Parameter optimization for torsion spring of deployable solar array system with multiple clearance joints considering rigid–flexible coupling dynamics

Li, Yuanyuan; Li, Meng; Liu, Yuanyuan; Geng, Xinyu; Cui, Chengbo

doi:10.1016/j.cja.2021.03.033

Cited by 24 publications

(5 citation statements)

References 46 publications

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“…Dou and Zhou [18] developed a drop-deployment process for folding solar-powered UAVs based on Lagrange's equation and identified differences between flexible and rigid bodies during deployment. Li et al [19] studied the sensitivity of design parameters of the solar panels of satellite folding array PV cell deployment mechanism and analyzed the effects of locking time, stabilization time, contact force, and clearance on the rigid-flexible coupled system from the perspective of multibody dynamics.…”

Section: Introductionmentioning

confidence: 99%

Comparative Study and Airspeed Sensitivity Analysis of Full-Wing Solar-Powered UAVs Using Rigid-Body, Multibody, and Rigid-Flexible Combo Models

Guo,

Mu,

Zhou

et al. 2024

International Journal of Aerospace Engineering

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Solar-powered UAVs are characterized by large-scale, lightweight, and low airspeed, and changes in airspeed lead to wing deformation or stalling, which can easily induce serious flight accidents. A single dynamic model cannot accurately describe this feature, and this airspeed sensitivity can only be analyzed by integrating rigid-body, multirigid-body, and rigid-flexible combo models. This paper proposes a dynamic analysis method for a mixture of rigid-body, multirigid-body, and rigid-flexible combo models, considering the applicable airspeed ranges, computational costs, and structural deformation assumptions of the three models and comparing the differences of modes and responses at different airspeeds, and quantitatively analyzes the effects of airspeed on the motion, deformation, and coupling. The results show that appropriate increase of airspeed is beneficial to the stability of large-scale lightweight platforms, but when it is increased to more than two times the cruise speed, the structural deformation is coupled with the flight dynamic modes, leading to the deterioration of the overall dynamic response. Finally, a mixture of the three models at different airspeeds is proposed, which is necessary for future ultralarge-scale solar-powered UAVs.

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Section: Introductionmentioning

confidence: 99%

Comparative Study and Airspeed Sensitivity Analysis of Full-Wing Solar-Powered UAVs Using Rigid-Body, Multibody, and Rigid-Flexible Combo Models

Guo,

Mu,

Zhou

et al. 2024

International Journal of Aerospace Engineering

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“…Therefore, the deployable mechanism for space applications has gradually become the focus of research [1]. A lot of work has been executed on mechanism design [2][3][4] and dynamic characteristics [5][6][7]. The focus is on deployable antennae [8,9] and spatial multi closed-loop linkage.…”

Section: Introductionmentioning

confidence: 99%

Development and Rotation Characteristics Analysis of a Large-Scale Deployable Arm

et al. 2023

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In the spin-off acceleration stage during high-speed rotation in space, the deployable arm of the space gravity simulation device must withstand a large axial centrifugal force and a driving torque. In this paper, a large-scale high-speed rotating deployable arm is proposed, and the relevant characteristics during the rotation process are analyzed. A new driving mode of towed deployment is proposed that can lead to the rapid and efficient deployment of a large-scale deployable arm. First, an optimized configuration of a deployable arm is proposed. Second, the deployment driving process of the deployable arm under several different drag driving modes is simulated and analyzed, and a comparative analysis is performed to select a simple and reliable drag deployment driving scheme. Then, the effects of various disturbances on the posture of the deployable arm during the rotation process are explored, guiding the posture control of the deployable arm. Finally, a 10 m four-unit prototype is developed for the stiffness and rotation tests, which verify that the theoretical analysis in this paper is correct.

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“…Chu et al 16 applied a genetic algorithm to ensure that each cable achieves the required tension and effectively avoided the problem of nonconvergence. Li et al 17 adopted a hierarchical optimisation strategy based on an adaptive simulated annealing algorithm and a nondominated sorting genetic algorithm for solar array systems with gap joints to eliminate gross errors caused by nonlinear and nonsmooth mechanical properties. McAdams and Li 18 proposed a genetic algorithm to develop an origami structure with the best geometric, functional and foldable properties for incorporating the final shape design into the computational origami design and optimisation process.…”

Section: Introductionmentioning

confidence: 99%

Optimisation design of a large space cable-pole tensioned parabolic cylindrical antenna mechanism

Zhu,

Shi,

Fan

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part C:

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The cable-strut structure optimisation of a large space cable-strut tensioned parabolic cylindrical antenna is studied. Firstly, the deployment mechanism is designed, and the degree of freedom and kinematics analysis of the mechanism are conducted. Secondly, a complete tension cable configuration with 58 tension cables in 24 categories is established on the basis of the structural characteristics and constraints. A configuration optimisation design method based on the influence coefficient of comprehensive stiffness is proposed. A less tensioned cable optimisation configuration with better static and dynamic stiffness performance is established on the basis of the fully tensioned cable configuration and using the proposed method, and the stiffness characteristics of the configuration are verified through the analysis of an example. Lastly, a mathematical surrogate model between the designed angle and length parameters of the reflector rod system and the fundamental frequency of the antenna is established using the response surface method, and the optimal solution of the reflector rod system is obtained by a genetic algorithm. The effectiveness of the optimisation is verified by finite element modelling and simulation analysis. This study provides a basis and reference for the structural dynamic modelling, characteristic analysis and optimal design of a large space cable-strut tensioned parabolic cylindrical antenna.

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Parameter optimization for torsion spring of deployable solar array system with multiple clearance joints considering rigid–flexible coupling dynamics

Cited by 24 publications

References 46 publications

Comparative Study and Airspeed Sensitivity Analysis of Full-Wing Solar-Powered UAVs Using Rigid-Body, Multibody, and Rigid-Flexible Combo Models

Comparative Study and Airspeed Sensitivity Analysis of Full-Wing Solar-Powered UAVs Using Rigid-Body, Multibody, and Rigid-Flexible Combo Models

Development and Rotation Characteristics Analysis of a Large-Scale Deployable Arm

Optimisation design of a large space cable-pole tensioned parabolic cylindrical antenna mechanism

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