The electric drive control system of corner reflectors of the spacecraft interferometer

Бібліографічні деталі
Parent link:MATEC Web of Conferences
Vol. 102 : Space Engineering.— 2017.— [01026, 4 p.]
Співавтор: Национальный исследовательский Томский политехнический университет (ТПУ) Институт неразрушающего контроля (ИНК) Кафедра физических методов и приборов контроля качества (ФМПК)
Інші автори: Langraf S. V. Sergey Vladimirovich, Bunkov D. S. Dmitry Sergeevich, Odnokopylov I. G. Ivan Georgievich, Galtseva (Gal’tseva) O. V. Olga Valerievna
Резюме:Title screen
This paper presents the electric drive control system of corner reflectors of the infrared Fourier transform spectrometer for meteorological satellite. Limited-swing brushless DC motor with a torsional bearing is used as a drive motor. Stringent requirements are imposed to the drive control system for stabilization of moving speed of the reflectors while obtaining the interferogram and for limitation of the reverse time. Research of influence of torsion on steady-state error of speed and ways of its compensation is conducted. The obtained results are consistent with the simulation results of the drive. It is shown that the developed drive is operable in a spacecraft system.
Опубліковано: 2017
Предмети:
Онлайн доступ:http://dx.doi.org/10.1051/matecconf/201710201026
http://earchive.tpu.ru/handle/11683/37972
Формат: Електронний ресурс Частина з книги
KOHA link:https://koha.lib.tpu.ru/cgi-bin/koha/opac-detail.pl?biblionumber=654199
Опис
Резюме:Title screen
This paper presents the electric drive control system of corner reflectors of the infrared Fourier transform spectrometer for meteorological satellite. Limited-swing brushless DC motor with a torsional bearing is used as a drive motor. Stringent requirements are imposed to the drive control system for stabilization of moving speed of the reflectors while obtaining the interferogram and for limitation of the reverse time. Research of influence of torsion on steady-state error of speed and ways of its compensation is conducted. The obtained results are consistent with the simulation results of the drive. It is shown that the developed drive is operable in a spacecraft system.
DOI:10.1051/matecconf/201710201026