Research And Implementation Of Performance Evaluation System For Hypersonic Flight Vehicles

With the rapid development of the computer and computing technology, CFD technology is well developed and begins to be applied to engineering practice. Now numerical simulations with CFD method gradually become an important method for flight vehicle design. The rich countries in the West attach great importance to CFD technology whose CFD computational method and computational software become riper. However, at home there are discernible differences in the CFD technology and CFD software. Meanwhile parallel computing based on massively parallel computers is an inevitable trend with the continuous increase in complexity of the flight vehicles.CFD computing method and CFD software techniques are regarded as the starting point of this thesis. This thesis aims to establish the parallel computing environment used for performance evaluation for hypersonic flight vehicles. Based on existing research results, we establish an evaluation system which integrates sub-systems of aerodynamic force computing, aero-thermal computing, ablation/erosion computing, flight stability computing and trajectory computing. Meanwhile we parallelize and integrate some of the sub-systems, which have important theoretical significance and practical value. The main contributions of this thesis are as follows.(1)This thesis has worked extensively with the present situation of academic and industrial institutions both at home and abroad in CFD computing environment, CFD computing technology and software systems. And it makes a comparison with various techniques and systems. Overall, CFD computational softwares abroad are often fully operational, quick in calculation, less resource exhausting and have excellent versatility while CFD computational softwares at home are weak developed, less extensible and have lower computational accuracy and slower computing speed.(2)This thesis presents the general design for the evaluation system of hypersonic flight vehicles and detailed design for sub-systems of aerodynamic force and trajectory computing, aero-thermal and ablation/erosion computing, flight stability computing, small platform of parallel computing and interactive graphics respectively. Next we implement the above designs, which have been used in engineering practice.(3)This thesis has parallelized parts of the programs of the evaluation system, in order to improve parallel efficient and reduce the calculation time. We take the aerodynamic force and aero-thermal computing for example, and domain decomposition is used for parallel CFD computations of structured grid. For the CFD example of NACA0012, parallel performance is tested in our parallel platform, which has high parallel efficiency.