Team MuonFinal Presentation

Chelsea DonaldsonGraham RischHenry ShennanJennifer NillJonathan Lumpkin

November 30, 2010

Mission Overview

Team Muon will look for evidence of the “airglow effect” produced when molecular oxygen in the upper atmosphere is excited by fluorescent and resonant processes by observing the intensty molecule’s spectral line emission at 557.7nm.

We expected that the airglow effect would be the most intense at higher altitudes and higher oxygen concentrations.

Design Overview

Design Overview

Design Overview

2 AA batteries Switch Camera 1 Gig Memory 3 9V batteries Switch Heater 9V battery Switch Arduino Microcontroller Hobo Internal Light Intensity to Temperature Frequency IC Humidity External Temperature

Airglow Key Data measuring components Data storage components Heat Power Switch Different areas of measurement

Design OverviewFlow Chart

Design OverviewOur balloon satellite worked by absorbing light through our filter, which filters out all light except ~560 +/- 5 nm wavelength light. The light then hits the light intensity to frequency IC and counts the particles every 1.044 seconds and the particle count information is stored on the Arduino Microcontroller.

Our changes from the proposal to the final design include changing our plan from measuring Earth’s magnetic field and detecting UV rays, to measuring muons with scintillators, and then finally to measuring airglow with a photomultiplier tube. We then revised our design further by measuring airglow with a light intensity to frequency IC instead of the photomultiplier tube.

Results & Analysis

The primary experiment onboard our satellite was unsuccessful.

The exact reason for its failure is currently unknown, although postflight testing indicates the problem may be within the IC itself.

Temperature readings from the HOBO may indicate that cooling of components played a role in that failure.

By increasing insulation and decreasing internal volume, we managed to keep the satellite at sustainable temperatures during a postflight cold test.

Internal and External Temperatures During Flight: 6 November 2010

-70

-60

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-20

-10

0

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6:00

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6:11

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8:41

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10:5

9:00

11:1

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5:00

11:5

6:30

12:0

8:00

12:1

9:30

12:3

1:00

Time

Tem

pera

ture

(¡C

)

Internal Temperature External Temperature

Results & AnalysisResults & AnalysisInternal/External Temperature Data (During Flight)

Launch

Troposphere

Tropopa

use

Burst

Stratosphere

Tropopause

Stratosphere

Troposphere

Temperature Test with Improved Insulation: 29 November 2010

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Time (2h total duration)

Temp

eratu

re (

¡C)

Internal Temperature External Temperature

Cold Test (Retest After Flight)

Results & AnalysisResults & Analysis

Finger touch

Put in co

oler

Took o

ut of cooler

Results & AnalysisResults & AnalysisRelative Humidity Data (During Flight)

Burst

Landing

Condensation Dissipates

Failure Analysis

Our sensor failed to provide meaningful data for the duration of the flight

Analysis: No apparent

correlation with the launch timeline

No apparent correlation with temperature or light

Later tests on the sensor proved it to be malfunctioning, but did not explain flight results

A sensor replacement will be necessary to ready the payload for reflight

Conclusions

As we were unable to collect meaningful data on light intensities in the wavelengths of interest during the flight, we are unable to make any comment as to the presence or absence of daytime airglow in the upper atmosphere.

The value of this experiment came more from discovering

why we had failed and using that information to learn

from our mistakes and correct those we could.

Appendix- Lessons Learned

What would you have done differently if you could do this over?

Would’ve asked more questions and gotten more help in the very beginning of the semester to make sure our experiment would work and is the right choice subsequently avoiding having to make a lot of changes later and losing a lot of time.

Agreed upon more “norms” of the group early on so everyone knows what to expect from each other and themselves in working with the team.

Do more testing with the experiments before launch. What could you have done to get different results?

Weould have done more testing in different conditions and for longer time periods to better anticipate any problems that may happen during flight.

Add more insulation (for internal temperature control).

Appendix- Ready to Fly Again How payload should be stored

Our payload needs to be stored in an environment that will not scratch the lens, or freeze the components.

How payload should be activated for flight In order to activate our BalloonSAT for flight again

the HOBO must be activated. Then the switches that power the other instruments must be flipped on to turn on the camera and our experiment and then the BalloonSAT is ready for flight.

Other We also need to do more testing of the experiment

to make sure our sensor is working correctly.

Appendix- RFP/Proposal/Requirement Compliance Matrix Level # Detail From Compliant?

