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CanSat Interim Presentation II

CanSat Interim Presentation II. Samuel Rustan (EE) Yasmin Belhaj (ME) Andrew Guerr (CE) Andrew Grant (ME) Maxwell Sandler  (ME) Technical Advisors: Dr. David Cartes , Dr. Victor DeBrunner Course Instructors: Dr. Kamal Amin, Dr. Michael Frank ME Senior Design Team #18

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CanSat Interim Presentation II

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  1. CanSat Interim Presentation II Samuel Rustan (EE) YasminBelhaj (ME) Andrew Guerr (CE) Andrew Grant (ME) Maxwell Sandler (ME) Technical Advisors: Dr. David Cartes, Dr. Victor DeBrunner Course Instructors: Dr. Kamal Amin, Dr. Michael Frank ME Senior Design Team #18 ECE Senior Design Team #10 March 19, 2013

  2. Overview • Mission Recap • Finalized design and configurations • Fabrication Update • Electronics and Integration • Software development • Timeline and Budget • Tasks remaining Presenter: Samuel Rustan

  3. CanSat Project Overview • Design a container/payload system to be launched via rocket and develop autonomous descent control strategy to safely land CanSat • Container will house payload for initial descent • Payload will house electronic components and “sensor” (egg) • Telemetry data will be transmitted for flight duration • Sample Design Parameters and Restrictions • Size • Mass • Material • Descent Control Strategy Presenter: Samuel Rustan

  4. CanSat Project Overview Presenter: Samuel Rustan

  5. Previous Benchmarks • Finalized design for launch and descent • Compared passive braking method • Parachute vs. Streamer • Determined egg protection strategy • Iterative trials, various materials • Selectable Objective – Impact Force Sensor • Procured and tested electronic components • Delivered successful Preliminary Design Review (PDR) • Feedback: Scored 92% from AIAA/NASA Panel Presenter: Samuel Rustan

  6. Updated Launch Configuration Parachute Separation Mechanism Electronic Components Shelving Container Aero-braking Structure Payload Egg Compartment

  7. Updated Descent Configuration Torsion Spring Torque of 2.14 [in*lb]

  8. Fabrication Update • Parts have been procured and machined • Dimensions finalized to fit in rocket bay • Mass budget concerns (underweight)

  9. Fabrication Update • Top Left: Side View with Aerobrake deployed • Top Right: Aerobrak cut-away with antenna • Bottom Left: Top View with aero-brake deployed Presenter: Andrew Grant

  10. Release Mechanism Prototype Presenter: Andrew Grant

  11. Sensor (Egg) Protection • Polystyrene beads chosen from experiment • 1050 [kg/m3] Presenter: Andrew Grant

  12. Integration of Electrical Components • Each sensor on separate circuit board • #2 & #1 screws used to attach to plastic platforms • Glue to secure • Rubber footpads used to separate components from platform • Holes will be drilled in platform to provide wire bundle channel • (not shown) Presenter: Samuel Rustan

  13. Configuration of Telemetry Components CanSat Onboard Electronics To Antenna USB XBEE Antenna Ground Station Note: USB cables for programming only Presenter: Samuel Rustan

  14. Integration of Electrical Components Accelerometer Press/Temp GPS Module Microcontroller Battery XBEE Radio Presenter: Samuel Rustan

  15. Communications: Range Tests • Results • 2.4 GHz, 60 mW • Insufficient Range • Improper Test • Link Margin: 20 [dB] • Receiver Sensitivity: 100 [dB] • Received Power: 80 [dB] • Link Margin = 100 – 80 • Enough margin to maintain link (accord. To Digi RF Tech) • Proposed Solutions • Increase Gain of Receiver Ant • Digi Int’l RF Engineer • Proper range test (5 [m] above any obstacle) Presenter: Samuel Rustan

  16. Ground Control Software Flight Software • Working “Beta” version • Migration is “so far good” • No noticeable difference between the Uno and Mini functionality Ground Station Software • Version 5, working “alpha” version • Written in Python • Both Mac (shown) & PC versions • Not yet fully integrated with all subsystems Presenter: Andrew Guerr

  17. Flight Software • Current • Working “Beta” version • Transmits telemetry data packet • Integrated with altimeter and GPS • Errors reading GPS data • Needs • Integration with accelerometer, voltage divider, buzzer, and motor • Support for user entry of altitude correction data • Altitude smoothing Presenter: Andrew Guerr

  18. Updated Gantt

  19. Funding / Project Budget

  20. Looking Forward • Parachute attachment • Complete fabrication of CanSat • Emphasis on Open House Display • Test separation mechanism and aero-braking deployment using altimeter • Complete microcontroller migration • Complete range testing • Demonstrate Telemetry with FSW & GCSW • Prepare User Manual • Present AIAA Critical Design Review (Mar 29th) • Prepare Open House Demonstration (April 18th)

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