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TEAM CHINESE BANDITOZONE PAYLOAD PRELIMINARILY DESIGN REPORT (PDR)

Zach BaumHarry Gao Ryan MoonSean Walsh

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TABLE OF CONTENTS Document Purpose Mission Goal Objectives Science Background Science Requirements Technical Background Technical Requirements Payload Design Payload Development Plan Project Management Glossary

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DOCUMENT PURPOSE This document describes the preliminary

design for the ozone measurement experiment for Team Chinese Bandits. It fulfills the LaACES project requirements for the Preliminary Design Review (PDR).

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DOCUMENT SCOPE

This document specifies the scientific purpose and requirement for the Ozone experiment and outlines the general instrument and schedule that we will follow to achieve them.

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CHANGE CONTROL AND UPDATE PROCEDURES

A change cannot be made to these finalized documents unless the following guidelines are met:

Changes can be made to controlled documents pending a consensus.

If a consensus cannot be achieved, the team will address a LaACES staff member for resolution.

A detailed log of changes to this controlled document must be kept. Each change must include the date that the change was made, as well as a reference to what was changed within the controlled document.

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MISSION GOAL

Create a profile of ozone concentration with respect to altitude from ground level to 100,000ft.

Ozone sensor reading for 2012 UND/UNF HASP payload

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SCIENCE OBJECTIVES

Map peak of ozone concentration in upper atmosphere.

Create ozone concentration profile with respect to altitude.

Map out any fluctuations within ozone profile.

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TECHNICAL OBJECTIVES

The payload must measure ozone concentration

The onboard program will be able to: Take temperature readings

within close proximity to ozone sensor

Maintain proper operating temperature for all necessary components

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OZONE Converts UV to heat UV-B,C destroy ozone UV-C splits O2

UV radiation types A, B and C are absorbed by ozone in different amounts

SCIENCE BACKGROUND

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Effects of CFC(chlorofluorocarbons) on the ozone

Illustration from: The Center for Atmospheric Science, University of Cambridge

Cl + O3 → ClO + O2

ClO + O3 → Cl + 2 O2

SCIENCE BACKGROUND

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UV AND OZONE Ozone bond energy is 6.04*10^-19 J/bond O2 bond energy is 8.27*10^-19 J/bond

For O2: λ ≤ 240 nm (UVC) For ozone: 330 nm < λ < 240 nm (UVA,UVB,UVC)

SCIENCE BACKGROUND

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OXYGEN-OZONE CYCLE Creation (λ<240nm)

O2 +hv 2 O O2 + O + M → O3 + M

Depletion (240nm< λ <270nm) O3 + hv → O2 + O O3 + O· → 2 O2 2 O· → O2

SCIENCE BACKGROUND

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SCIENCE BACKGROUND

Ozone concentrated in middle and high latitudes

Caused by circulation of stratosphere

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OZONE PEAK

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OZONE PEAK

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SCIENCE REQUIREMENTS

The payload must take measurements of ozone concentration every 3 seconds

Team Chinese Bandits must receive time and altitude GPS information for analysis from LaACES management

The payload must measure the peak ozone concentration to within .2ppmv

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OZONE SENSOR POSSIBILITIES

• ECC Ozonesonde

• Indium Tin Oxide

TECHNICAL BACKGROUND

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ECC OZONESONDE O3(g) + 2KI(aq) + H2O --> I2(g) + 2KOH(aq)

+ O2(g) Measurement of ozone concentration comes

from the rate at which ozone enters the cell and the current produced

Reaction Yields I2 Violet vapor 2KOH blue/clear solution

Temperature constraint 0°C to +40°C

TECHNICAL BACKGROUND

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THE INDIUM-TIN OXIDE (ITO) SENSOR Developed by Dr. Patel of North Florida University Used in recent Avengers LaACES project and HASP

programs Acts like a semiconductor. (Vacancy) + (O3) → (Oo) + O2 Must be kept in the operating temperature range of 25-30°C to remain accurate

ITO sensors as used by Avengers team in 2009-2010

TECHNICAL BACKGROUND

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TECHNICAL BACKGROUNDSPECIFICATIONS OF OZONE SENSORSSpecification Droplet

Measurement Technologies ECC

Ozonesonde

Science Pump Corporation ECC

Ozonesonde

ITO Sensor

accuracy +/-1.2ppmv at worst

+/-.4ppmv at best

---- To within .2ppmv

precision +/-1.2ppmvat worst

+/-10% .1 ppmv

Pressure range 4-1050 hPa (mbar)

