Flexible spacecraft attitude maneuver by application of sliding mode control

Bang, Hyochoong; Ha, Cheolkeun; Kim, Jin Hyoung

doi:10.1016/j.actaastro.2005.04.009

Cited by 86 publications

(48 citation statements)

References 13 publications

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“…[8][9][10] In [8], the equations of the three-dimensional motion of a satellite are obtained, aiding the Lagrange method, using just one mode and ignoring torsion and in-plane bending of panels. In [9], the mode summation procedure is used to simulate solar panels, and 12 bending modes have been taken into account, thereby improving the simulation.…”

Section: Introductionmentioning

confidence: 99%

An accurate and simple model for flexible satellites for three-dimensional studies

2010

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In this paper, an accurate and simple model of a satellite with two flexible solar panels for three-dimensional dynamic studies is proposed and compared with other models. In the proposed model, each solar panel is assumed to be rigid and attached to the satellite body via a simple hinge, a torsional spring, and a torsional damper. Kane's method is utilized to derive the equations of motion. The model of flexible satellite with the assumption of Euler-Bernoulli beam for the solar panels, generally used in the literature, has been introduced for comparison. A comprehensive model of flexible satellite, considering solar panels as flexible and finite element panels, has been provided in ADAMS environment as a reference when comparing the two mentioned models. The Euler-Bernoulli model does not appropriately simulate the three-dimensional motion of satellite. Conversely, the hinged, rigid-panel model proposed in this paper provides suitable results in both two-and three-dimensional maneuvers.

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Section: Introductionmentioning

confidence: 99%

An accurate and simple model for flexible satellites for three-dimensional studies

2010

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“…Thus, deformations of solar panels should be discretized with finite element method (FEM) [4] or modal approach using mode shapes [5][6][7][8]. The FEM model is not convenient for designing control system, because its degree of freedom is usually too large [9].…”

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confidence: 99%

Studies on global analytical mode for a three-axis attitude stabilized spacecraft by using the Rayleigh–Ritz method

2016

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With extending the Rayleigh-Ritz procedure to study the hub-plate system, the characteristics of global analytical modes are addressed for a typical rigid-flexible coupling dynamic system, i.e., a threeaxis attitude stabilized spacecraft installed with a pair of solar arrays. The displacement field of the solar arrays is expressed as a series of admissible functions which is a set of characteristic orthogonal polynomials generated directly by employing Gram-Schmidt process. The rigid body motion of spacecraft is represented by the product of constant and generalized coordinate. Then, through Rayleigh-Ritz procedure, the eigenvalue equation of the three-axis attitude stabilized spacecraft installed with a pair of solar arrays is derived. Solving this eigenvalue equation, the frequencies and analytical expressions of global modes for the flexible spacecraft are obtained. To validate the present analysis, comparisons between the results of the present method and ANSYS software are performed and very good agreement is achieved. The convergence studies demonstrate the high accuracy, excellent convergence and high efficiency of the present approach. Finally, the method is applied to study the characteristics of global modes of the flexible spacecraft.

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“…Thus, it is very challenging to design an attitude controller for flexible spacecraft to achieve rapid and precise maneuver performance. Various control methods have been applied to deal with this problem, such as passivity-based control [6,9], sliding mode control (SMC) [1,11,13], active disturbance rejection control [3,4], backstepping control [14] and so forth [7,19,31]. Although these methods have provided for sufficient reliable results, they can only ensure the asymptotic convergence.…”

Section: Introductionmentioning

confidence: 99%

Disturbance observer-based second order sliding mode attitude tracking control for flexible spacecraft

Pukdeboon¹,

Jitpattanakul²

2017

Kybernetika

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Flexible spacecraft attitude maneuver by application of sliding mode control

Cited by 86 publications

References 13 publications

An accurate and simple model for flexible satellites for three-dimensional studies

An accurate and simple model for flexible satellites for three-dimensional studies

Studies on global analytical mode for a three-axis attitude stabilized spacecraft by using the Rayleigh–Ritz method

Disturbance observer-based second order sliding mode attitude tracking control for flexible spacecraft

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