OZONE MEASUREMENTS:A LAACES PAYLOAD PROPOSALBY TEAM CHINESE BANDITS

Zach BaumHarry Gao Ryan MoonJohn ReeksSean Walsh

MISSION GOAL

The mission goal of this payload is to measure the concentration of Ozone (O3) as a function of Altitude and Time

PREVIOUS ATTEMPTS BY OTHER TEAMS Previous Team Reason for

FailureProposed Fix

Avengers Phase 2 Blown EEPROM failure to calibrate sensor

Allow more time for testing and double check vital electronics as part of preflight checklist.

Avengers Phase 1 Unable to keep sensor in operating range. Wiring issuing with circuit.

Design system with the ability to increase temperature(heater). Have guidelines to follow for wiring circuits to ensure proper debugging.

OBJECTIVES Science Objectives

The objective of this project is to measure the concentration of Ozone (O3) focusing on an altitude from 10 km to 50 km from sea level

Measure the concentration of ozone with respect to time of day

Technical Objectives Produce readable measurements on ozone

concentration To keep sensors within operating range Record collected data for retrieval

SCIENCE BACKGROUND

WHAT IS OZONE?

The Ozone layer is located in the lower portion of the stratosphere, from approximately 10 km to 50 km above ground

SCIENCE BACKGROUNDWHY IS OZONE IMPORTANT Ultraviolet radiation is a major source for

destroying and creating stratospheric ozone

*Team Avenger 2010-2011 CDR presentation

REQUIREMENTS

Science Requirements Shall measure ozone concentration as a function of

altitude and time Technical Requirements

Temperature in the BalloonSat shall be kept within the operating range of onboard sensors and electronics

Ozone shall be measured as a voltage coming from the sensor

The measurement of ozone shall be recorded and time stamped in order to calculate altitude

PRINCIPLES OF OPERATION Measured voltage is a function of Ozone

concentration Two choice of implementation Potassium Iodide Sensors (KI)

Reacts with the ozone to generate a small current Liquid form (mixing chemical) Led to many problems including leaks, spills, and

short circuits Indium Tin Oxide sensor has variable

resistance based on Ozone and NOx concentration More accurate than KI sensors because it utilizes a

metal-oxide compound.

SENSORS AND ELECTRICAL ITO detects Ozone Concentration

Thermistor measures temperature inside payload Used to regulate temperature

Balloon Sat Board 9 Volt board Records and processes input data

Power Supply Lithium batteries connected in parallel

SENSOR INTERFACE

CONTROL ELECTRONICS

Data Data

Power

POWER

POWER SUPPLY

*Data from previous project by Avengers group. (CDR)

Consumer Consumption Rate

Ozone Sensors(per sensor)

10 mA 40 mAh

Thermistor 5 mA 20 mAhHeater TBD TBDBalloon Sat 53 mA 212 mAhTotal Greater than 68

mAGreater than 272 mAh

PROJECT MANAGEMENT Meetings outside of mandatory meetings

Monday, Wednesday: 6:00 PM Tuesday, Thursday: 5:30 PM

Internal deadlines set every Monday Meetings monitor task progress

MECHANICAL DESIGN External Structure

¾ inch thick insulating foam Hexagonal shape 2 vertical holes 17 cm (6.7 in) apart through

opposite walls for interface to LaACES payload strings

Internal Structure Brace board used to carry and support internal

components Light weight

ITO will be mounted on a foam panel

WEIGHT BUDGET** Payload has 500 g mass limitation

+/- 48

WEIGHT BUDGET (CONT.) Possible improvements:

A smaller battery can be used -50g +/- 20

The amount of wire may be reduced -20g +/- 10

The foam width may be reduced from ¾ inch to ½ inch

-35g +/- 20

Adjusted Total: 425g +/- 56

ORGANIZATIONMember’s Name

Title Major Responsibility

Testing/Calibration Prototyping Documentation

Zack Baum

Project Manager*

Communication between team and staff, task assignment, progress tracking

Mechanical Mechanical Managerial/ Managerial

Sean Walsh

Mechanical*

Mechanical Design

Mechanical Mechanical Mechanical

Harry Gao Electrical*/ Software*

Electrical and Software design

Electrical/Software Electrical/ Software

Electrical/Software

John Reeks

Electrical Electrical Design

Electrical Electrical Electrical

Ryan Moon

Software Software design Software Software Software

RISK ANALYSIS

*based upon Avengers Phase 1

CONFIGURATION MANAGEMENT Leads present prototypes two weeks prior to

Pre-CDR Each lead is responsible for completion of

tasks Documentation Research Design

Manager is responsible for monitoring tasks and deadlines

STAFFING PLANTask Category Project LeadProject Management Zach BaumScience Requirements John ReeksElectronics Harry GaoFlight Software Harry GaoMechanical Sean WalshIntegration Ryan MoonSystem Testing Sean WalshCalibrations Harry GaoData Processing and Analysis John ReeksDocumentation Ryan Moon

TIMELINE OF MILESTONES

TIMELINE OF MAJOR TASK CATEGORIES

COSMIC RAYS:A LAACES PAYLOAD PROPOSALBY TEAM CHINESE BANDITS

Zach BaumHarry GaoRyan MoonJohn ReeksSean Walsh

MISSION GOAL

The goal of this project is to create a payload that will measure the flux of cosmic radiation as a function of altitude.

