DemoSat V

1. DemoSat V Critical Design Review Metropolitan State College of Denver April 13, 2007

2. Three missions in one payload • FieldSat and GPSSat will be incorporated into one assembly. • LandSat will be the main body for all three missions.

3. Sat System Requirements • The payload module must weigh less than 1.5kg • Record orientation and vibration in the form of data and store it on large-capacity media • Record and verify GPS • Land upright deploy a camera and capture a photo of the landing site

4. Mission Descriptions • Field Sat • To record on-board orientation and vibration during flight • GPS Sat • Verify GPS position accuracy during flight • LAND Sat • Develop novel methods for upright landing

5. Mission Goals and Nasa Benefit • To develop and integrate new attitude and orientation designs • To implement new upright landing technologies • Verify GPS accuracy to track vehicle landings

6. Field/GPSSat System Overview • The central component of this package is a microcontroller • The Field and GPS subsystems communicate with the microcontroller • Raw data from the subsystems will be recorded on flash memory for later analysis

7. Field/GPSSat System Interfaces Accelerometers SD Cards Gyros MicroController GPS Camera Altitude Sensor Deployment latch Batteries Temp sensor

8. Field/GPS Sat Subsystem Overview • Field subsystem contains an inertial measurement unit • Three gyroscopes to measure rotation • Accelerometers to measure linear acceleration • Altimeter • GPS receiver

9. Field Subsystem Schematic IMU Microcontroller Altimeter Accelerometers Gyroscopes

10. Field Subsystem Interface • Inputs: • none • Outputs: • Altitude • Acceleration in three dimensions • Rotation of three axes

11. Land Sat Subsystem Overview • Landing subsystem contain the deployment latch, and imaging system • The imaging system will consist of a micro camera that records landing imagery to storage media • The deployment latch will be a solenoid.

12. LandSat System Requirements Component: • Camera unit • Battery (onboard) • Flash Drive (micro-controller) • Thermal Protection • Electric resistive heating • Impact Protection • Exo-skeleton

13. LandSat Subsystem Schematic Land Deployment Microcontroller Camera Deployment SD Card Storage

14. Land Subsystem Interface • Inputs: • Deployment signal from microcontroller. • Outputs: • Camera Deployment, photo storage

15. Mass Budget • Sensors                         20 g • Camera 10 g         • Micro-controller board < 100 g         • Secure Digital board (2)    < 50 g         • Secure Digital card (2)    2 g         • Battery/other power source 100 g • Heating, insulation         100 g • Case 300 g • Waterproofing/Body Panels 300g • Estimated mass       1100 g

16. Field/GPS Sat Monetary Budget • Gyro Sensors (3) Donated • Micro-controller Board $ 100.00 • SD Board (2) $ 30.00 • SD Cards (2) $ 28.00 • Accelerometers (1) $ 50.00 • Altimeter Donated • GPS Unit $ 100.00 • Camera $ 75.00 • Incidentals* $ 400.00 *includes all necessary hardware Total $ 850.00

17. Project Organization Professor Keith Norwood Faculty Advisor Matt Hanley Team Captain GPS Sat Land Sat Field Sat Evan Spitler Devlin Thyne Matt Hoffman Vincent Yates David Fifield Jason Igo Jamal Givens

18. Pre- CDR February Establish Team March Research and Development April Design and Cost Analysis Post-CDR May Finalize design and initial Prototyping June Acquisition of required materials July Construct and test August Launch and Compile Data Schedule

19. Any Questions?