An Application Research On The New Fluidic Thrust Vector Nozzle

Fluidic thrust vectoring nozzle is an important type of thrust vector technology in recent years,which can achieve the deflection of the jet through the flow control without the movement of the nozzle wall.A Bypass Dual Throat Fluid Thrust Vectoring Nozzle is studied in this paper.The research mainly includes two aspects: Full vector rudderless flight control based on the nozzle and the performance of nozzles in high temperature environment.Firstly,a single binary nozzle can only generate one-way thrust vectors.In order to satisfy the pitch,yaw and roll control effect of the aircraft simultaneously,this paper studies the layout of "single inverted V-dual nozzle" based on the basic nozzle.In order to explore the thrust vector control law of the new layout nozzle,the numerical simulation calculation and force experiment are carried out.Then the aircraft using the new layout nozzle is designed and manufactured.Finally,the aircraft successfully carried out full thrust vector control flight and the flight data are collected.Subsequently,the effect of high temperature on the performance of the Bypass Dual Throat Fluid Thrust Vectoring Nozzle is studied.And the nozzle model is installed on the micro turbojet engine in order to verify the performance of nozzle in real application environment.The results show that:1.The new layout nozzle can effectively control the pitch,yaw and roll attitude of the aircraft during cruising,which realize the rudderless flight with pure fluid thrust vector control.The effect of vector control and rudder control is similar in rolling maneuverability,which are about 100 degrees/s.But for pitch maneuverability,the effect of vector control is weak.When the rudder controls the pitch of the aircraft,the maximum rate of the head-up angle can be up to 50 degrees/s,while when the vector controls the pitch of the aircraft,the maximum rate of the head-up angle can be about 26 degrees/s.2.The force measurement experiment results show that the vector angle varies linearly with the nozzle valve opening and the nozzle does not exist hysteresis.The maximum thrust vector angle is in agreement with the simulation results,and can reach about 20 degrees.3.Influence of nozzle pressure ratio on the performance affect more than the temperature;Compared with the other performance parameters,the thrust vector angle is more sensitive to the change of temperature;Compared with the high nozzle pressure ratio(NPR>4)condition,the high temperature environment has more effect on low NPR.The fluid thrust vector nozzle studied in this paper has passed low-speed force measurement and flight test,micro turbojet engine test and high-temperature simulation,which shows that it has potential application value in engineering.