ASSESSMENT OF PREVIOUS FLIGHTS

Group Payload Summary What needs improvement Possible Solutions

Team Flux2002-2003

Compared change in air density to radiation

counts

Only radiation counts were taken. Flux should be taken for increased

understanding

Radiation counts should be taken over a known

area and field of view to determine flux

Team GR22005-2006

Tried to determine the change in flux of cosmic

radiation and gamma radiation with altitude using Geiger-Mueller

sensors

The Geiger-Mueller sensor coated with lead

lost function at low temperature

Reduce focus of measurement to

ionizing particles and use sensors with less

risk of failure

Team Cosmic2009-2010

Determined the flux of cosmic radiation using dual scintillators and

photomultiplier tubes

There were outlying points and noise which caused inaccuracies in

the data

Use a different sensor configuration that reduces noise and provides greater

accuracy

PREVIOUS FLIGHT DATA

Radiation Intensity with altitude as taken by Team Cosmic, 2009-2010

OBJECTIVES Science Objectives

Measure the intensity of ionizing cosmic radiation as flux

Technical Objectives Design and build a system that can:

Withstand atmospheric conditions up to 100,000 feet

Count the number of radiation hits on separate sensors

Measure the energy of radiation hits over time on separate sensors

Monitor temperature and pressure to determine that they are in the operational range of the sensors

Record collected data and output for retrieval

SCIENCE BACKGROUND Two types of Cosmic Rays

Primary Secondary

Primary Rays High energy charged particles Enter the atmosphere

Secondary Rays Product of Primary interactions

*http://www.mpi-hd.mpg.de/hfm/CosmicRay/Showers.html

SCIENCE BACKGROUND Possible Sensors

Geiger Counter Detects radiation with gaseous ionizing detector Creates charge relative to amount of radiation

Track-Etch Technique Clear plastic stacked Charged particle causes chemical bond breaking along

path Must be chemically dissolved after flight to observe

paths PMT Scintillator Combination

Scintillator releases light when charged particle passes through

Photomultiplier tube converts light to a charge

REQUIREMENTS

Science Requirements To measure flux of ionizing radiation as a

function of altitude Technical Requirements

Provide necessary power to all components that need it

Sample the number of hits over an interval, every 1000 feet

Convert the sensor’s current pulse into a voltage pulse

Store each measurement of cosmic ray

SENSORS AND ELECTRICAL Geiger Counter

Signal will be output as electrical charge Measures all radiation

Track-Etch Technique Plastic must be broken down with chemicals after

flight Paths must be measured with microscope

PMT Scintillator Combination Signal will be output as electrical Measures ionizing radiation passing through with

less interference from gamma radiation

PRINCIPLES OF OPERATION After evaluation of possible sensors, the PMT

Scintillator combination was chosen for feasibility test

Measurement of cosmic ray collisions as a function of current pulses over an interval

The two scintillators receive energy when charged particles collide with them. They then emit this energy as light, with the amount of light produced proportional to the energy of the particle

The photomultiplier tube collects this light and produces a current proportional to the amount of light it receives

SYSTEM DESIGN

SENSOR INTERFACE

CONTROL ELECTRONICS

POWER

POWER BUDGET

Consumer Consumption rate

Total Consumption

PMT 22 mA 88 mAhPMT 22 mA 88 mAhBalloon Sat 53 mA 212 mAhDC to DC 50 mA 200 mAhTotal 147 mA 588 mAh

MECHANICAL DESIGN External Structure

¾ inch thick insulating foam Hexagonal Shape 2 vertical holes 17 cm (6.7 in) apart through

opposite walls for interface to LaACES payload strings

Internal Structure Brace board will brace payload and carry

electronic components

WEIGHT BUDGETPart: Measuremen

tmethod

Mass:

Foam Casing Estimated 130 +/- 10gPower Supply Estimated 147 +/- 30gBalloonSat Weighed 68.9 +/- 0.05gSensor and Interface

Estimated 150 +/- 30g

Total: 496 +/- 44g

*Estimates based upon the similar Team Cosmic payload

REFERENCES http://imagine.gsfc.nasa.gov/docs/science/know_l1/

cosmic_rays.htm http://www.srl.caltech.edu/personnel/dick/cos_encyc.html http://www.sciencedirect.com/science/article/pii/

S1350448701002281 http://galileo.ftecs.com/stone-diss/chap3/count-rate.html http://laspace.lsu.edu/aces/teams/2009-2010/teams/Cosmic/

LSU_3.php http://laspace.lsu.edu/aces/Teams/2010-2011/LSU/Avengers/

LSU_3.php http://laspace.lsu.edu/aces/teams/2009-2010/teams/Avengers/

LSU_1.php