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Research On Comprehensive Optimization Design Method Of Hypersonic Vehicle Considering Control Performance

Posted on:2021-10-24Degree:MasterType:Thesis
Country:ChinaCandidate:C L YiFull Text:PDF
GTID:2492306479460384Subject:Navigation, guidance and control
Abstract/Summary:PDF Full Text Request
The hypersonic vehicle model is very complex,and strong couplings between disciplines and uncertainty caused by environmental factors increase the difficulty in model performance analysis and optimization.Aiming at the strong multidisciplinary coupling problems of the hypersonic vehicle,comprehensive optimization methods considering control performance are proposed,including model simplification,trajectory design and distributed optimization.The specific works of this paper are provided as follows:Firstly,the parametric model of the hypersonic vehicle is constructed,including the generation of geometry,the calculation of aerodynamic force,moment and thrust,and the establishment of model database.The optimal design variables are determined by the sensitivity analysis of the shape parameters.Then,the true model is simplified using the data fitting method,and the surrogate model of hypersonic vehicle is obtained.The reliability of the surrogate model is verified by data comparison and performance analysis.Secondly,according to the constraint conditions in relation to scramjet and cruise performances,the starting and ending points of the trajectory are determined.The climb trajectory of the hypersonic vehicle is designed.First,the vehicle reaches the cruising speed through climb under the constant dynamic pressure,then the vehicle reaches the cruising altitude through climb under the constant Mach number,and the climbing command of hypersonic vehicle is obtained.Then,the tracking control of the trajectory is realized by LQR controller for the hypersonic vehicle.Finally,the distributed optimization architecture considering control performance is proposed for the hypersonic vehicle.Based on the theory of gap metric,the performance index of optimal design is constructed.The complex optimization problem is divided into the shape parameter optimization considering control performance and the controller parameter optimization.The results of the comprehensive optimization design are obtained using the particle swarm optimization method.The effectiveness of the proposed optimization strategy is verified by simulation and comparative analysis.
Keywords/Search Tags:Hypersonic vehicle, Comprehensive optimization method, Surrogate model, Trajectory design, Flight control
PDF Full Text Request
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