Redesign Of Unmanned Aerial Vehicle Impeller Based On Reverse Engineering

The unmanned aerial vehicle(UAV) is one of the aero engine main parts which plays the role of energy conversion at work. UAV impeller design has been the difficulties to develop. Focus on the introduction of foreign advanced technology. At the same time, strengthen the digestive absorption and improve research and development ability. They are the main facing problems of UAV impeller design in our country. The use of reverse engineering technology to reconstruct, improve and optimize the impeller model is an effective means to achieve product innovation and redesign. Because UAV impeller working environment is very bad. Under the combined effect of centrifugal force and aerodynamic force, with pressure than speed and continuous improvement, requirements on the strength of the impeller is also more and more high. Structural optimization for the purpose of design has become more and more important. Therefore, this paper uses reverse engineering technology to realize the model reconstruction of the impeller entity, and the reconstruction of the impeller strength analysis and structural optimization to achieve the re design of the impeller. The main contents of this paper are as follows:1. The key technology of the UAV impeller reverse reconstruction is developed. Based on Geomagic studio, Imageware and UG software, extracting feature method is adopted to reconstruct the impeller model and the reverse reconstruction were studied. The technology includes UAV impeller data acquisition, data pretreatment, blade surface reconstruction, accuracy in detecting and fairing, and impeller reconstruction model of precision evaluation technology.2. Using the finite element analysis software ANSYS Workbench to analyze the static strength of the impeller model. According to the structure characteristics of the UAV impeller, the model of the impeller is simplified. Considering the influence of UAV impeller blade thickness and fillet size on strength, every kind of thickness and fillet composition analysis model and finite element model are established. Choose the original blade thickness to trial and judgment model accuracy. Through analyzing the static strength of the model, the maximum equivalent stress of the impeller model is obtained. And the position of the maximum deformation is obtained which provides the structure optimization data for the impeller.3. Based on ANSYS Workbench to optimize the structure of the impeller model. By using the parametric modeling function of Pro/E software, the parameters of the model are defined as the model parameters, and the optimization model of the parameters of the UAV is established. Taking the blade deformation, the maximum equivalent stress and the quality as the optimization objective, the Workbench finite element analysis was used to optimize the impeller. Obtain the optimum size of the impeller, and achieve the redesign of the impeller.