3-1014 hPa (mbar)

----

Temperature range

0℃ - 40℃ 0℃ - 40℃ 25℃ -30℃Current draw 120mA 115mA 10mA (per

sensor)

Voltage required 12V ---- Variable (~3V)*see power

budget

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HOW SENSORS MEET REQUIREMENTSRequirement DMT ozonesonde Science Pump

ozonesondeITO Sensor

Must be accurate to within .2

ppmv

Highest accuracy of +/-4% yields +/- 0.4

ppmv at largest expected values.

Lowest accuracy of +/- 12% yields +/- 1.2

ppmv

Accuracy between

ozonesonde units

comparable.

Accurate within +/- 0.2 ppmv

Payload must operate throughout the flight

KI solution may spill at transition from ascent to descent as balloon

is released.

KI solution may spill at transition from ascent to

descent as balloon is released.

measures throughout flight

as long as operational

temperature range is maintained

Payload must not have a mass

greater than 500g

~700 grams sensor with required

batteries, over budget by itself

~600 grams sensor with

required batteries, over budget by itself

~200 grams sensor and required

batteries, reasonable to stay

within budget

Cost must remain within

the allotted $500 budget

$413 ~$400 Free from Dr. Patel

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TEMPERATURE SENSOR(THERMISTOR) Used to detect temperature of BalloonSat

and more specifically, the onboard ozone sensor

Resistor that varies significantly with temperature

Temperature can be approximated by the the following equation

Beaded thermistor with insulation

TECHNICAL BACKGROUND

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HEATER The heater must deliver heat evenly to the

ITO sensor to ensure the temperature of all the ITO sensor strips is maintained

Tape heaters such as polyimide (or Kapton) heaters meet this requirement, as well as having:Low weightA flat design for easy placementLow outgassing to function in very low

pressuresHigh watt density transmission

TECHNICAL BACKGROUND

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GPS UNIT LaACES uses a Lassen iQ GPS unit. The unit

can determine accuracy To the nearest 33 ft with 50% accuracy To the nearest 52.5 ft with 90% accuracy

UND/UNF used the same GPS

TECHNICAL BACKGROUND

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TECHNICAL REQUIREMENTS The payload must: Not have a mass greater than 500g Not exceed 3oz/in2 on any surface Have two holes 17in apart through which the payload will

interface with the balloon Costs must remain within the allotted $500 budget for Chinese

Bandits In order for the payload to create an ozone profile of the

atmosphere, the following requirements must be met: Payload must take measurements of ozone concentration

throughout the flight Payload must be recovered for post-flight analysis Altitude must be known to within 65 feet For the accuracy to be known within 65 feet, the following

requirements must be met: Real-time clock must be synced with GPS time during pre-

flight Real-time clock must be accurate to within 3 seconds of the

LaACES LASSEN iQ GPS

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SYSTEM DESIGN

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TRACEABILITYObjective Requirement ImplementationPayload shall Comply with LaACES Requirements

Not have mass greater than 500g Payload designNot exceed 3oz/in2 on any surface Payload DesignCosts must remain within the allotted $500 budget

Payload Design

Have two holes 17cm apart through which the payload will interface with the balloon

Payload Design

a.) Map peak of ozone in upper atmosphere as accurately as possible b.) Map out any fluctuations within ozone profile

Payload must measure the peak ozone concentration to within .2ppmv

Ozone sensor

Altitude must be known to within 65 feet

Synchronization of real time clock and GPS

Real-time clock must be synced with LaACES GPS pre-flight

Program that can set the real time clock

Real-time clock must be accurate to within 3 seconds of the LaACES GPS

Setting of real time clock

Create ozone concentration profile with respect to altitude

Must receive time and altitude GPS information for post-flight analysis from LaACES management

Receiving information from LaACES

Real-time clock must be accurate to within 3 seconds of the LaACES GPS

Setting of real time clock

Onboard program will take temperature readings and maintain proper operating temperature 

Payload must remain within operating range of sensors

Thermistor and heater

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SENSOR INTERFACE

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CONTROL ELECTRONICS

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POWER

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POWER BUDGETPower Budget

Consumer Consumption Rate Voltage Energy

Ozone Sensors 10 mA * 8 sensors = 80 mA

Variable (dependent on sensor, 3V max)

