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Published byEmery Young Modified over 9 years ago
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Brandon Robinson Danut Tabacaru Victor Ho Autonomous Spacecraft Impact Monitoring Preliminary design presentation Autonomous Spacecraft Impact Monitoring Preliminary design presentation
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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
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Budget update *Denotes total cost including items purchased using OCE and in-house funding.
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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
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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 9235 8-channel quarter-bridge strain gauge modules Vishay 240UZ
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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
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Hardware update (3)
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software update Software MATLAB LabView Measurement Studio NI Measurement Studio Included drivers GUI, Analysis, etc. Visual C++ Modular Calibration Force and Position Block Diagrams
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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
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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
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Milestone update
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Thank you
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