Analytical Synthesis of Stabilization Laws for Spacecraft Orbit Attitude Using Information on an Angle and the Full Vector of Angular Velocity
- Авторы: Zubov N.E.1, Mikrin E.A.2, Ryabchenko V.N.1, Sorokin I.V.2
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Учреждения:
- Bauman Moscow State Technical University
- Korolev Rocket and Space Corporation Energiya
- Выпуск: Том 61, № 2 (2018)
- Страницы: 201-211
- Раздел: Flight Dynamics and Control of Flight Vehicles
- URL: https://journals.rcsi.science/1068-7998/article/view/230486
- DOI: https://doi.org/10.3103/S1068799818020083
- ID: 230486
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Аннотация
The problem of stabilizing the spacecraft orbit attitude was solved analytically for the sixth order model of its rotary motion with the use of the output feedback control synthesis that is based on decomposition of a control object. Numerical simulation data are presented.
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Об авторах
N. Zubov
Bauman Moscow State Technical University
Автор, ответственный за переписку.
Email: nik.zubov@gmail.com
Россия, ul. 2-ya Baumanskaya 5, Moscow, 105005
E. Mikrin
Korolev Rocket and Space Corporation Energiya
Email: nik.zubov@gmail.com
Россия, ul. Lenina 4a, Korolev, Moskow region, 141070
V. Ryabchenko
Bauman Moscow State Technical University
Email: nik.zubov@gmail.com
Россия, ul. 2-ya Baumanskaya 5, Moscow, 105005
I. Sorokin
Korolev Rocket and Space Corporation Energiya
Email: nik.zubov@gmail.com
Россия, ul. Lenina 4a, Korolev, Moskow region, 141070
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