Multidisciplinary Design Optimization For Winged Re-entry Vehicles Considering Stability And Control Characteristics

Winged Re-entry Vehicles(RV-W) are the focus of the design and development of Reusable launch vehicles(RLV) at present stage,and the research on the design technology of RV-W has been generally carried out in the major aerospace countries.However,there are still some technical difficulties in RV-W overall design,such as the multi-disciplinary design optimization,the strong interaction effect between disciplines,and the long design cycle.In order to effectively shorten the overall design cycle and improve the quality of the design scheme,this paper investigates the overall rapid design,analysis and optimization techniques of RV-W.Main work of this paper focuses on the following aspects:Firstly,the rapid analytical method and solve programs of the multi-disciplinary modules of RV-W design are researched and developed respectively.(1)Aerodynamics: a rapid aerodynamic prediction method oriented to full flow range and full speed range is studied and developed.Several test cases demonstrate that the prediction method has high automation,fast calculation speed and strong robustness;(2)Aerodynamic heating & thermal protection system(TPS) design optimization: a rapid prediction method of aerodynamic heating of hypersonic vehicle for continuous and rarefied gas is established,and a prediction method for the wall radiation temperature is built.A module for rapid analysis and optimization of hypersonic vehicle thermal protection system is carried out.(3)Stability and control: combining "quasi motion" with "hypersonic panel method",a fast prediction method of dynamic derivatives for hypersonic vehicles is developed.The stability and control characteristics of RV-W are analyzed,and some criteria of coupling departure are deduced.(4)Trajectory: an optimization strategy for re-entry trajectory of RV-W is established,and a trajectory method satisfying a series of constraints is designed to achieve effective combination of numerical solution and optimization theory of motion equation.Secondly,according to the design principles and objects,combining the input/output with interactions of disciplines,the general design process of RV-W is proposed.Based on the general design process,integrated modules of aerodynamics,aerothermaldynamics,TPS,stability/control,trajectory and weight estimation,the multidisciplinary design optimization method and integration system for RV-W are established and developed.Finally,bases on the multidisciplinary design optimization method and integration system for RV-W,the aerodynamic performance,aerothermodynamic environment,thermal protection system,re-entry trajectory of X-37 B analog are optimized with considering stability and control characteristics.Besides,for aero-assisted orbital transfer vehicles,the coplanar orbital transfer from high earth orbit to low earth orbit for a RV-W is studied,and the results indicate that the stability and control constraints have little effect on fuel-saving criterion for aero assisted orbit transfer.The developed multidisciplinary design optimization approaches for RV-W showed in this paper are demonstrated to be effecitve by two examples discussed above,which also indicate the MDO integration system is robust.