Numerical Method Of Aerodynamic Heating With Ablation Effects For Hypersonic Vehicles

The outstanding achievements in hypersonic vehicle development are closely related to the progress in thermal protection technics. Due to the need to withstand the rather harsh thermal conditions accompanying with the development of hypersonic vehicle, the early thermal protection materials no longer have the adequate properties for the requirement of TPS(Thermal Protection Systems) and have been replaced by the carbon-carbon materials gradually. The ablation of heatshield during the reentry will have a considerable impact on the aerodynamic heating, and simulation the procedure with acceptable fidelity and low cost is the critical part of TPS design process.In this thesis, for rapid and accurate prediction of TPS aero-heating characteristics under the ablation condition, a computing technology of aerodynamic heating with ablation effects for hypersonic vehicle is presented, and a program and an interface are compiled to update a set of software.Firstly, there is a brief introduction of single complex configuration aerodynamic heating computation technic which is the base of this thesis. This technic coupled the inviscid outer-flow solutions and engineering method was developed to predict the aero-heating properties for hypersonic vehicles. Combined with the structure heating, this technic could be used to analyze aero-heating and structure heat conduction characteristics for hypersonic vehicle.Secondly, ablation effect is the research focus in this thesis. A study of ablation model and computing technique is carried out, then an algorithm of ablation effects based on temperature partition is proposed. This algorithm could accurately predict the TPS material ablation characteristics in engineering practice.Then, based on the single complex configuration aerodynamic heating computation technic, combined with carbonaceous material ablation computation algorithm developed in this thesis, an aerodynamic heating with structure heat conduction and ablation effects program is compiled and update a software. A typical configuration case is chosen to validate the program.Finally, for assumed layout of cruising aircrafts in hypersonic speed, this method carries out calculations and theoretical analysis of temperature distribution characteristics, TPS material mass loss and heat flux distribution characteristics with ablation appearing, and discusses the influence of ablation material and structure model on aerodynamic heating simulation. The research results show that the computing technology developed in this paper can provide technical support for hypersonic aircraft scheme selection and the design of the thermal protection systems.