Ozone Measurements: A LaACES Payload Proposal by Team Chinese Bandits

1. Ozone Measurements:A LaACESPayload Proposalby Team Chinese Bandits Zach Baum Harry Gao Ryan Moon John Reeks Sean Walsh

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

3. Previous Attempts by other Teams

4. 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

5. Science BackgroundWhat is Ozone? • The Ozone layer is located in the lower portion of the stratosphere, from approximately 10 km to 50 km above ground

6. Science BackgroundWhy is Ozone important • Ultraviolet radiation is a major source for destroying and creating stratospheric ozone *Team Avenger 2010-2011 CDR presentation

7. 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

8. 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.

10. 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

11. Sensor Interface

12. Control Electronics Data Data Power

13. Power

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

15. 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

16. 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

17. Weight Budget** • Payload has 500 g mass limitation +/- 48

18. Weight Budget (cont.) • Possible improvements:

19. Organization

20. Risk Analysis *based upon Avengers Phase 1

21. 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

22. Staffing Plan

23. Timeline of Milestones

24. Timeline of Major Task Categories

25. Cosmic Rays:A LaACESPayload Proposalby Team Chinese Bandits Zach Baum Harry Gao Ryan Moon John Reeks Sean Walsh

26. 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.

27. Assessment of Previous Flights

28. Previous Flight Data Radiation Intensity with altitude as taken by Team Cosmic, 2009-2010

29. 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

30. 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

31. 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

32. 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

33. 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

34. 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

35. System Design

36. Sensor Interface

37. Control Electronics

38. Power

39. Power Budget

40. 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

41. Weight Budget *Estimates based upon the similar Team Cosmic payload

42. 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