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12 June 2000 Thermal and mechanical characterization of NASA high-displacement actuators for satellite instrumentation
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NASA's High Displacement Actuators (HDAs) are being examined for several potential aerospace applications. In order to determine if these HDAs are suitable for these applications, the strain must be determined as a function of applied voltage and stress over the range of temperature required for the environment of space. Additionally, the variability between HDAs of the same design must be determined to establish their performance average and standard deviation. Towards this end, a matched set of rectangular HDAs were fabricated and characterize to determine their on-center displacement. These actuators were run at a 1 Hz frequency using peak-to-peak voltages from 100 to 800 volts with a maximum negative voltage of -150 volts. The test temperature ranged from -101 to 66 degrees C at 28 degrees C intervals. Loads ranging form 50g to 1450g were line loaded on center to observe the effects of strain on displacement. After preliminary characterization, these HDAs were incorporated into a prototype linear motor drive system for satellite instrumentation. This paper describes the fabrication, test methodology and the resulting performance of these HDAs as well as the linear piezo motor.
© (2000) COPYRIGHT Society of Photo-Optical Instrumentation Engineers (SPIE). Downloading of the abstract is permitted for personal use only.
Robert G. Bryant, S. A. Evans, E. R. Long Jr., and Robert Lee Fox "Thermal and mechanical characterization of NASA high-displacement actuators for satellite instrumentation", Proc. SPIE 3991, Smart Structures and Materials 2000: Industrial and Commercial Applications of Smart Structures Technologies, (12 June 2000);

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