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DemoSat IV:

DemoSat IV:. RedRoverSat. Jaime Catchen, Chris Homolac, Emily Walters. August 9, 2006. University of Colorado at Boulder. Mission Statement & Goals:. Mission Timeline.

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DemoSat IV:

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  1. DemoSat IV: RedRoverSat Jaime Catchen, Chris Homolac, Emily Walters August 9, 2006 University of Colorado at Boulder

  2. Mission Statement & Goals: Mission Timeline RedRoverSat is an autonomous rover designed to measure wind speed and direction and the moisture of the soil at its landing site. This research hopes to be beneficial to understanding the objectives of the Astrobiology Field Laboratory. Launch Thermal system heats payload Payload lands C&DH senses landing After rover senses landing, rover detaches from flight line Rover moves four times in a pre-programmed path and stops for one minute to run experiments and record data Recovery

  3. Students working on the design of autonomous payloads with moving parts The rover will perform experiments similar to those that will be part of the Astrobiology Field Laboratory Benefits to NASA:

  4. Project Management: Project Management Jaime Catchen Science Chris Homolac – Wind Jenny O’Brien – Wind Emily Walters – Soil C&DH Jaime Catchen Chris Homolac Leon Slavkin Structures Rebekah Hanson Leon Slavkin Emily Walters Power/Thermal Chris Homolac Project start date: May 22, 2006

  5. Design: Structure

  6. Design: C&DH Atmega32 • 32 Kb programmable flash, 1 Kb EEPROM • 32 I/O pins • 8 analog inputs • Software in C programming language H-bridge Motor control

  7. Design: Landing Sensors Accelerometer checks stability of the rover every 30 seconds for 5 min. Temperature and/or Pressure Sensors confirm that rover is not at high altitude. Safety Timer ensures that rover does eventually deploy, no single point of failure. Control Timer 2:15 hours Safety Timer If >30 Minutes Accelerometer If Stable for 5 min No No Yes Yes Temperature Sensor If >16 C Pressure Sensor If > 83 kPa No Detach From Flight Line Yes

  8. Soil probe measures the voltage across the two metals Driven by servo Design: Science Wind Soil NiCr Wire Panel for Wire 1 Panel for Wire 2 Servo mount

  9. Power Lithium Polymer [11.1V 2100 mAh] Heaters/Main systems Lithium 9V Battery Deployment Nichrome Design: Power & Thermal Thermal • Series of (6) 5W 4Ω Ceramic Resistors • Foam/Aluminum tape insulation • Thermostat Control Lithium 9V Battery/ Resistance Heater Lithium Polymer Power Supply with insulation and heaters

  10. Total Cost $730.00 Design: Budgets Total Mass 1658 g Thermal Thermal

  11. Testing

  12. Results • Recovery • Both wheels came off during landing • Flight line Nichrome was broken • Flight line torn • Servos tried to deploy science experiments in proper orientation • Soil probe bent, wind panel bent • Wind Nichrome broken Motor Shaft • Post Flight • No data stored to EEPROM • Battery discharged to 8v • H-bridge, battery, right motor, heaters, servos, AVR still in working order • Motor gears stripped Wheel Hub

  13. Improvements and Lessons Learned • Improvements to the Design • Put wheels inside frame • Write a byte to EEPROM periodically throughout flight code • Put experiments inside structure or make rover a vessel for any experiment • Mechanical detachment mechanism instead of Nichrome • Lessons Learned • No test like the actual flight • Dealing with unpredictability of flight circumstances and landing site

  14. DemoSat IV: Questions? University of Colorado at Boulder

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