Minimization of Vibration of Spacecraft Appendages During Shape Control Using Smart Structures

Chen²

2022

AEAT

Purpose This paper aims to present a multi-axis actuating approach to attenuate the bending and torsional vibration of the solar array through the reaction wheel (RW) actuators. Design/methodology/approach The motion equation of the solar array with the RW actuators is derived in modal coordinates for controller design. The reaction torques, induced by the speed change of the RW actuators, are controlled for vibration attenuation through the constraints on the actuators’ rotating speed. The proposed control approach is firstly verified with numerical simulation on the finite element model of a full-scale solar array. Experimental study of a simplified elastic plate model is subsequently performed for feasibility and validity investigation. Findings Both the numerical and experimental studies demonstrated the success of adopting RW as the actuator. Results from numerical simulation reveal that the vibration response peak can be reduced by 80% with 2% of mass increase by using the RW actuators. Practical implications It is demonstrated that the multi-axis actuating method using RW actuators has a great potential in vibration attenuation of the multi-panel deployable solar array. Originality/value An approach to reduce bending and torsional vibration of solar array based on RW actuators is investigated. Theoretical analysis, numerical simulation and experimental study are conducted to demonstrate the validity of the proposed vibration attenuation approach and its potential application in the spacecraft design.

Section: Introductionmentioning

confidence: 99%

Bending and torsional vibration attenuation of multi-panel deployable solar array using reaction wheel actuators

Chen²

2022

AEAT

“…The dynamic shape control of piezo-actuated structures has also received extensive attentions (Irschik, 2002). The improved dynamic shape control of the flexible structures in open loop can be achieved using flatness-based design methodology (Kugi et al, 2006; Schröck et al, 2013) or Pontryagin’s principle (Kalaycioglu and Silva, 2000). However, compared with many flexible structures, the important coupling effect between structure and aerodynamics loads must be considered in modeling, analysis, and control of morphing wings (Bae et al, 2005; Li et al, 2016).…”

Section: Introductionmentioning

confidence: 99%

“…The process of static shape control estimates the final voltage values for the actuators to reach a required target wing shape. However, the voltage profiles, that is, variation of voltage with respect to time, for each actuator may not be obtained because the static shape control process provides only the initial and final static voltage values (Kalaycioglu and Silva, 2000). Some simple voltage profiles including step and ramp profiles may be applied in practice, and those profiles could excite the low structural modes because of the flexibility necessary to achieve the morphing control.…”

Section: Introductionmentioning

confidence: 99%

Dynamic shape control of piezocomposite-actuated morphing wings with vibration suppression

Journal of Intelligent Material Systems and Structures

Zhou

Xun

et al. 2017

Aerodynamic properties and aeroelastic responses of morphing wings can be improved via active shape control using piezoelectric actuators. In this article, a type of piezocomposite material called macro-fiber composite is used for actuation to achieve shape control of the morphing wing. This study focuses on the vibration suppression of the wing during dynamic morphing motion in open-loop architecture. The aeroelastic model is established using finite element method and Theodorsen unsteady aerodynamic loads. Because the arbitrary selection of any admissible control voltage profiles will cause vibrations of the wing structure and fluctuations in aerodynamic lift, a dynamic shape control approach is presented to optimize the voltage profiles for the actuators. A proof-of-concept simulation is presented for a scaled high-aspect-ratio wing. The results show that continuous, smooth morphing motion with gentle aeroelastic responses can be realized by applying the optimum voltage profiles. The dynamic shape control performance of the morphing wing can be improved compared with step and ramp voltage profiles.

“…In general, owing to increased requirement for weight savings, aerospace structures are becoming more flexible, whereas their performance requirements are becoming more stringent. Active vibration control using smart piezoelectric materials has drawn widespread interest in enhancing performance and control characteristics of the flexible structures (Kalaycioglu and Silva, 2000). Piezocomposite materials are advanced piezoelectric devices with effective material properties, good conformability, and anisotropic actuation effects (Bent et al, 1995; Ray and Reddy, 2013).…”

Section: Introductionmentioning

confidence: 99%

Optimal unimorph and bimorph configurations of piezocomposite actuators for bending and twisting vibration control of plate structures

Journal of Intelligent Material Systems and Structures

Zhou

et al. 2017

Optimal configuration of anisotropic piezocomposite actuators is investigated for vibration control of flexible structures. Actuation effects of the actuators in unimorph and antisymmetric angle-ply bimorph configurations are analyzed. Dynamic equations of the piezo-actuated plate are established using finite element method. The locations and lead zirconate titanate fiber orientations of actuators are optimized simultaneously to improve vibration control performance of a plate. The optimization criterion is presented based on controllability Gramian matrix of the system. The properties of macro-fiber composite are used in the simulations of the actuators. The optimal unimorph and bimorph configurations of actuators are presented for three cases: bending control, twisting control, and coupled bending–twisting control. The results indicate that both optimal locations and fiber orientations are different for bending control and twisting control. A trade-off between control authority for bending and torsional modes can be found in coupled bending–twisting control. The actuators should be placed in the regions of high average strain of the interested modes with appropriate fiber orientations. Special piezocomposite actuators with optimal fiber orientations can be used to achieve improved coupled bending–twisting vibration control performance.