TY - GEN
T1 - Athermalization of deformable reflector’s actuators for radio astronomy satellites
AU - Kashiyama, Reo
AU - Sakamoto, Hiraku
AU - Okuma, Masaaki
AU - Tanaka, Hiroaki
AU - Ishimura, Kosei
N1 - Funding Information:
This work is supported by ISAS/JAXA Strategic Research and Development Grant, and JSPS KAKENHI Grant Number JP26249131. The authors deeply appreciate Nozomu Kogiso, Osaka Prefecture University, for research coordination and various advices.
Publisher Copyright:
© 2018 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 2018
Y1 - 2018
N2 - This paper develops an athermalization method to cancel the mismatch of the coefficient of thermal expansion (CTE) that exists in active control mechanisms, through analysis, prototyping, and tests. Essentially, the CTE mismatch between piezoceramics and the other structures made of super invar is cancelled by combing with another metallic part. In addition, this paper clarifies the mechanism of thermal deformation caused by inner structure of a piezoelectric stack actuator. It shows in both finite-element analysis and tests that the CTE mismatch cancellation is affected by the dimension tolerance of the inner structure, but successfully adjustable by the proposed methods. Moreover, the high thermal sensitivity of the actuator is exploited to propose another type of smart actuator, which uses active thermal deformation. This alternative approach is also evaluated through analysis, prototyping, and tests.
AB - This paper develops an athermalization method to cancel the mismatch of the coefficient of thermal expansion (CTE) that exists in active control mechanisms, through analysis, prototyping, and tests. Essentially, the CTE mismatch between piezoceramics and the other structures made of super invar is cancelled by combing with another metallic part. In addition, this paper clarifies the mechanism of thermal deformation caused by inner structure of a piezoelectric stack actuator. It shows in both finite-element analysis and tests that the CTE mismatch cancellation is affected by the dimension tolerance of the inner structure, but successfully adjustable by the proposed methods. Moreover, the high thermal sensitivity of the actuator is exploited to propose another type of smart actuator, which uses active thermal deformation. This alternative approach is also evaluated through analysis, prototyping, and tests.
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U2 - 10.2514/6.2018-1199
DO - 10.2514/6.2018-1199
M3 - Conference contribution
AN - SCOPUS:85141651411
SN - 9781624105302
T3 - AIAA Spacecraft Structures Conference, 2018
BT - AIAA Spacecraft Structures
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Spacecraft Structures Conference, 2018
Y2 - 8 January 2018 through 12 January 2018
ER -