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NMT Space Launch Spring 2013

NMT Space Launch Spring 2013. 20 km & up -55 o C to -46 o C. Stratosphere. 3-4 Hours. Balloon Release. Chute Deploy. Joseph MacGillivray (Lead), Levi Magnuson, Lloyd Puckett, Karen Quezada, Sam Chesebrough , Jaclene Gutierrez, and Cameron Lucas. Tropopause 11 to 20 km -55 o C.

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NMT Space Launch Spring 2013

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  1. NMT Space Launch Spring 2013 • 20 km & up • -55oC to -46oC • Stratosphere 3-4Hours Balloon Release Chute Deploy Joseph MacGillivray (Lead), Levi Magnuson, Lloyd Puckett, Karen Quezada, Sam Chesebrough, JacleneGutierrez, and Cameron Lucas • Tropopause • 11 to 20 km • -55oC Ascent (5 m/s, 1 Hr) Descent (7 m/s, 0.4 Hr) • Troposhpere • 0 to 11 km • 15oC to -55oC • Background and Objective • Purpose • Study the little-known effects of the atmosphere and space on piezoelectric sensorsusing structural health monitoring (SHM) techniques. • Importance • SHM could significantly reduce cost of satellite launches by reducing pre-flight testing time and localized damage detection of loose bolts and cracks. • Solution • The team will launch SHM experiments on High-Altitude Balloon and Sub-Orbital Rocket. This proof-of-concept flight will pave the way for SHM integration on commercial and defense satellites. • Data will be collected before, during, and after flights to ascertain the structural state of several key points on the experiment. Design Results – Balloon Launch Release Landing • Wireless • Wireless proof-of-concept success • Impedance • Microcontroller issue prevented useful data • WID3 unfit for continued use • Wave Propagation • Successful proof-of-concept; confirms known physics • Figure 5 shows Temperature dependence for pulse-speed propagation. These shifts will need to be accounted for in the suborbital data analysis. Wireless Hub Plate Impedance Hub Plate Impedance Sensors Wave Sensor Plate Wave Hub Plate Figures 5: Life-Cycle Wave Propagation Data Figure 3: Prototype Canister Design • Wireless • Collect Wireless • Four wireless strain gauges • Sensors read/report strain, temperature, and pressure changes during launch • Conclusion • Previous Work – Design & Prototype Complete • Objective – Codify Space Environment Effects • Product Specifications – Survive & Collect Data • Program Plan – Suborbital Launch in Spring • Results – Structure, Wireless, and SHM • Impedance • Collect Sensor Data • Corresponds to sensor’s resistance to motion • Data plots Impedance (Ohms) vs. Frequency (kHz) Figure 1: Balloon Launch Profile (Left), Rocket Launch Profile (Right) Previous Work • Background • Precursor Experiment launched Spring 2011 • Collected data demonstrated that quantified space environment effects SHM data. • Further analysis was required, spawning this year’s experiment. • Wave Propagation • Collect Signal Data • Corresponds to wave propagation of signal (change) • Data plots Voltage (V) vs. Time (µsec) • Future Work • March 2013 • Professional Journal Paper Review • Final Data Analysis - Balloon • April 2013 • Sub-Orbital Rocket Launch • Preliminary Data Analysis - Rocket Figure 2: Previous Experiment • Acknowledgements: Dr. Zagrai, Chris White, Ben Cooper, Jon Schlavin Figures 4: Sensor Plate, Metis HubTouch, Sensor Data

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