Structural Optimization And Simulation Analysis Of Reusable Aircraft Hatch

When an aircraft takes off,takes off or enters orbit,it will be subject to complex effects such as high temperature,corrosion,vibration and shock,and there are high requirements for the accuracy and stability of the aircraft’s motion.Aiming at the design optimization problem of the hatch structure and material parameters,in this paper,the layout optimization and lightweight design of the key parts of the hatch structure are carried out,the optimization of the hatch composite material parameters,and the research on the load force of the rigid-flexible coupling structure.The main research content as follows:Firstly,studying the overall design of the reusable aircraft hatch structure.In view of the technical requirements and design principles of the aircraft hatch structure,this chapter adopts conceptual design methods and refers to relevant domestic and foreign hatch mechanism schemes to determine the three-dimensional model of the hatch mechanism;for the hatch to work in a complex outer space environment,The hatch should be repeatedly extended and retracted,to resist damage and high temperature resistance.The motion characteristics of the hatch and the retractable mechanism are analyzed,and then the repeatable retractable hatch mechanism is designed to meet the requirements of use.Secondly,studying the optimization of the hinge layout of the aircraft hatch structure and the lightweight of the hinge structure.In view of the problems of heavy weight,material redundancy and unreasonable layout in the structure of the conceptual design,this chapter uses the Topology Optimization solver to optimize the structural topology and lightweight design of the model designed in the previous chapter based on the SIMP variable density OC optimization criterion method.Under the condition of meeting the design requirements,a more reasonable material distribution of the hinge,a reasonable layout of the hinge,and a reduction in mass are obtained.After checking the optimized structure,the optimized model is obtained,and the strength and stiffness of the structure are improved.The validity of the topology optimization method is comfirmed,and it provides reference for designers.Then,studying the optimization of the composite material layup of the aircraft hatch skin.In view of the problems of the aircraft hatch working in a complex environment,corrosion resistance and high temperature resistance,the skin is laminated with carbon fiber composite material.This chapter combines the finite element method with the optimization design idea,and based on the laminate theory,the Ansys Workbench Design Exploration module is used as a tool for parameter optimization of the ply angle of the composite skin.Through analysis and calculation,the best ply angle of the cabin door skin is obtained,the stiffness and stiffness of the aircraft hatch have important guiding significance to the reasonable design of the aircraft hatch.Finally,studying the load distribution of the rigid-flexible structure of the aircraft hatch.Aiming at the load distribution problem of the hinge on the ground and under microgravity conditions.This chapter takes the hinge structure of composite hatch as the research object,adopts the replacement principle of stiffness,etc.,uses the Ansys software Apdl module to export the hinge modal neutral file,imports it into Adams co-simulation.The simulation results show that because the hinge structure is a statically indeterminate structure,uneven load distribution and redundant constraints of the hinge appear during simulation.The bearing connection method can solve the simulation problem.Rigid-flexible coupling structure compared with a pure rigid structure,the load distribution conforms to the actual load distribution;The dynamic analysis of rigid-flexible coupling structure can reflect the force of parts more truly.