Brandon Robinson Danut Tabacaru Victor Ho Autonomous Spacecraft Impact Monitoring Preliminary design presentation Autonomous Spacecraft Impact Monitoring Preliminary design presentation

Project overview Test plate set up with strain gauges and transducers Phase 1: Impact force magnitude and direction detection Phase 2: Damage detection and analysis

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

Hardware update (1) Test Plate Test surface has been sanded down for strain gauge placement Holes have been drilled for frame attachment Frame Holes drilled and sanded for plate attachment Test Plate and Frame

Hardware update (2) Strain Gauges All 16 gauges are glued to the test plate 4 per side 2” spacing between each gauge 1” spacing between edge boundary and strain gauge Test Plate with Strain Gauges Attached

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

software update (1) Software Calibration Completed Testing Required Input, GUI Least Squares Force & Position Idea/Math Least Squares Transducers Driver Problems Calibration GUI

software update (2) Least Squares

Modeling update ANSYS 10.0 Analytical model using FEM Modeled using Aluminum 6061 properties Shell 8node93 Provide a baseline for physical model Test plate modeled in ANSYS

Issues to Address Stage 3 Dropped to put focus on Stage 1 and Stage 2 Influence of Pressure Difference in Space Environment Duration of Impact Forces

Risk management Accuracy can be reduced if very high accuracy is not obtainable Budget remaining in case of additional parts required

Milestone update

Thank you