400 mAh

Thermistor 5 mA 3 V 25 mAh

Heater 117 mA 12 V 585 mAh

Balloon Sat 53 mA 9 V 265 mAh

Total 255 mA   1275 mAh

Power Supply 1

Power Supply 2

Needed capacity

690 mAh 585 mAh

Required Voltage

9 V 12 V

AA Lithium IonVoltage (per battery)

1.5 V

Capacity(per battery)

3000 mAh

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SOFTWARE DESIGN

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DATA FORMAT AND STORAGEByte Offset Data Description

0 Hour Timestamps the Data

1 Minute

2 Second

3 ITO1 Reads ozone concentration

4 ITO2

5 ITO3

6 ITO4

7 ITO5

8 ITO6

9 ITO7

10 ITO8

11 Thermistor Reads temperature of ITO Array

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SOFTWARE DESIGN

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SOFTWARE DESIGN

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THERMAL DESIGN

Component Operating Temperature Range

ADC, RTC, BASICStamp,

EEPROM

-40℃ - 85℃

Lithium Batteries -40℃ - 60℃

ITO Sensor 25℃ - 30℃

o FOAMULAR insulating foam will reduce heat loss

o Kapton heaters provide 5 W/in2

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MECHANICAL DESIGN

Regular hexagonal prism FOAMULAR insulating foam

Lightweight Thermally insulating

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MECHANICAL DESIGNExternal Structure

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MECHANICAL DESIGN

INTERNAL STRUCTURE

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MECHANICAL DESIGN

WEIGHT BUDGETComponent Quantity Mass Uncertainty Calculated/

MeasuredBalloonSAT 1 68.9g +/- 0.05g MeasuredLithium AA

Batteries (9V total unit)

6 88.3g +/- 0.1g Measured

Lithium AA Batteries (12V

total unit)

8 117.9g +/- 0.1g Measured

FOAMULAR Casing

1 57.5g +/- 2 g Calculated

Total   332.6g +/- 2 g  Component Approximate

MassITO sensor and

Operational Amplifier

70g

Sensor Interface 15gElectrical Wiring 15g

Heater and Thermistor

10g

Glue, Paint, Structural

Components

10g

Total 125g

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PAYLOAD DEVELOPMENT PLAN

ELECTRICAL DESIGN DEVELOPMENT

Ozone sensor Select sensor that best meets requirements

Measure ozone to within .2ppmv Take measurements throughout the flight

Order sensor Draw sensor schematic Calibrate sensor Determine necessary gain for conditioning circuit Build conditioning circuit Test in lab conditions with software Test in simulated flight environment with software Finalize schematic

Re-evaluate weight budget to make it more accurate Re-evaluate power budget to make it more accurate

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PAYLOAD DEVELOPMENT PLAN

SOFTWARE DESIGN DEVELOPMENT Read/Write to EEPROM

Create subroutine to write to EEPROM Create subroutine to read from EEPROM

Reading sensors Create subroutine to get data from ADC Create subroutine to timestamp readings

Temperature control Create subroutine to read temperature sensor

and compare to operating range Create subroutine to turn on/off heater

Test all programs on circuits in lab environment

Test all programs on circuits in simulated flight environment

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PAYLOAD DEVELOPMENT PLAN

MECHANICAL DESIGN DEVELOPMENT Determine needed volume to contain

components Determine method of component attachment

to payload Foam cutting and assembling training Thermal tests to ensure sufficient thickness Assemble payload Shock test to confirm system design Re-evaluate weight budget to make it more

accurate

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THERMAL DESIGN DEVELOPMENT Heater Development

Determine thermal interactions of payloadDetermine thermal requirements of heater

Choose heater that best meets thermal requirementsDetermine how the heater will be attached

to the sensor Attach heater to sensor

Test heater/sensor configuration, along with software, under simulated flight environment

