Aerodynamic Characteristics And Fluid-structure Interaction Computations And Analysis Of Supersonic Spinning Flying Vehicle

When designing a flying vehicle such as bullet, missile or non-spinnmg/spinning rocket to operate for some period of time at supersonic or hypersonic flight velocities, one has usually to deal with several features to fulfill the operational demands. Along with some general features, such as aerodynamic design, there is another most important design aspect arising only when flying at high velocities:the aero-heating of the flying vehicle. Moreover, with the continuous increase of modern slender rocket flight velocity, it has become important to compute the effects of the coupling between aerodynamic loads and structure elastic forces, even the coupling between aerodynamic loads, thermal loads and elastic forces. Since aeroelasticity and aerothermoelascity effects can contribute to the design of the rockets significantly, there is a strong need in the aerospace domain to predict these fluid-structure interactions computationally. In the present study, a numerical method for the aerodynamic/aero-heating computations is carried out using computational fluid dynamics (CFD) analysis tool. While, CFD in conjunction with computational structural dynamics (CSD) analysis tool are used for the static aeroelasticity and aerothermoelasticity analysis. These two tools are working together under one platform of ANSYS workbench multiphysics coupling.Firstly, M910bullet and wing-body missile F4computational models are established. Their aerodynamic characteristics are simulated numerically by the method, which is combining CFD code and empirical formula. Many aerodynamic coefficients are calculated and compared with the experimental data and the error is mainly within the engineering error. In the condition of different flight velocity and different angles of attack, the temperature contours and the temperature distribution along the center line of missiles windward side are calculated and analyzed. The results provide valuable reference of the slender wrap fins spinning rocket’s static aero-elastic and static aero-thermo-elastic numerical computation.Secondly, normal force coefficient distribution of the axisymmetric multistage launch vehicle model is determined, and the computational results are in good agreement with the experimental data. Based on the CFD/CSD and inertial relief methods, static aeroelastic behaviors of the rocket are numerically simulated. Next, one-way and two-way coupling of the rocket are carried out and studied. The results highlight that the rocket deformation aspects are decided by the normal force distribution along the rocket length. Rocket deformation becomes larger with increasing the flight angle of attack. Drag and lift force coefficients decrease and pitching moment coefficients increases due to rocket deformations, center of pressure location forwards and stability of the rockets decreases. Accordingly, the flight trajectory may affected by the change of these aerodynamic coefficients and stability.Finally, the aerodynamic heating of the high-temperature wind tunnel’s experiment model is computed, and the temperature distribution and flux distribution are compared with the experimental data, which revealed well-agreement. Subsequently, static aero-thermo-elastic analyses of the slender wrap fins spinning rocket are carried out using ANSYS Workbench platform. The results demonstrate that spinning causes a significant impact on the deformations and stresses. Furthermore, thermal stresses have a dominate influence at the rocket warhead and tail edges, even more than the one produced by aerodynamic loads.The present study outcomes provide a valuable reference for aerodynamic/aero-heating characteristics and fluid-solid interaction analyses of high-speed spinning flying vehicle that should be taken into consideration during the design stages.