Active structural health monitoring during sub-orbital space flight

2012 ◽  
Vol 132 (3) ◽  
pp. 1964-1964
Author(s):  
Andrei N. Zagrai ◽  
William Reiser ◽  
Brandon Runnels ◽  
Chris White ◽  
Abraham Light-Marquez ◽  
...  
Keyword(s):  
Structural Health Monitoring ◽  
Health Monitoring ◽  
Space Flight ◽  
Structural Health ◽  
Orbital Space

Design, development, and assembly of sub-orbital space flight structural health monitoring experiment

2012 ◽  
Author(s):  
William Reiser ◽  
Brandon Runnels ◽  
Chris White ◽  
Abraham Light-Marquez ◽  
Andrei Zagrai ◽  
...  
Keyword(s):  
Structural Health Monitoring ◽  
Health Monitoring ◽  
Space Flight ◽  
Design Development ◽  
Structural Health ◽  
Orbital Space

Design, Development, and Assembly of Space Flight Structural Health Monitoring Experiment

2012 ◽  
Author(s):  
David Siler ◽  
Ben Cooper ◽  
Chris White ◽  
Stephen Marinsek ◽  
Andrei Zagrai ◽  
...  
Keyword(s):  
Wave Propagation ◽  
Structural Health Monitoring ◽  
Data Acquisition ◽  
Health Monitoring ◽  
Space Flight ◽  
Design Development ◽  
Active Sensors ◽  
Electromechanical Impedance ◽  
Structural Health ◽  
Propagation Experiment

The paper presents the design, development, and assembly of Structural Health Monitoring (SHM) experiments intended to be launch in space on a sub-orbital rocket flight as well as a high altitude balloon flight. The experiments designed investigate the use of both piezoelectric sensing hardware in a wave propagation experiment and piezoelectric wafer active sensors (PWAS) in an electromechanical impedance experiment as active elements of spacecraft SHM systems. The list of PWAS experiments includes a bolted-joint test and an experiment to monitor PWAS condition during spaceflight. Electromechanical impedances of piezoelectric sensors will be recorded in-flight at varying input frequencies using an onboard data acquisition system. The wave propagation experiment will utilize the sensing hardware of the Metis Design MD7 Digital SHM system. The payload will employ a triggering system that will begin experiment data acquisition upon sufficient saturation of g-loading. The experiment designs must be able to withstand the harsh environment of space, intense vibrations from the rocket launch, and large shock loading upon re-entry. The paper discusses issues encountered during design, development, and assembly of the payload and aspects central to successful demonstration of the SHM system during both the sub-orbital space flight and balloon launch.

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