Vibration Suppression of Flexible Spacecraft During Attitude Maneuvers

Hu, Qinglei

doi:10.2514/1.12967

Cited by 102 publications

(53 citation statements)

References 9 publications

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“…Based on the sliding mode output feedback control, controllers for maneuvering the single-axis flexible spacecraft have been designed in Refs. [8][9][10][11][12]. Nevertheless, when applied to threeaxis stabilized spacecraft, the approaches need to be properly modified by ignoring some nonlinear coupling terms.…”

Section: Introductionmentioning

confidence: 99%

“…[19,20] for details. For the second problem, a wide range of approaches have been proposed for using piezoelectric material to actively control the vibration of flexible structures, such as Strain Rate Feedback (SRF) control [21,22], positive position feedback (PPF) control [8][9][10], modal velocity feedback [23,24], linear quadratic regulator (LQR) control [25], and so on. Among them, the SRF works by feeding the structural velocity coordinate information directly to a compensator.…”

Section: Introductionmentioning

confidence: 99%

“…However, in most of the previous studies concerning SMC, it is assumed that the spacecraft is rigid and no flexible mode actions are considered. For the flexible spacecraft model, finite mathematical discretization was used to design sliding mode controllers and there have been significant research efforts for the general feedback attitude control of flexible spacecraft [8][9][10][11][12][13][14][15][16]. Based on the sliding mode output feedback control, controllers for maneuvering the single-axis flexible spacecraft have been designed in Refs.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Sliding mode maneuvering control and active vibration damping of three-axis stabilized flexible spacecraft with actuator dynamics

2007

Nonlinear Dyn

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This paper presents a dual-stage control system design method for the three-axis-rotational maneuver control and vibration stabilization of a spacecraft with flexible appendages embedded with piezoceramics as sensor and actuator. In this design approach, the attitude control system and vibration suppression were designed separately using a lower order model. Based on the sliding mode control (SMC) theory, a discontinuous attitude control law in the form of the input voltage of the reaction wheel is derived to control the orientation of the spacecraft actuated by the reaction wheel, in which the reaction wheel dynamics is also considered from the real applications point of view. The asymptotic stability is shown using Lyapunov analysis. Furthermore, an adaptive version of the proposed attitude control law is also designed for adapting the unknown upper bounds of the lumped disturbance so that the limitation of knowing the bound of the disturbance in advance is released. In addition, the concept of varying the width of boundary layer instead of a fixed one is also employed to eliminate the chattering and improve the pointing precision as well. For actively suppressing the induced vibration, modal velocity feedback and strain rate feedback control methods are presented Q. Hu ( ) and compared by using piezoelectric materials as additional sensors and actuators bonded on the surface of the flexible appendages. Numerical simulations are performed to show that rotational maneuver and vibration suppression are accomplished in spite of the presence of disturbance torque and parameter uncertainty.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Sliding mode maneuvering control and active vibration damping of three-axis stabilized flexible spacecraft with actuator dynamics

2007

Nonlinear Dyn

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show abstract

“…However, in most of the previous studies concerning SMC, it is assumed that the spacecraft is rigid and no flexible mode actions are considered. For the flexible spacecraft model, finite mathematical discretization was used to design sliding mode controllers and there have been significant research efforts for the general feedback attitude control of flexible spacecraft [10][11][12][13][14][15][16]. Based on output feedback control concept, controllers for maneuvering the single-axis flexible spacecraft have been designed in [10][11][12][13][14].…”

Section: Introductionmentioning

confidence: 99%

Robust adaptive sliding mode attitude maneuvering and vibration damping of three-axis-stabilized flexible spacecraft with actuator saturation limits

2008

Nonlinear Dyn

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130

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This paper presents a dual-stage control system design method for flexible spacecraft attitude maneuvering control by use of on-off thrusters and active vibration suppression by embedded smart material as actuator. As a stepping stone, an adaptive sliding mode controller with the assumption of knowing the upper bounds of the lumped perturbation is designed that ensures exponential convergence or uniform ultimate boundedness (UUB) of the attitude control system in the presence of bounded parameter variation/disturbances and control input saturation as well. Then this adaptive controller is redesigned such that the need for knowing the upper bound in advance is eliminated. Lyapunov analysis shows that this modified adaptive controller can also guarantee the exponential convergence or UUB of the system. For actively suppressing the induced vibration, linear quadratic regulator (LQR) based positive position feedback control method is presented. Numerical simulations are performed to show that rotational maneuver and vibration suppression are accomplished in spite of the presence of disturbance torque/parameter uncertainty and saturation input.

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“…However, as seen from simulation results chattering occurs in control action. A comparison between linear and sliding mode controllers with reaction wheels is studied [17] where only small angle orientations are considered. Designed sliding mode controller stabilizes spacecraft attitude dynamics 30 times faster than output feedback controller with reaction wheels.…”

Section: Introductionmentioning

confidence: 99%