Transcript Team Chinese Bandit Ozone Payload Proposal

TEAM CHINESE BANDIT
OZONE PAYLOAD
PRELIMINARILY DESIGN
REPORT (PDR)
Zach Baum
Harry Gao
Ryan Moon
Sean Walsh
1
TABLE OF CONTENTS
Document Purpose
 Mission Goal
 Objectives
 Science Background
 Science Requirements
 Technical Background
 Technical Requirements
 Payload Design
 Payload Development Plan
 Project Management
 Glossary

2
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).
3
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.
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Ozone sensor reading for 2012 UND/UNF HASP payload
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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SCIENCE BACKGROUND
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
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SCIENCE BACKGROUND
Effects of CFC(chlorofluorocarbons) on the ozone
Cl + O3 → ClO + O2
ClO + O3 → Cl + 2 O2
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Illustration from: The Center for Atmospheric Science, University of Cambridge
SCIENCE BACKGROUND
UV AND OZONE



Ozone bond energy is 6.04*10^-19 J/bond
O2 bond energy is 8.27*10^-19 J/bond
𝐸=
ℎ𝑐
λ
For O2: λ ≤ 240 nm (UVC)
 For ozone: 330 nm < λ < 240 nm (UVA,UVB,UVC)

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SCIENCE BACKGROUND
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

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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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TECHNICAL BACKGROUND
OZONE SENSOR POSSIBILITIES
• ECC Ozonesonde
• Indium Tin Oxide
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TECHNICAL BACKGROUND
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
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TECHNICAL BACKGROUND
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
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TECHNICAL BACKGROUND
SPECIFICATIONS OF OZONE SENSORS
Specification
accuracy
precision
Pressure range
Temperature
range
Current draw
Voltage required
Droplet
Science Pump
Measurement
Corporation ECC
Technologies ECC
Ozonesonde
Ozonesonde
+/-1.2ppmv at
---worst
+/-.4ppmv at best
+/-1.2ppmvat
+/-10%
worst
4-1050 hPa
3-1014 hPa
(mbar)
(mbar)
0℃ - 40℃
0℃ - 40℃
ITO Sensor
To within
.2ppmv
.1 ppmv
---25℃ -30℃
120mA
115mA
10mA (per
sensor)
12V
----
Variable (~3V)
*see power
budget
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HOW SENSORS MEET REQUIREMENTS
Requirement
DMT ozonesonde
Science Pump
ozonesonde
ITO 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
KI solution may spill at
transition from ascent to
descent as balloon is
released.
KI solution may measures throughout
spill at transition
flight as long as
from ascent to
operational
descent as balloon temperature range is
is released.
maintained
Payload must not
have a mass
greater than 500g
~700 grams sensor with
required batteries, over
budget by itself
~600 grams
~200 grams sensor
sensor with
and required
required batteries, batteries, reasonable
to stay within budget
over budget by
itself
Cost must remain
within the allotted
$500 budget
$413
Payload must
operate
throughout the
flight
~$400
Free from Dr. Patel
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TECHNICAL BACKGROUND
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

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Beaded thermistor
with insulation
TECHNICAL BACKGROUND
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 weight
 A flat design for easy placement
 Low outgassing to function in very low
pressures
 High watt density transmission

