1. Brandon Robinson Danut Tabacaru Victor Ho Autonomous Spacecraft Impact Monitoring Critical design review Autonomous Spacecraft Impact Monitoring Critical design review

2. Project overview Test plate set up with strain gauges and transducers Primary Objective: Impact force magnitude and direction detection Secondary Objective: Damage detection and analysis

3. Budget update *Denotes total cost including items purchased using OCE and in-house funding.

4. Hardware update (1) Test Plate and Frame Coordinates marked off on test plate surface Frame has been attached and bolted on securely Routing holes drilled in frame Test Plate and Frame

5. Hardware update (2) Strain Gauges and Wiring All 16 gauges are glued to the test plate Strain gauges wired to junction using thin strain gauge wire Shielded triple wire use from junction to data acquisition module Test Plate with Strain Gauges Attached and Wired

6. Hardware update (3) Transducers Pulsing Circuit Nothing Changed Pulsing Circuit

7. software update (1) Software Calibration Completed Generates Coefficients Least Squares Force & Position Completed Outputs Force and Position (Demo) Least Squares Transducers Remainder of Time Software GUIs

8. software update (2) Calibration Force & Position

9. Calibration Force measuring device used to manually apply forces 121 Points to Calibrate Forces between 26N-70N used Measurements taken at least 5 times each Force Measurement Device used for Calibration

10. Modeling update ANSYS 10.0 Analytical model using FEM Educational version Limited nodes and elements Provide a theoretical estimate of the strain at each gauge Test plate modeled in ANSYS

11. Obstacles and solutions Strain gauge wiring change Repeated calibration to improve results Calibration in stable temperature environment

12. Milestone update

13. Thank you