team chinese bandit ozone payload preliminarily design report (pdr )
DESCRIPTION
Team Chinese Bandit Ozone Payload Preliminarily Design Report (PDR ). Zach Baum Harry Gao Ryan Moon Sean Walsh. Table of Contents. Document Purpose Mission Goal Objectives Science Background Science Requirements Technical Background Technical Requirements Payload Design - PowerPoint PPT PresentationTRANSCRIPT
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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