| With the rapid development in the field of spaceflight and the gradual deepening of space exploration in unknown areas,reusable orbiter has become a key research object at home and abroad.In this thesis,the overall structural design and structural layout optimization of the hatch deployable mechanism are studied,including the design,material selection and configuration selection of the hatch deployable mechanism,the optimization of the parameters of the deployable mechanism,the optimization of the structural layout of the hatch reinforcement and center lock,and the analysis of the rigid-flexible coupling dynamics of the hatch deployable mechanism,and the main research contents are as follows.Firstly,the overall design of the hatch deployable mechanism of the orbiting vehicle is studied,and the overall structural design and material selection of the hatch deployable mechanism are completed under the requirement of relevant indexes and design principles.For the selection of the configuration of the deployable mechanism,this thesis makes a second-level fuzzy comprehensive evaluation of the configuration scheme based on the hierarchical analysis method,and the best configuration scheme is selected.After determining the design of the deployable mechanism,a parametric model of the hatch deployable mechanism is established based on the analysis of the mechanism motion principle,and the optimal structural parameters are obtained by taking the hatch rotation angle as the optimization target under the constraints of rod length and transmission angle.Secondly,for the structural layout optimization of the hatch reinforcement and lock point,a joint simulation optimization method based on MATLAB and ANSYS is proposed to solve the problem that the discrete variables of the layout and the continuous variables of the position are coupled with each other,which leads to the unsatisfactory optimization effect.The command flow text of the simplified finite element model with parameterization is created by using ANSYS parameterization language,and the genetic algorithm written by MATLAB is used as the main program to call ANSYS to solve and output the results to the text,and the text is used as the data interface to realize data transfer and automate the optimization procedure.Under this optimization method,the number and location of layouts are used as design variables to optimize the design with the objective of minimum mass or minimum number of masses under the constraints of fundamental frequency and deformation.The research results prove that the optimization method has good applicability and certain reference value.Then,to address the problem of uneven hinge load distribution due to the invariant force on the rigid body during the unfolding process of the hatch deployable mechanism,a method based on the modal neutrality file is adopted to realize the flexibilization of the rigid body,the hinge is flexibilized by this method,and a rigidflexible coupling virtual prototype model is established to simulate and analyze the hinge load distribution while extracting the driving moment curve to provide reference for the selection of experimental equipment under the premise of ensuring the correctness of modal neutral file information.The results show that the load distribution of the hinges under the rigid-flexible coupling structure is uniform,The magnitude of the load on the hinge in the special position is consistent with the theoretical calculated value.Finally,the hatch deployable mechanism measurement test bench was built,and the test data were compared with the simulation data for analysis.The results showed that the two data had good consistency in terms of trend and magnitude,which verified that the structural design parameters met the technical requirements and the simulation model was correct. |
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