Estimating the springback compensation of the profile is one of the key technologies for the digital manufacturing of aircraft. This paper takes the L profile and the T profile as the research object. Finite element method is used to simulate the forming process of profile recesses and predict the springback compensation of the profile recesses, The validity of the finite element method is verified by the experiment of profile recesses forming. The relationship between the die reduction and the target recess depth is also analyzed. The results show that: The springback of the area near the transition zone is large, and the farther the area is, the smaller the springback is; The springback value of L profile after straight recess is larger than that of T profile after straight recess. The finite element simulation results are reasonable and can meet the need of springback prediction, The finite element simulation and experiment method proposed in this paper can be used to guide the production practice, it can provide a reference basis for the springback compensation of the die and reduce the manufacturing cost.
In this paper, the optimization , numerical simulation and experimental verification of a composite box wave spring shock absorber are carried out. In the process of design, the position of the layer, the direction of the layer and the thickness of the layer are optimized, and three feasible design schemes are given in combination with the actual manufacturing factors. Using carbon brazing prepreg, three kinds of test pieces were manufactured by molding method and verified by static test. The three schemes are evaluated with the displacement mass ratio as the evaluation standard. The results show that the optimized scheme of the full 0 degree gradation layer has the lightest quality and maximum deformation margin while satisfying the required loading requirements, and the difference between the test value and the simulation value is not very large, which shows that the optimization process has a certain reference significance.
Use the aeroengine turbine blade as a carrier,the collaborative design method of turbine blade with single data source (SDS) model was investigated using model based definition(MBD) technology. The integrated program team and the unified information platform were set up. A complete set of collaborative design method with MBD was established. The method includes making turbine blade parallel design and manufacture processing with SDS model, confirming technical details of collaborative design,standardizing production process control, stipulating dimensioning method of simplified SDS model with PMI in UG. The blades designed with SDS model have come into use and show good performance,the digitization of aviation technology was improved.
From the deficiency of the front scholar’s research on micro-honeycomb core, the paper presented the Y mode, then derived the governing equations and boundary conditions of the cell walls through principle of minimum potential energy. The strain energy density function of the Y mode constructed by using the modified couple stress theory which contains one material length scale parameter is capable to represent the scale effect. The paper deduced the in-plane equivalent parameters of micro-honeycomb core by the equality of strain energy. A titanium honeycomb core was taken as the example. The results of two models indicate that the in-plane elasticity modulus of micro-positive hexagon core are isotropic and bigger than that of macro-core.
The key route of dynamic load cascading base on virtual durable road is proposed, the road model is a high-precision virtual road which is the same as the actual road after laser scanning, combine with the precise vehicle dynamics model and FTire model, this method can obtain dynamic load of parts which are very close to the real car, and dynamic load was used to analyze and optimize the durability of auto parts. The sensitivity factors that affect the simulation precision are identified by comparing the vehicle test with the virtual simulation of the forces and moments on wheel center, and more accurate dynamic load is obtained through virtual simulation. Finally, with the chassis sub-frame as example, the fatigue durability analysis was carried out with the dynamic load of test and simulation, the results show that the dynamic load cascading method based on virtual durable road model has better application foreground，according to different enterprise test standard and requirements of quality assurance，the fatigue life of parts are evaluated by using appropriate safety factors. The application of virtual durable road can make the fatigue-life prediction of parts in advance, improve design maturity, lower development costs, reducetest risk
A feasible, efficient and economical method for opening design of a composite wing girder web plate of a civil aircraft is summarized. Firstly, according to the design principle of the composite laminate, the layering sequence and layering ratio of the wing beam are determined, and then the girder web and girder flange are laid as a whole. Then, by using the classical laminate theory to calculate the equivalent material property of the wing beam, the method of calculating the equivalent elastic modulus of the laminate with different thickness is deduced. Finally, the influence of the open shape and Angle on the strength of the composite wing girder web under shear loading is analyzed. The research method not only can solve the problem of specific engineering design, and summarizes the design process, put forward a set of feasible, economic and efficient design method of composite material mouth shape, has a certain universality, can effectively reduce development costs and shorten the development cycle, at the same time also can be applied to other types of composite laminate open problems.
