Parametric Configuration Model For Of Civil Jet And Integrated Aerodynamic/structural Design Of Wings

This research work aims at solving two problems - the parametric CAD model of aircraft configuration and integrated aerodynamic/structural design of wings for civil jets. For aircraft conceptual design the parametric CAD model of configuration is helpful in speeding up configuration design, and also provides the basis for aircraft multidisciplinary design optimization (MDO). The integrated aerodynamic/structural design method is proved to be a formal method for the rational tradeoff between aerodynamic and structural requirements of wings.This research work mainly includes the following several aspects:1) A parametric mathematical model for civil jets was proposed by using class function and shape function transformation method, which can be used to establish the parametric geometric models for the wing, tail, fuselage and nacelle configuration for civil jets. The geometric model for the fairings between the fuselage and wing is also studied. The positions of aircraft component are defined. The parametric geometric models for entire aircraft configuration are established.2) Based on the parametric geometric models of civil jets, the software for the automatic generation of parametric CAD model is developed by using the CATIA software API method. Given the parameters from aircraft conceptual design, the aircraft configuration CAD model can be generated quickly by the software.3) By using the multidisciplinary design optimization methods, a procedure of the wing aerodynamic/structure multidisciplinary design optimization is proposed. The each step implementing the procedure is presented, and computation environment for the wing aerodynamic/structure multidisciplinary design optimization is established with software iSIGHT.The typical application examples indicates that the software, which is developed based on parametric geometric models for civil jets, can generate quickly the three dimensional CAD model of civil jets configuration and the CAD model has the good precision. This research work provides the basis for aircraft multidisciplinary design optimization (MDO). The optimal sets for the lift-drag ratio and the structural weight can be obtained by using the wing aerodynamic/structure multidisciplinary design optimization method and its computation environment, which means this method can be considered as a formal method for the rational tradeoff between aerodynamic and structural requirements of wings.