Basic Requirements

       

O 1 The Satellite shall be launched to a height of 30km and be recovered after landing on November 6

MS Yes

O 2 The BalloonSat shall have a maximum mass of 850 grams. MS Yes mass-830g

O 3 Budget is 300$ MS Yes

O 4 The balloonsat shall take internal and external temperature readings MS Yes with Hobo

O 5 The ballonsat shall carry a camera that will take pictures every 20 seconds.

MS Yes

O 6 The internal temperature shall not dip below -10 degrees Celsius MS No-internal temp reached -25

O 7 The satellite shall carry a photomultiplier tube and filters to measure oxygen light emissions

MS No-a light frequency converter was used instead

Appendix- Level 1

Level 1System Requirements

       Requirement Met?

S 1 The Balloonsat shall be attached to a weather balloon and have a hole through which the flight string will pass.

O1 Yes

S 2 The Balloonsat must be insulated and heated sufficiently enough to ensure the functionality of the payload and ensure that the internal temperature does not drop below -20C.

O4/O6 Yes-all equipment functioned properly

S 4 The balloonsat shall not leak light so that only a certain wavelength is measured

O7 Yes

S 5 A HOBO data logger shall record internal and external temperature of the balloonsat

O4 Yes

S 6 A mass budget and a monetary budget shall be created. O2,O3 Yes

S 7 A Canon A570IS Digital camera shall be flown. O5 Yes

S 8 The BalloonSat shall carry enough power to operate for a specified period of time during the flight.

O1 Yes

S 9 The balloon sat shall carry all necessary experimental equipment O7 Yes

Appendix- Level 2

Level 2Subsystem Requirements

       

SS 1 The BalloonSat shall be constructed of foam core and aluminum tape S3 Yes

SS 2 Payload must be secured so damage does not occur during flight/landing S3 Yes

SS 3 The photomultiplier tube shall be filtered by an optical lens in addition to a neutral density film to prevent oversaturation and misreadings

S9 Yes-with the PMT replaced by light to frequency converter

SS 4 A heating circuit shall be used with three 9V batteries. S2 Yes

SS 5 The balloonsat shall be insulated with insulation foam S2 Yes

SS 6 A magnifying circuit shall be used to amplify power for the PMT S8 No, not necessary

SS 9 An Arduino shall be flown to collect and store data from PMT S9 Yes-however, the sensitivity was too high and the resultant data was unusable.

Appendix- Mass & Cost SummaryPart Description Manufacturer Supplier Dimensions Weight Cost

S1 A570IS camera and accessories Canon GTS 45x75x90mm 228g N/A

S2 HOBO data logger Onset Inc. GTS 68x48x19mm 30g N/A

S3 Arduino Duemilanove and MicroSD shield Arduino Sparkfun 70x53x6mm 35g $44.90

S4 Switches (2) unknown GTS 10x20x20mm 10g N/A

P1 Light to Frequency Converter and housing Taos semi. Sparkfun 5x10x4mm 63g $42.50

P2 6000mAh lithium battery generic Shennan 30x4x75mm 90g Donated

P3 560nm bandpass filter Newport Optics CASA-APS 25mm dia., 5mm long

20g Donated

P4 Neutral Density Filter, 20% Unknown CASA-APS 25mm dia., 5mm long

20g Donated

P6 Filter mount N/A (PVC stock) Shennan 25mm dia, 30mm long

<5g $0.60

A1 Foam Board unknown GTS 4mm, 1.3m3 60g N/A

A2 Foam Insulation unknown GTS 6mm, 0.8m3 50g N/A

A3 Heating circuit, excl. batteries unknown GTS 10x50x50mm 55g N/A

A4 10 9V batteries (3 flight, 7 testing) Duracell McGuckin’s 48x25x15 46g ea. (184g flight)

$30.00

T CO2 (s) (temperature testing) N/A Safeway’s N/A N/A $5.00

Totals 830g $274.35*

A note on part codes (column 1): P: primary systems, S: secondary systems,A: Auxiliary/Structure, T: testing*includes “sunk cost” of parts for an earlier mission, detailed in DD •Newport - 1-877-835-9620

•SparkFun- 1-303-284-0979•McGuckin Hardware- 1-303-443-1822

Company Contact Info:

*Final weight after preparing for reflight is 844 grams

Appendix- Message to Next Semester Go into this class knowing you will be doing a lot of

work outside of class, but you will also be learning an exceptional amount about engineering, science, and teamwork, all of which are very valuable for your college experience and career later in life. Plan ahead so you can make sure you are on track throughout the semester because it is easy to get behind with all of the work that needs to be done. Communicate with your team and be able to know how to utilize each other’s strengths and support them for their weaknesses and allow them to do the same with you. Most of all, have a blast, this is a great experience that few people will ever get to have!