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 Phase 3: Damage repair

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

Hardware update (1) Test Plate 14.5” x 14.5” dimensions 1/16” thickness Industrial grade 6061 aluminum Frame Aluminum pieces cut from dry-wall frames Frame attached to edges of plate so that a 12” x 12” area of the plate is left unsupported Test Plate and Frame

Hardware update (2) Strain Gauges Vishay 240UZ Low Cost 0.24” gauge length 4 per side layout – 16 in total Data Acquisition NI cDAQ-9174 chassis NI channel quarter-bridge strain gauge modules Vishay 240UZ

Hardware update (3) Transducers Pulsing Circuit Amplification 555 Timer Transformer Coil Voltage Ladder Pulse 555 Timer Class C Amp Class A Amp Amplified Pulse Pulsing Circuit

Hardware update (3)

software update Software MATLAB LabView Measurement Studio NI Measurement Studio Included drivers GUI, Analysis, etc. Visual C++ Modular Calibration Force and Position Block Diagrams

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

Risk management Project is spaced out into phases Phase I – Essential Phase II – Possible Phase III – If time permits Accuracy can be reduced Budget remaining

Milestone update

Thank you