Coupled Dynamics Modeling And Experimental Study For Laminated Plate Or Beam Appendages With Large Angle Rotation

Composite materials compared to aluminum alloy,titanium alloy and other commonly used materials,own more excellent mechanical properties.Especially the laminated composite materials which are composed of high strength,high modulus fiber materials and high performance matrix resins have been widely used in space flight and aviation etc.With the development of space technology,the structural dimensions of flexible appendages attached to spacecraft become larger and larger.During the operation of the spacecraft,The coupling effect between large-scale motion of the composite laminates plate or beam appendages and its own elastic deformation movement bring vibration and coupling defor mation.The vibration and coupling deformation have a significant effect on the attitude movement of spacecraft.Therefore,the rigid-flexible coupling dynamics modeling of typical spacecraft with laminated plate or beam appendages in large angle rotation have been studied in this paperBased on higher-order shear deformation theory and Hamilton variational principle,this paper choose laminated plate or beam appendages in large angle rotation as study objects,the rigid-flexible coupling dynamic equations are established.By using the floating frame of reference formulation and the finite element method,the kinematic relationship and the elastic deformation of the laminated plate or beam is described.This model take the coupling between large overall motion of laminated composite plate or beam and its elastic deformation movement into consideration,as well as the laminated structures and the constitutive relation of laminated plate or beam.According to the numerical method,start from the rigid-flexible coupling dynamic model,the numerical simulation for laminated and none-laminated plate or beam undergoing large angle rotation is carried out.The influence of the laminated structures of the laminated plate or beam on the dynamic characteristics of the system is investigated.On the basis of these,the influence of laminated structure parameters,such as ply angle,ply thickness,ply sequence,and the influence of motion parameters,such as constrains driving and rotation angle,on the dynamic properties of the system are further discussed.The simulation results have validated that considering the laminated structures of the laminated composite appendages in this paper is necessary and the dynamics model established in this paper is right.In order to investigate the influence of the laminated structure of laminated plate appendages and rotational speed on the dynamic characteristics of the system the experiments verification of laminated composite plates in large angle rotation are performed.In these experiments,the angular acceleration of laminated composite plates is measured by piezoelectric accelerometer.Then,through comparing and anslysising the experiments results and simulation results,the nonlinear model builded in this paper is correct and universa l.Finally,summarize the whole research work and the conclusions are obtained.Meanwhile,the shortcomings of this study are presented and the prospect of the future research are proposed.