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The concept of space solar power satellite (SSPS) is an advanced system for collecting solar energy in space and transmitting it wirelessly to earth. However, due to the long service life, in-orbit damage may occur in the structural system of SSPS. Therefore, sensor placement layouts for structural health monitoring should be firstly considered in this concept. In this paper, based on genetic algorithm, an optimal sensor placement method for deployable antenna module health monitoring in SSPS is proposed. According to the characteristics of the deployable antenna module, the designs of sensor placement are listed. Furthermore, based on effective independence method and effective interval index, a combined fitness function is defined to maximize linear independence in targeted modes while simultaneously avoiding redundant information at nearby positions. In addition, by considering the reliability of sensors located at deployable mechanisms, another fitness function is constituted. Moreover, the solution process of optimal sensor placement by using genetic algorithm is clearly demonstrated. At last, a numerical example about the sensor placement layout in a deployable antenna module of SSPS is presented, which by synthetically considering all the above mentioned performances. All results can illustrate the effectiveness and feasibility of the proposed sensor placement method in SSPS. [ABSTRACT FROM AUTHOR]

This study aims to propose a static and dynamic evaluation for 160 m solar sail by comparing the results obtained using an 8 m scalable principle prototype. Based on the model updating and parameter modification theories, the finite element analysis (FEA) model of the 8 m prototype is constructed, and results are obtained to validate the effectiveness of the proposed numerical simulation method. The static deformation is compared with experimental data with errors in acceptable limits. Moreover, the numerical simulation and analysis method for wrinkle patterns are also applied based on the structural buckling theory and linear combination technology. The calculated indices of peak-valley value, half-wavelength, and wrinkle number are compared with the prototype experiment. By validating the numerical simulation approach in the 8 m prototype, the same analysis method can be directly extended in the application of the 160 m solar sail. The deformation response of the overall system and wrinkle patterns of the 160 m sail are provided. The transient dynamic responses of acceleration, displacement, and vibration amplitudes are also simulated and compared using different parameters. All the results obtained herein provide valuable suggestions and reference to large solar sail design in the future. • The simulation and analysis method for solar sail is validated by scalable prototype. • Wrinkles of sail are simulated based on buckling theory and validated by experiment. • Static deformation, stress and wrinkles are analyzed to evaluate 160 m sail concept. • Transient dynamic responses of 160 m sail with different parameters are provided. [ABSTRACT FROM AUTHOR]

Highlights • Limitation of the previous models and superiority of three-dimensional redundancy elimination model (3DREM) are proposed. • The proposed 3DREM for OSP can consider nearest neighbor nodes and sensor distribution. • By using weighting factor and normalization, the optimization problem is solved by genetic algorithm. • The first numerical example can be regarded as a benchmark structure to compare redundancy models in future studies. • The performance of sensor layout is improved and evaluated by five criteria. Abstract Spatial lattice structures are widely applied in engineering fields attributed to their superiorities in weight and reasonable stress. It is essential to select the best sensor placement layout for structural health monitoring and safety purposes, yet it is neither realistic nor efficient to place sensors in every location possible on the structure. To meet the strong requirements for optimal sensor placement in spatial lattice structure, this paper aims to investigate a combined objective function based on effective independence method and three dimensional redundancy elimination model to balance between optimal sensor placement performance and elimination in redundancy. To eliminate redundant information and resource waste caused by the clustered sensor distribution, the three-dimensional redundancy elimination model is constructed with the consideration of nearer nodes and overall sensor distribution ranges in three-dimensional cases. In addition, the combined function is constructed by giving the two component functions equal significance using weighting factors and normalization, and solved by genetic algorithm. Finally, the proposed method for spatial lattice structure is supported by three numerical examples including a simple lattice structure, a ground spatial truss structure and a space docking modular in space solar power satellite. [ABSTRACT FROM AUTHOR]