Research On Dynamic Mechanical Response Of Developable Carbon Fiber Composite Structure

The "SIASAIL-I" solar sail developed by the Shenyang Institute of Automation,Chinese Academy of Sciences is equipped with the Xiaoxiang-1 07 satellite of the Changsha Tianyi Research Institute,and has successfully verified a number of key technologies in orbit.This paper conducts research based on the key technical issues in the future development of the supporting structure of the "SIASAIL" series of solar sails.In view of the future development of the "SIASAIL" series of solar sails,the curling diameter of the deployable support structure must be small enough,and the problem of "blossoming" cannot occur during the deployment process,and it can be stably deployed in the space environment,and the solar sail service environment exists With a complicated time-temperature relationship.This paper designs and prepares a neutral stable composite material laminate structure,which is similar to the bistable composite material laminate structure in that both can be maintained in a fully curled and fully expanded state without external force stable.The difference between the two is that the neutral stable composite material laminate structure can also maintain a stable state when partially unfolded.Therefore,the neutral stable composite material laminate structure can overcome the large end impact when the bistable composite material laminate structure is deployed,which causes insufficient deployment stability and "bulging" phenomenon.Therefore,the neutral stable composite material laminated structure is more suitable as the supporting structure of the solar sail than the bistable composite material laminated structure.However,when performing missions,spacecraft are often exposed to high temperature and long-term load working environments,and the same is true for supporting structures.In order to meet the development needs of lightweight spacecraft,the support rod based on the neutral stable composite material laminated structure uses a resin material as the matrix material.This material will have a greater impact on the mechanical properties of the spacecraft in the working environment.The impact of this in turn affects the overall performance of the support structure.In summary,the main research work of this paper includes: deriving the classical laminate theory under the viscoelastic model,using the principle of minimum potential energy to obtain the necessary conditions for the existence of the bistable structure under the viscoelastic model and the necessary conditions for the existence of the neutral stable structure;Through the DMA experiment combined with the carbon fiber epoxy resin matrix composite material unit model,the numerical solution of the viscoelastic properties of the carbon fiber epoxy resin matrix composite material is obtained,the relationship between the crimp diameter and the carbon fiber angle is given,and the laying angle that meets the design conditions is found,through the combination of numerical analysis and finite element method,the optimal laying method of the neutral stable laminated structure is given;The neutral stable structure was prepared according to the design parameters,and the expansion experiment was carried out to analyze the ejection force and expansion force of the neutral stable laminated structure and the effect of long-term expansion on the neutral stable composite structure.In the end,this research successfully synthesized an unfolding and stable neutral stable structure through theoretical guidance design,gave the design parameters of the neutral stable structure,and confirmed that the neutral stable structure prepared can be derived from the theoretical model prediction.