Research And Application Of Aerospace Vehicle MDO Process And Related Technologies

Aerospace vehicle design method plays an important role in increasingly intensive aerospace competition. Traditional design method handles the complex coupled interaction in aerospace vehicle design ineffectively and can not fulfill the target of"fast, good and economical". The MDO (Multidisciplinary Design Optimization) method handles the optimal design problem of coupled multidisciplinary system. It has very practical and important meaning to increase the aerospace vehicle design level. Aimed at increasing the aerospace vehicle design level, this thesis takes MDO process, the core of MDO, as main research object. Based on the systematic study of aerospace vehicle design problem, several optimization processes and related technologies, improvements are made to some optimization process and adapted to the requirements of computation and engineering practice of aerospace vehicle design with related technologies. According to the further consideration of aerospace vehicle development trend, these research productions are utilized in the subsonic near-space vehicle design and MEMS (Micro Electro-Mechanical System) micro beam design.At first, the hypersonic vehicle design problem is studied based on collaborative optimization. On the basis of systematic study of collaborative optimization, the hypersonic vehicle preliminary design collaborative optimization is brought forward and performed with variable complexity model. The effectiveness of MDO process and further study direction are confirmed.Secondly, the BLISS 2000 process is studied and improved. Several BLISS process are studied, and EBLISS 2000 is developed based on BLISS 2000, which is improved on the aspects of object functions, sensitivity analysis, constraints handling and moving limit. The test case shows the efficiency of EBLISS 2000 is much higher than BLISS 2000. The ETLISS process is also proposed for the three level system based on EBLISS 2000Thirdly, the combination of EBLISS 2000 and aerospace vehicle design computation is studied. The consistency of EBLISS 2000 optimal before and after decomposition is proved. The deterministic global optimization is studied and the GRGFF (Generalized Reduced Gradient Method based Filled Function) method is developed. The general high dimensional topology optimization nature of MDO problem is pointed out with several research modes. For the"black box"mode, the sequential approximation method LHS-MQ based on Latin hyper cubic sampling and multiquadric radial basis function is provided. Quasi sequential number-theoretic optimization method QSNTO is developed based on LHS-MQ and GRGFF. Combined with QSNTO, GBLISS 2000(Global Bi-Level Integrated System Synthesis 2000) is developed, which fits the existence of much computation in aerospace vehicle design better. The test case shows the effectiveness of GBLISS 2000.Fourthly, the combination of GBLISS 2000 and aerospace vehicle design uncertainty engineering practical demands is studied. A systematic research of aerospace vehicle design uncertainty is done. The system uncertainty analysis method SUA is analyzed and the revised system uncertainty analysis method RSUA is given. The combination method of RSUA and MDO process is analyzed and the UGBLISS 2000 (Uncertainty based Global Bi-Level Integrated System Synthesis 2000) process is developed based on the combination of RSUA and GBLISS 2000. The UGBLISS 2000 fits the existence of uncertainty in the aerospace vehicle design better. Test case shows the effectiveness of UGBLISS 2000.Finally, applied these research results and combined with the development trend of aerospace vehicle, the design problems of subsonic near space vehicle wing and MEMS micro beam are studied. Based on the nonlinear aeroelastic computation, the static aeroelastic numerical analysis model of subsonic near space vehicle is built with CFD-FASTRAN, Python, MSC-PATRAN and PCL. The GBLISS 2000 formulation of this design problem is given and solved with the object of range. The optimal wing performance is much better than the original wing performance. Based on the systematic MEMS system and MDO technology, the MEMS CAD"top-down"design process based on MDO is provided. The micro beam electromechanical model is built on ANSYS and APDL. The UGBLISS 2000 formulation of this problem is given and solved with some comprehensive indicator object. The result is better than deterministic optimal design.To sum up, the thesis aims at improving aerospace vehicle design level, develops excellent EBLISS 2000, GBLISS 2000 and UGBLISS 2000 processes and applies them in advanced aerospace design. Much exploring work of MDO process theory and advanced aerospace design application are done, which establishes a good base for aerospace vehicle MDO.