Remote Atmospheric Sensing Device

1
Remote Atmospheric Sensing Device

• Team UNO

2
Team UNO

• Donald Swart
• Cindy Gravois
• René Langlois
• UNO Advisor
• Lawrence Blanchard

3
Objectives

• Using the measurable quantities of UV intensity
• Measure total column thickness of the ozone layer
• Measure relative ozone concentration as a
  function of altitude
• Measure UVB and UVC as it is transmitted and
  attenuated through the stratosphere

4
Expected Results

• Flight profile
• 0 to 30km
• Approximately 90 minute flight
• Increasing UV intensity with increasing altitude
• Largest change at about 15km
• The curve shown on this graph represents ozone
  density as a function of altitude
• Using ozone coverage estimates for the area of
  Palestine, TX provided by NOAA and taken over the
  last 3 years during this week we should see about
  320 DU of ozone coverage.

5
Failure to Launch

• Lack of proper program code
• Programmer quit without warning or writing code
• Progress reports were falsified
• Processor Damaged
• Insufficient time to rework an entirely new
  circuit design

6
Electrical Design

• Detector Array
• Filtered Photo diodes
• Dark Current Compensation
• Controller
• PIC16F917
• 8 16 Kb FRAM units
• Pressure Detection
• Temperature Detection/Regulation

7
New Electrical Design

• BalloonSAT
• 2 bad BalloonSAT boards before good board found
• Required team members to learn a new programming
  language in less than a day
• Voltage regulator broke off during final testing
• Advantage greater on board memory

8
Mechanical Design

• Box
• 8x6x5 inches
• Allows space for all components
• Reflective tape to prevent overheating
• Insulation
• Styrofoam sheets
• 1 inch of exterior foam retains heat
• Provides support for inner electronics

9
New Mechanical Design

• Outer box size unchanged
• Inner box had to be adjusted to accommodate a
  completely new circuit
• Wasted mass due to insufficient time to reduce
  box size
• Advantage more insulation

10
Power System

• Main Payload and Diodes
• Energizer CR 2025 batteries
• 3 V, 170 mAh each
• Heater
• Energizer CR 2025 batteries
• Stacked to provide 6V
• CR 2025 are very lightweight
• 9 total used, less mass than standard 9 V battery
• Can last 5 hours with a constant draw of 30 mA

11
New Power Design

• BalloonSAT required 9V input and had a greater
  current draw than PIC
• 2 9V batteries were used which consumed more mass
  than original power system

12
Final Conclusions

• Forced use of completely new circuit design
• Lack of adequate programming for PIC
• Lost time for proper testing
• Short circuited PIC
• Not found sooner due to misinformation from a
  faculty advisor
• Lack of time for overall testing in new circuit

13
Lessons Learned

• More thorough progress reporting steps
• More team communication
• Common working times and locations
• Cross training on all aspects of essential
  payload design and processes
• i.e. in the event of loss of the programmer
• Greater emphasis on cross training

14
Acknowledgements

• LACES
• Dr. Brad Ellison
• Dr. Greg Guzik
• Stennis Space Center
• Lester Langford
• UNO
• Dr. Greg Seab
• Dr. Terry Reamer
• Dr. Edit Bourgeois
• Dr. Azzam