Re-evaluate power budget to make it more accurate

Re-evaluate weight budget to make it more accurate

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MISSION DEVELOPMENT The mission will be dependent upon the tasks

listed below: Proper calibration of all sensors is completed Full flight simulation will be run in order to confirm

proper design of all systems Creation of an hour by hour schedule from 24 hours

prior to launch through end of payload operations Creation of a list of all required spare parts that can

be brought within the budget of the payload Creation of a pre-flight checklist Create a list of all component calibrations that

must be done during pre-flight operations Creation of a spreadsheet for post-flight data

analysis Creation of a template for the science presentation

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STAFF ORGANIZATION AND RESPONSIBILITIES

Zach BaumProject Manager

Assistant on:ElectricalMechanicalFlight Data Analysis

Ryan MoonVersion Control and Editing Lead

Assistant on:MechanicalSoftwareSystem TestingFlight Data Analysis

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STAFF ORGANIZATION AND RESPONSIBILITIES

Harry GaoElectrical LeadSoftware LeadCalibrations Lead

Sean WalshMechanical LeadSystem Testing Lead

Assistant on:CalibrationsVersion Control and EditingWritingSoftwareElectrical

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MASTER SCHEDULE

WORK BREAKDOWN STRUCTURE

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MASTER SCHEDULE

WORK BREAKDOWN STRUCTURE

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STAFFING PLANCategory Team Member

Project Manager Zach Baum

Software Developer and Lead

Harry Gao

Mechanical Lead Sean WalshElectrical Lead Harry Gao

Calibrations Ryan MoonDocumentation John Reeks

Integration Zach Baum

Version Control and Editing

Ryan Moon

System Testing Sean Walsh

TIMELINE AND MILESTONES

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RISK MANAGEMENT AND CONTINGENCY

System Risk Contingency Plan

Trigger Who is responsible

Electrical Not returning correct data

Calibration and testing in simulated conditions

Changes in output related to unexpected conditions

Team

Electrical Interface and component problems

Testing components hardware and software before, during, and after assembly

Faulty wiring and components

Harry/John

Mechanical Inclement weather

Structurally sound and sealed mechanical design and testing

Weather Sean/Ryan

Electrical/Mechanical

Inability to maintain operating temperature

Using a heater and thermistor, testing in simulated flight conditions

Extreme cold Team

Electrical Frying EEPROM Have back-up parts, and use extreme caution pre-flight

Stupidity/Carelessness

Zach

All systems Loss of payload Prepare failure report

Loss of payload during flight

Team/LaACES staff

All systems Loss of team member

Rest of team would pick up responsibilities

Increased workload

Team

Project Management

Not meeting deadlines

Set early deadlines to allow for mistakes to be fixed

Poor project management

Zach

Electrical/Software

Not enough memory

Get memory expansion

Not enough space on EEPROM

Harry

All systems Over budget Find cheaper and more cost-effective components

Not enough money

Team

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REFERENCE DOCUMENTSSlide 1:Picture <http://www.nc-climate.ncsu.edu/secc_edu/images/Ozone1.png>Slide 3:Picture http://images.fineartamerica.com/images-medium-large/ozone-molecule-11-russell-kightley.jpgSlide 6:Ozone sensor reading for 2012 UND/UNF HASP payloadSlide 9:Info & right picture <http://www.epa.gov/sunwise/doc/uvradiation.html>Slide 10:Picture <http://www.atm.ch.cam.ac.uk/tour/tour_images/cartoon.gif>Slide 11:Picture <http://www.mmscrusaders.com/newscirocks/ozone/ozone.htm>Slide 14:I2 Sensor info <http://mil-ram.com/public/ta_2102_i2_page.html>Slide 15:Info & picture <http://laspace.lsu.edu/hasp/groups/2012/applications/Payload_07/UND_UNF_HASP_2012_Application.pdf>Slide 16:Info & picture <http://en.wikipedia.org/wiki/Thermistor>Picture <http://2.bp.blogspot.com/-CG6epZAQe_s/TpmuVqn57mI/AAAAAAAABHI/6PEEvCNTeug/s1600/Iodine%252C+Matias+Molnar.JPG>

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GLOSSARY ITO Sensor- Ozone detector using Indium-Tin Oxide as

it’s main component in ozone detection KI Sensor- Ozone detector utilizing potassium Iodide as it’s

main component in ozone detection Ozone - a triatomic molecule consisting of three oxygen

atoms Ppm- parts per million Ultraviolet radiation(UV)- electromagnetic radiation with a

wavelength shorter than visible light but longer than X-Rays . This ranges from 10nm to 100nm

Ultraviolet A (UVA) -electromagnetic radiation from 315nm to 400nm

Ultraviolet B (UVB) - electromagnetic radiation from 280nm to 315nm

Ultraviolet C (UVC)- electromagnetic radiation from 100nm to 280nm