Algorithms of Stabilization of a Spacecraft with Flexible Elements

Ovchinnikov, M Y; Tkachev, S. S.; Shestopyorov, Aleksey Igorevich

doi:10.1134/s1064230719030146

Cited by 8 publications

(3 citation statements)

References 13 publications

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“…Numerous control design methods have been adapted and applied for attitude control of flexible spacecrafts. First of all, this concerns classical methods, such as proportionalintegral-derivative (PID) controller [3], a linear quadratic regulator (LQR) [5] and sliding mode (SM) control [6]. In [7] attitude trajectory, the tracking problem is solved by means of LMI-based gain-scheduled H-infinity control.…”

Section: Introductionmentioning

confidence: 99%

“…Hence, a reduced (rigid) model of the spacecraft is used to obtain an attitude control law. In this context the following methods are tested: an inertia-free nonlinear attitude control algorithm derived by Sanyal et al [30] and implemented by Posani et al [24]; LQR [5] as well as SDRE techniques; the SDRE algorithm tuned by an input-shaping technique to reduce undesired elastic oscillations [31]. In the present paper, the LQR-PSO strategy is presented.…”

Section: Introductionmentioning

confidence: 99%

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Attitude Stabilization of a Satellite with Large Flexible Elements Using On-Board Actuators Only

Tkachev,

Shestoperov,

Okhitina

et al. 2023

Mathematics

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Attitude control of a satellite with three flexible elements is considered. Control torque is developed by a set of reaction wheels, which are installed on the central hub of the satellite. The flexible elements are large, so the control torque constraints must be taken into account. In the paper, a control algorithm based on a linear-quadratic regulator is studied. The asymptotic stability of this control is shown. The choice of the control parameters is based on the closed form solution of the corresponding algebraic Riccati equation, which is supplemented by the linear matrix inequality. To increase the convergence rate, particle swarm optimization is used to tune the control parameters.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Attitude Stabilization of a Satellite with Large Flexible Elements Using On-Board Actuators Only

Tkachev,

Shestoperov,

Okhitina

et al. 2023

Mathematics

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show abstract

“…In particular, the relevance of this problem now is increasing due to the broad development of multifunctional satellites, which are built on the base of constructional schemes of nanosatellites with passive and active attitude control. 5–21 Modern small satellites are not inferior in their functionality to the old large spacecraft due to the miniaturization of electronic components. Moreover, the launch of small satellites is significantly cheaper compared to the heavy ones.…”

Section: Introductionmentioning

confidence: 99%

Attitude control of nanosatellite with single thruster using relative displacements of movable unit

Doroshin

Eremenko

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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The attitude dynamics of a nanosatellite (NS) with one movable unit changing its angular position relative to a main body of the nanosatellite is considered. This relative movability of the unit can be implemented with the help of flexible rods of variable length connecting the unit with the main body. Change of the relative position of the movable unit shifts the center of mass of the entire mechanical system. The NS has a single jet engine rigidly mounted into the NS main body. The shift of the mass center creates an arm of the jet-engine thrust and a corresponding control torque. Schemes to control the attitude dynamics of the satellite using the movability of its unit are developed, using both the torque from the engine and inertia change.

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