1. Space Proximity Atmospheric Research above Tropospheric Altitudes
HumTemP
Team SPARTA
Space Proximity Atmospheric Research above Tropospheric Altitudes
Jerod Baker
Lisa Caraway
James Mathis
Norfolk State University

2. Mission Goal
Our goal for this experiment is to accurately characterize the atmosphere by investigating humidity, temperature and pressure, as it relates to altitude, within the troposphere, tropopause and lower stratosphere.
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3. Science Background
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4. 9/21/2018
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5. Science Background 9/21/2018 SPARTA - PDR

7. Science Objectives Relative Humidity Measurements above the Tropopause
Compare to NOAA (National Oceanic and Atmospheric Administration
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8. Science Objectives
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9. Scientific Requirements
Data points needed: 100
Minimum pressure measurements: 3 mBars
Minimum Relative Humidity Levels: 0%-5%
Altitude Resolution: 304.8m (1000ft.)
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10. 9/21/2018
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12. Technical Objectives Launch 500g payload 30km
Collect data in near vacuum environment
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13. Technical Requirements
Data rate once per minute
Temperature and Humidity sensors function in -70 degree environment.
Power supply functions in cold
Payload withstands force of landing
Recover data after landing.
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14. Technical Requirements cont.
Power ~ 3 hours
Interior temperature maintained above -20o C
Sensors outside of payload to detect temperature and humidity
Minimal movement inside of Payload
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15. 9/21/2018
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System Design

16. 9/21/2018
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Payload Diagram

17. Weight Budget Items Weight (g) Uncertainty (g) Box/Insulation 100 ±10
Circuits
120
±15
Power & Cables
110
±20
Total
330
± 100
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19. Software Design: Preflight
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Software Design: Preflight

20. Software Design: In-flight
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Software Design: In-flight

21. Software Design: Post flight
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Software Design: Post flight

22. Data Format and Storage
Byte
Data Stored
Format
Sampling Rate 1
Hours
00-24
N/A 2
Minutes
00-59 3
Seconds 4
Temperature
TBD
1 pt./ min 5
Pressure 6 RH
##%
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24. 9/21/2018
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Electrical Design

25. Control Electronics and Sensor Interface
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Control Electronics and Sensor Interface

26. 9/21/2018
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Power Supply

27. Total Min Current drain Total Max Current drain
Power Budget
Power Source 1
Operational Voltage
(V)
Current
(min – max)
(I)
Hours to Function (H)
Total Min Current drain
(I*H)
Total Max Current drain
BalloonSAT 5V
53.7mA 3 - 
161mA 
Power Source 2
Pressure Sensor (Approx)
7V - 9V
 75mA - 100mA
225mA
300mA 
Humidity Sensor (Approx)
7V – 9V
50mA - 60mA
150mA
180mA
Temperature Sensor (Approx)
50mA – 60mA
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29. System Testing Shock test Software test Vacuum test Thermal test
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31. Risk Severity Matrix 5 4 3 Undocumented changes Bad Solder joint
Exceed weight budget 3
Not installing new battery for launch
Not taking computer/program to launch
Payload not recovered 2
Payload dropped preflight 1
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32. Timeline
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33. Timeline
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34. Milestones Preliminary Design Review Critical Design Review
Flight Readiness Review
Balloon Launch
Science Presentation
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35. Team leader/Management
SPARTA Organization
Responsibilities
Team Member
Team leader/Management
Dr. Hinton
Mechanical Design
Jerod Baker
Software Design
JP Mathis
Electronic Design
Lisa Caraway
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37. Conclusion Launch a balloon payload up to 30km
Measure relative humidity, temperature and pressure
Compare our data to NOAA’s
Reach milestones
PDR
CDR
FRR
Science Report
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38. Thanks for Your Attention!
Q&A