Calculating Method Of Aerodynamic Heating For Hypersonic Multi-body Separation Process

With the rapid development of hypersonic vehicle technology, the problem of multi-bodyseparation with high Mach number and low-altitude is attracting more and more attention. Theaerodynamic heating problem during multi-body separation has become increasingly important. Butthe combination of research on aerodynamic heating with multi-body separation problem is little.Therefore, research on this issue becomes very necessary.In this thesis, a computing technology of aerodynamic heating for hypersonic vehicle multi-bodyseparation process is presented, and a program interface is compiled to form a set of software. Amethod of combining numerical simulation with aerodynamic heating engineering is developed tostudy the aerodynamic heating calculative technology in hypersonic vehicle multi-body separationprocess. The Euler equation is used to calculate the inviscid solution outside the boundary layer, andthe aerodynamic heating engineering method is used to calculate the heat transfer in boundary layer.Then the structure heating is coupled and the chemical non-equilibrium effect and the characteristicsof transition are also considered.Firstly, this thesis analyzes and improves the calculating method of aerodynamic heating forcomplex shape aircrafts, and studies the effect of material properties changing with the flow field onaerodynamic heating result. The calculation results show that this approach can meet the requirementfor the engineering needs.Secondly, based on the computing technology of aerodynamic heating, and combined withmulti-body separation process, this thesis present a computing technology of aerodynamic heating forhypersonic vehicle multi-body separation process, and a method of dividing the separate body andsetting the thermal protection system according to the divided body. This method can accuratelysimulate the thermal protection system in practical engineering.Finally, for assumed layout of multi-body separation aircrafts, this method carries outcalculations and theoretical analysis of temperature distribution characteristics and heat fluxdistribution characteristics of multi-body separation process, and discusses the influence ofmulti-body separation process on aerodynamic heating. The research results show that the computingtechnology developed by this paper can provide technical support for hypersonic aircraft schemeselection and the design of the thermal protection systems.