Reseach Of Lateral Jet Of Platelet Structure In Hypersonic Vehicle

Along with the rapid development of science and technology, the traditional rudder vehicle control system has been unable to achieve high maneuvering efficiency of the demand of the quick change track. Especially in the military field, high speed, big mobility cruise missile puts forward higher requirements on air defense missile. Lateral jet belongs to the reaction jets control system, it is one of the key technology of precision and posture adjustment. Direct force control of the lateral jet is suitable for the domain and the whole airspace at full speed, with fast reaction, high efficiency, it becomes one of the most important means of attitude control. This article mainly research and numerical analysis the interference field caused by lateral jet under the condition of supersonic of the platelet nose.First of all, This paper on the floor plate under the condition of small scale Mosaic nozzle has carried on the design and simulation, by solving the basic equations and variable cross-section isentropic equation to determine the nozzle design principles; and confirmed its presence in the small-scale generation supersonic flow conditions possibilities. Considering the thickness of the nozzle and total pressure influence on the flow, We find that it’s influence on the nozzle flow conforms to the general rule.According to the actual situation of lateral jet flow and reasonable assumptions, we establish a mathematical model of flow field of lateral jet interference. k-ε Turbulence model is adopted to solve the basic control three-dimensional Navier-Stokes equations, we use AUSM-DV type MUSCL difference scheme to analysis convection item and LU-SSOR implicit format for discrete time items.under the different emergence Angle parameters, we numerical calculate the interference flow field. We find that the separation shock wave were delayed by the jet of Negative emergence Angle. Greatly improved the area of high pressure and the value. Increasing the positive gain effect. But the attached compressed affects the strength of the bow shock is stronger, make the temperature near the jet more bad. With the angle ? increases from negative to positive,Amplification factor decreases. The gain effect turn to negative. Downstream thermal environment has also improved.The second, by changing the size of the jet Mach and pressure ratio,we control the intensity of the shock wave. The result show that the flow of jet itself was very pressing by the shock wave. in order to meet the demand of thermal protection, If the jets break through the boundary layer but not interact with ball head detached shock wave, the jets has a better cooling to the downstream model wall heat effect. At the same time,Through the selection of nozzle position, we verify the installation again that the end of the vehicle flow equipment can maximize the effect of the increase is gain.At last, we compared the multiple jets series-parallel structure research, we found that under the same static thrust, parallel structure has better ability to control aerocraft.