project Meet early and often with team Tim May and ITL staff are great

resources Secure internal components as best as

you can Extra weight, use it for insulation Be friendly and work well with your

teammates Don’t give up and work hard