DynamoTeam Careful Harry

Glenda Alvarenga

J.J. Busse

Emily Eggers

Adam Kemp

Gabrielle Massone

Dalton Smith

Corey Wilson

Launch Readiness Review

MissionTo investigate high altitude power generation from the motion of Dynamo using a Kinetic

Energy Generator (K.E.G.)

Design Overview

Foamcore

Insulation

Aluminum Tape

Design Overview

Arduino Uno with microSD Shield

Arduino configured with K.E.G

Design Overview

Canon SD780 Camera

HOBO Data Logger

Design Overview

Heater and Batteries

Test Results3 Primary Types of TestingGenerator (K.E.G.)TechnicalStructural

1 2 3 4 5 6 7 8 9 10 11 12 13 14 150

1

2

3

4

5

6

7

Voltage during Oscillation

Voltage

Time (s)

Vo

ltag

e (m

V)

Greatest voltage = great-est flux = greatest accel-eration

Least voltage = least flux = least acceleration

1 5 9 13 17 21 25 29 33 37 41 45 49 53 57 61 65 69 73 77 81 85 89 93 97 101 105 109 113 1170

100

200

300

400

500

600

700

ADXL 335 Accelerometer Oscillation Test

x

y

z

Time (ms)

Acc

eler

atio

n (

Eac

h I

nte

ger

Ch

ang

e fr

om

In

itia

l =

1%

G)

Max X Acceleration (3.2 G)

Max Y Acceleration(2.3 G)

Max Z Acceleration(.71 G)

Min X Acceleration (-3.2 G)

Min Z Acceleration (-2.1 G)

Min Y Acceleration (-2.9 G)

Baseline X, Y, Z acceleration at rest

Baseline X, Y, Z acceleration at rest

Technical Testing Arduino

Source code debugging through compiler Ran all code for sensors through serial port/serial monitor to

ascertain proper function Installed and tested microSD shield and card for data logging Precautions taken to avoid data overwrite upon start up Files loaded onto computer from microSD card via SD Card to

USB reader Data transferred to excel worksheets and analyzed

Technical Testing Camera

Allowed to run during all tests – successfully took pictures at 10 second intervals

HOBO Successfully gathered internal/external temperature and humidity

data throughout duration of cold test Heater

Demonstrated some malfunction during cold test Excessively low temperatures cause resistors to stop working Performs successfully at all other times

Technical Testing Cold Test

Tried 3 times – still inconclusive Follow-up testing to determine if structure and insulation are

adequate Miscellaneous

All switches, wires, solder joints, and other circuitry are performing successfully

33:43.036:49.039:55.043:01.046:07.049:13.052:19.055:25.058:31.001:37.004:43.007:49.010:55.014:01.017:07.00

5

10

15

20

25

Cold Test #1 – Internal Temperature

Temperature (*C) (1)

Time (min:sec)

Tem

per

atu

re (

C)

Final Temperature too high

Starting Room Temperature

33:43.036:07.038:31.040:55.043:19.045:43.048:07.050:31.052:55.055:19.057:43.000:07.002:31.004:55.007:19.009:43.012:07.014:31.016:55.0

-2

-1.5

-1

-0.5

0

0.5

1

Exteral Temperature

Time (min:sec)

Tem

per

atu

re (

C)

Temperature goes up?

56:28.059:16.002:04.004:52.007:40.010:28.013:16.016:04.018:52.021:40.024:28.027:16.030:04.032:52.035:40.038:28.0

-40

-30

-20

-10

0

10

20Cold Test #2

Time (min:sec)

Tem

per

atu

re (

C)

Removal of Sat. from cooler

Supposedly External

Supposedly Internal

Initial Temperature

Structural Tests Whip test

Initially failed due to string breakage – string too weak Successful test with proper flight string

Drop/kick Test Survived inadvertent fall down three stories in DLC Maintained integrity through most severe testing, with little

visible damage

Predicted Results Dynamo will generate a measurable amount of energy, likely

in the range of millivolts to centivolts HOBO will gather temperature and humidity data Camera will take pictures at 10 second intervals throughout

the flight Structure will survive the trip and be ready for a relaunch

Biggest Worries Satellite becomes too cold – cold test inconclusive 3 times Energy generated is not significant enough to register on the

sensor Unnoticed errors in coding compromise data collection General technological malfunctions Flight string is compromised and Dynamo is lost

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.