Cansat 2008: University of New Hampshire Final Presentation

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    Cansat 2008: University of New Hampshire Final Presentation - Presentation Transcript

    1. CANSAT Final Presentation June 15 th 2008
    2. WildCatSat Team
    3. Outline
      • Design Overview
      • Raw Data Plots
      • Processed/Analyzed Data Plots
      • Outcome of Flight Ops/Failure Analysis
      • Comparison of Actual CONOPS to Planned CONOPS
    4. Mechanical Design Overview
      • System Bus:
      • ABS Plastic
      • Rapid Prototype using 3-D Printer
      • Recovery System:
      • Octagonal Parachute
        • Rip-Stop Nylon
        • Area: 1.016 m 2
      • Nylon Cord
      • Up-righting System:
      • Hinged side doors
      • Torsion springs provide force to open doors
      • Pin connected to servo motor holds doors in place/releases doors
      • Parachute Release System:
      • Pin attached to side door
      • Pin holds parachute to bus while doors closed
      • Total Measured Mass: 470g
      Mechanical Design Overview
    5. Structural Drawings
    6. Electrical System Diagram Processor Pressure Sensor Transceiver Buzzer Servo Transceiver Computer
    7. Electrical Design Overview
      • Sensors:
      • SCP1000 Barometric pressure and temp. sensor
      • Microprocessor:
      • Atmel ATMega168
      • Transmitter:
      • Aerocomm AC4790-1000M
      • Battery
      • 11.1V 800 mAh Li-Poly
      • 12.26V Initial, 12.19V After Mission: 0.7V Drop
      • Ground Station Computer:
      • HP Pavilion N5425
      • Ground Station Receiver:
      • Aerocomm ConnexLink 4790
      • Ground Station Antenna:
      • External high gain omni-directional antenna
      Ground Station
    8. Raw Data Plots
    9. Processed Data Note: Matlab truncation of LS digit = loss in accuracy 0 20 40 60 80 100 120 140 160 180 200 8.4 8.6 8.8 9 9.2 x 10 4 Mission Time (s) Pressure (Pa) 0 20 40 60 80 100 120 140 160 180 200 -200 0 200 400 600 800 Mission Time (s) Altitude (m)
    10. Processed Data (cont.) (Processed with Matlab’s ‘Diff’ and ‘Filter’ functions and window size of 10) From VTI Tech: “Assumed constant temp. gradient of dT/dH from 1976 US Standard Atmosphere” H = 30°C/(6.5°C/km)*(1-(P/101325Pa)^0.19 Reference: VTI Technologies
    11. Flight Operations
      • Altitude Transmission: Success
      • Average Descent Rate: 3.3767 m/s
      • Descent Time: (1340s-1160s)/60 ~3 min
    12. Flight Operations (cont.)
      • Recovery: Success
      • Up-righting System: Success
      • Ground Temperature (bonus): Not Met
      From: 34.48.097N 101.35.244W To: 34.47.88N 101.35.562W ~1.28km Lateral Distance Traveled Reference: http://www.movable-type.co.uk/scripts/latlong.html
      • Pattern Loss ~30%
      • Ground Absorption
      • Terrain
      • Ground Station Antenna height
      a) Elev. Pattern b) Azimuth Pattern Reference: Aerocomm Corp. Failure Analysis
      • Satellite activated
      • Satellite loaded into rocket
      • Satellite takes initial pressure reading
      • Rocket launches
      • Satellite detects pressure change, starts sending
      • pressure/altitude data
      • Satellite ejects from rocket
      • Parachute deploys, slowing descent
      • Satellite descends at less than 4.6 m/s
      • Satellite continues to transmit data
      • Satellite lands
      • Doors open up-righting satellite
      • Parachute released
      • Buzzer activates
      • Ground temperature reading and transmission
      • Data transmission stops
      Preparation Launch Deployment Descent Recovery CONOPS Comparison
        • UNH ECE Dept.
        • UNH ME Dept.
      WildCatSat Sponsors
      • Jon Arlington at
        • Orbital Sciences Corp.
      • The Byrd Family
      Todd Gross Professor and Chair May-Win Thein Associate Professor
    13. Questions? Professor May-Win Thein Project Advisor Ph.D Mechanical Engineering [email_address] Robert Terry Team Leader Electrical Engineer [email_address]

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