1. Space Cadets Ali Javed Ravneet Singh Ravneet Singh Brock Couvillion Dean Slama Dean Slama Temperature, Pressure, Humidity, and Imaging Characteristics at Various Altitudes

2. MISSION GOALS The goal is to study the relationships between the temperature, pressure, humidity, and altitude ranging from 0 to 100,000 ft in an effort to identify trends at various layers of the atmosphere using a balloon payload launched from Palestine, TX.

3. OBJECTIVES The objective of this project is to fly a balloon payload to an altitude of 100,000 ft to measure, record and verify temperature, pressure, and humidity trends. Also, record video of the flight and verify the trends at various atmospheric layers.

4. Science Objectives Verify the decrease of temperature in tropopause Verify the increase of temperature in stratosphere Verify the decrease of pressure with altitude Verify the decrease in humidity with altitude. Identify the motion of flight.

5. Earth’s Atmosphere

6. Temperature

7. Pressure

8. MOISTURE RAIN Amount of moisture the air can hold before it rains.

9. LINEAR VOLTAGE SENSOR30 SECONDS

10. Areas that are elevated have a higher percentage of humidity compared to areas of lower elevation. 209 ft elevation 653 ft elevation 20 ft elevation

11. IMAGING CHARACTERISTICS

12. System Design

13. Electronics/Sensors 12V Battery pack provides voltage 8 1.5V AA Lithium Batteries Temperature-Sensitive Diodes Voltage across diode varies directly with temperature, low output range. Linear-Voltage Humidity Sensor Powered by 5V Output is linear voltage from.8-3.5V Pressure Transducer Powered by 5V Output is linear voltage

14. Signal Conditioning Op-Amps condition signals to match range of ADC

15. Control System Basic Stamp issues commands Retrieves Values From ADC Writes values to EEProm Issues commands to Camera Camera Data stored in internal Memory

16. Flight Software *Initialize *Take readings every 30 seconds and writes to EEProm *Control Camera *Prevent memory overflow

17. Power Supply

18. Power Budget

19. Thermal Design Need to do a thermal test of internal operating temperature in a low- temperature environment For now the assumption is that the operating electronics will generate enough heat to maintain proper operating temperatures above -40 degrees Celsius ComponentMinimum Operating Temperature Maximum Operating Temperature Basic Stamp BS2P24 -40 ° C 85 ° C A/D Converter ADC0834 -40 ° C 85 ° C Memory EEPROM -40 ° C 85 ° C Real-time Clock DS1302 -40 ° C 85 ° C Temperature Sensor PT303J2 -80 °C150 °C Pressure Sensor 24PCCFA6G -40 °C85 °C Humidity Sensor HS1101LF -60 °C140 °C Operating Temperatures

20. Mechanical Design (External) Hexagonal-shaped shell Hexagonal-shaped shell 10.7 cm on each side 10.7 cm on each side 21 cm in height 21 cm in height Dimensions subject to change Dimensions subject to change

21. Mechanical Design (Internal) Camera mounted in bottom corner of shell Camera mounted in bottom corner of shell BalloonSat attached to one of the walls BalloonSat attached to one of the walls Power systems attached to opposite wall Power systems attached to opposite wall 3 sensors burrowed in wall, exposed to outside 3 sensors burrowed in wall, exposed to outside 1 sensor(temperature) attached to guide ropes(1 foot above payload) 1 sensor(temperature) attached to guide ropes(1 foot above payload)

22. Risk Management RISKCONTIGENCYRESPONSIBILITY MECHANICAL The extended Temperature sensor breaks on landing Make sure sensor is secureDean/Ravneet ELECTRICAL Sensor fails during flight Test all sensors before flightAli/Brock Camera dies during flight Check battery pack sauter before flight Ali/Brock GENERAL Wrong sensor orderCheck model number before ordering Dean/Brock