Abstract
Composite ultra-thin boom can be folded elastically. Moreover, such booms are able to self-deploy by releasing stored strain energy, which can be applied in deployable antenna, solar sail, and optical telescopes. Surrogate models for imperfection-sensitive quantities of interest and multi-objective optimization are developed for the design of a new N-shape cross-section composite ultra-thin deployable boom. The proposed optimal design method integrates four general steps: (1) design of experiments, wherein the sampling designs of the N boom are created on the basis of the two-factor five-level full factorial design of experiments method; (2) efficient computational analyses of each design sample, wherein the post-buckling behavior of the N boom are analyzed under three different axial directions using nonlinear finite element ABAQUS/Explicit solver; (3) establishing the surrogate models of bending stiffness around the x-and yaxes and torsional stiffness around the z-axis by response surface method (RSM); (4) performing the multi-objective optimization design using modified non-dominated sorting genetic algorithm to realize the optimal design. The bending stiffness around the x-and yaxes and the torsional stiffness around the z-axis are set as the objectives, mass is set as the constraint, and the bonded web height and the central angle of the middle tape spring of the N boom are set as the variables. The typical surrogate modeling method can be applied to different problems in structural and material design.
Highlights
Deployable structures, such as solar sails, antennae and optical telescopes, have been essential for space applications because of the limited volume of launching vehicles and the large-scale operating requirements in space
The proposed N deployable boom concept consisted of three tape springs, wherein the middle tape spring had two circumscribed circles and two adjacent tape springs that bonded along one longitudinal edge of the C shapes
The surrogate models for imperfection-sensitive quantities of interest of bending stiffness and torsional stiffness were derived from the quartic polynomials on the basis of response surface (RS) method
Summary
Deployable structures, such as solar sails, antennae and optical telescopes, have been essential for space applications because of the limited volume of launching vehicles and the large-scale operating requirements in space. H. Yang et al.: Design of a New N-Shape Composite Ultra-Thin Deployable Boom in the Post-Buckling Range for deployable booms was predicted [17]. The bending and torsional behaviors of the TRAC booms were studied using numerical analysis and experimental testing [20]. This work aims to propose a new N-shape cross section (N) boom and to assess structural bending and torsional stiffness throughout the entire post-buckling process around the three axes. The N composite ultra-thin deployable boom, which has a configuration similar to that of the TRAC boom, consists of three tape springs. The structural bending and torsional stiffness throughout the entire post-buckling process around the three axes should be analyzed to increase the capacity of the N boom in deploying state.
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