Analytical Synthesis of Stabilization Laws for Spacecraft Orbit Attitude Using Information on an Angle and the Full Vector of Angular Velocity

N. E. Zubov; E. A. Mikrin; V. N. Ryabchenko; I. V. Sorokin

doi:10.3103/S1068799818020083

Analytical Synthesis of Stabilization Laws for Spacecraft Orbit Attitude Using Information on an Angle and the Full Vector of Angular Velocity

Авторлар: Zubov N.E.¹, Mikrin E.A.², Ryabchenko V.N.¹, Sorokin I.V.²
Мекемелер:
1. Bauman Moscow State Technical University
2. Korolev Rocket and Space Corporation Energiya
Шығарылым: Том 61, № 2 (2018)
Беттер: 201-211
Бөлім: 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.