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TECHNICAL BACKGROUND
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
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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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TRACEABILITY
Objective
Payload shall Comply with
LaACES Requirements
Requirement
Not have mass greater than 500g
Not exceed 3oz/in2 on any surface
Costs must remain within the allotted
$500 budget
Have two holes 17cm apart through
which the payload will interface with
the balloon
Payload must measure the peak ozone
concentration to within .2ppmv
Implementation
Payload design
Payload Design
Payload Design
Altitude must be known to within 65
feet
Real-time clock must be accurate to
within 3 seconds of the LaACES GPS
Synchronization of
real time clock and
GPS
Program that can
set the real time
clock
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
Real-time clock must be accurate to
within 3 seconds of the LaACES GPS
Receiving
information from
LaACES
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
a.) Map peak of ozone in upper
atmosphere as accurately as
possible
b.) Map out any fluctuations
within ozone profile
Real-time clock must be synced with
LaACES GPS pre-flight
Payload Design
Ozone sensor
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SENSOR INTERFACE
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CONTROL ELECTRONICS
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POWER
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POWER BUDGET
Power 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
3V
25 mAh
Heater
117 mA
12 V
585 mAh
Balloon Sat
53 mA
9V
265 mAh
Total
255 mA
1275 mAh
Power Supply
1
Power Supply
2
Needed
capacity
690 mAh
585 mAh
Voltage (per
battery)
1.5 V
Required
Voltage
9V
12 V
Capacity(per
battery)
3000 mAh
AA Lithium Ion
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SOFTWARE DESIGN
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DATA FORMAT AND STORAGE
Byte Offset
Data
Description
0
Hour
Timestamps the Data
1
Minute
2
Second
3
ITO1
4
ITO2
5
ITO3
6
ITO4
7
ITO5
8
ITO6
9
ITO7
10
ITO8
11
Thermistor
Reads ozone concentration
Reads temperature of ITO Array
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SOFTWARE DESIGN
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SOFTWARE DESIGN
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THERMAL DESIGN
Component
ADC, RTC,
BASICStamp, EEPROM
Lithium Batteries
ITO Sensor
Operating Temperature
Range
-40℃ - 85℃
-40℃ - 60℃
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 DESIGN
External Structure
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MECHANICAL DESIGN
INTERNAL STRUCTURE
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MECHANICAL DESIGN
WEIGHT BUDGET
Component
Quantity
Mass
Uncertainty
BalloonSAT
Lithium AA
Batteries (9V total
unit)
Lithium AA
Batteries (12V
total unit)
FOAMULAR
Casing
Total
1
6
68.9g
88.3g
+/- 0.05g
+/- 0.1g
Calculated/Measure
d
Measured
Measured
8
117.9g
+/- 0.1g
Measured
1
57.5g
+/- 2 g
Calculated
332.6g
Approximate
Mass
70g
+/- 2 g
Component
ITO sensor and
Operational
Amplifier
Sensor Interface
15g
Electrical Wiring
15g
Heater and
Thermistor
Glue, Paint,
Structural
Components
Total
10g
10g
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 payload
 Determine thermal requirements of heater


Determine how the heater will be attached to
the sensor




Choose heater that best meets thermal requirements
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 Baum
 Project Manager
 Assistant on:
 Electrical
 Mechanical
 Flight Data Analysis
Ryan Moon
 Version Control and Editing Lead
 Assistant on:
 Mechanical
 Software
 System Testing
 Flight Data Analysis
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STAFF ORGANIZATION AND
RESPONSIBILITIES


Harry Gao
 Electrical Lead
 Software Lead
 Calibrations Lead
Sean Walsh
 Mechanical Lead
 System Testing Lead
 Assistant on:
 Calibrations
 Version Control and Editing
 Writing
 Software
 Electrical
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MASTER SCHEDULE
WORK BREAKDOWN STRUCTURE
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MASTER SCHEDULE
WORK BREAKDOWN STRUCTURE
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STAFFING PLAN
Category
Team Member
Project Manager
Zach Baum
Software Developer
and Lead
Mechanical Lead
Harry Gao
Electrical Lead
Harry Gao
Calibrations
Ryan Moon
Documentation
John Reeks
Integration
Zach Baum
Version Control and
Editing
System Testing
Ryan Moon
Sean Walsh
Sean Walsh
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TIMELINE AND MILESTONES
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RISK MANAGEMENT AND CONTINGENCY
System
Risk
Contingency Plan
Electrical
Not returning
correct data
Calibration and
testing in simulated
conditions
Electrical
Interface and
component
problems
Testing components
hardware and
software before,
during, and after
assembly
Structurally sound
and sealed
mechanical design
and testing
Using a heater and
thermistor, testing
in simulated flight
conditions
Have back-up parts,
and use extreme
caution pre-flight
Prepare failure
report
Rest of team would
pick up
responsibilities
Set early deadlines
to allow for
mistakes to be fixed
Get memory
expansion
Find cheaper and
more cost-effective
Mechanical
Inclement
weather
Electrical/Mechanic Inability to
al
maintain
operating
temperature
Electrical
Frying EEPROM
All systems
Loss of payload
All systems
Loss of team
member
Project
Management
Not meeting
deadlines
Electrical/Software
Not enough
memory
Over budget
All systems
Trigger
Changes in output
related to
unexpected
conditions
Faulty wiring and
components
Who is
responsible
Team
Harry/John
Weather
Sean/Ryan
Extreme cold
Team
Stupidity/Carelessn
ess
Zach
Loss of payload
during flight
Increased workload
Team/LaACES staff
Poor project
management
Zach
Not enough space
on EEPROM
Not enough money
Harry
Team
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Team
REFERENCE DOCUMENTS
Slide 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.jpg
Slide 6:
Ozone sensor reading for 2012 UND/UNF HASP payload
Slide 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

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

ITO SensorOzone 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
54