Email this article Analytical Synthesis of Stabilization Laws for Spacecraft Orbit Attitude Using Information on an Angle and the Full Vector of Angular Velocity
- Authors: Zubov N.E.1, Mikrin E.A.2, Ryabchenko V.N.1, Sorokin I.V.2
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Affiliations:
- Bauman Moscow State Technical University
- Korolev Rocket and Space Corporation Energiya
- Issue: Vol 61, No 2 (2018)
- Pages: 201-211
- Section: Flight Dynamics and Control of Flight Vehicles
- URL: https://journal-vniispk.ru/1068-7998/article/view/230486
- DOI: https://doi.org/10.3103/S1068799818020083
- ID: 230486
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Abstract
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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About the authors
N. E. Zubov
Bauman Moscow State Technical University
Author for correspondence.
Email: nik.zubov@gmail.com
Russian Federation, ul. 2-ya Baumanskaya 5, Moscow, 105005
E. A. Mikrin
Korolev Rocket and Space Corporation Energiya
Email: nik.zubov@gmail.com
Russian Federation, ul. Lenina 4a, Korolev, Moskow region, 141070
V. N. Ryabchenko
Bauman Moscow State Technical University
Email: nik.zubov@gmail.com
Russian Federation, ul. 2-ya Baumanskaya 5, Moscow, 105005
I. V. Sorokin
Korolev Rocket and Space Corporation Energiya
Email: nik.zubov@gmail.com
Russian Federation, ul. Lenina 4a, Korolev, Moskow region, 141070
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