Investigation Of Dynamic Characteristics Of Hypersonic Airframe/Propulsion Integrative Vehicle

In this paper, a numerical simulation investigation of hypersonic airframe/propulsion integrative vehicle was presented, which based on the Reynolds Averaged Navier Stokes equations and SA one-equation turbulence model. The 2-order Roe scheme and the dual-time-step methed are respectively applied to discreat of the spatial and time derivative of the unsteady fluency. Based on the unsteady Etkin pneumatics model, a numerical simulation investigation of force-oscillation of the little swing was established. The pitch, yaw and roll three directions of direct damping derivative, crossed dynamic derivative and cross-coupling dynamic derivative were solved by the numerical solution of the force-harmonic analysis method.The characteristics of unsteady flow-field and unsteady aerodynamic force/moment for HBS (Hyper Ballistic Shape)and Finner were investigated to verify the reliability of numerical methods. Dynamic stability derivatives were calculated from load history of the unsteady flow. The influence of frequency of force-oscillation, inner-iteration steps and mesh dimension to dynamic flow-field and dynamic aerodynamic force/moment was investigated. The dynamic stability derivatives predicted by the present methods quite agree with the experiment results.According to published literature and photographs, the X-51 hypersonic waverider aircraft's aerodynamic configuration is modeled using engineering Catia software and a 3d X-51-Type hypersonic vehicle with highly integrated scramjet and airframe system was designed. The basic cowl-closed and cowl-open force and moment coefficient predictions were calculated with computational fluid dynamics tools to evaluate the longitudinal performance. The analysis of an integration of aerodynamic and propulsion flow field characteristics was also performed. Using the unsteady aerodynamic model and the simulation of dynamic derivative, the stability dynamic derivative and the crossed dynamic derivative were obtained, and dynamic characteristics are surveyed by the present unsteady numerical simulation methods for the two shapes which the hypersonic inlet of X-51-Type is fully open and closed.