Performance Analysis And Structural Optimization Of Thrust Vector Nozzle With Vertical Secondary Flow Channel

With rapid development of aerospace technology,the performance requirements of thrust vector devices for aerospace vehicles are increasing.Due to the large disadvantages,traditional mechanical thrust vector device can not meet development needs.The research focus of thrust vector technology began to gradually turn to shock vector control technology.As a kind of pneumatic jet technology,shock vector control technology can realize large vector pitching angle and begin to become a new direction of thrust vector technology research.Based on the concept of shock wave and Laval,Gambit is used to construct a thrust vector nozzle with vertical secondary flow channel.The thrust pitching angle dp is generated by the interaction between the secondary flow with the secondary shock and the main stream.The secondary flow channel is composed of a front vacuum chamber,a secondary flow ehamber and a rear vacuum chamber.Coupled solver of Fluent is used to analyze the effect of the distance from secondary flow chamber to nozzle outlet e,secondary flow chamber wedge angle δ1the secondary flow chamber oblique wall deflection angle γ,the front vacuum chamber width w1,NPR and SPR on thrust pitching angle δp.Finally,the Isight software is used to optimize the structure of the secondary flow channel of the nozzle.Structural optimization design is carried out by the Latin hypercube design method and RSM modeled method.Using the MIGA algorithm and ASA algorithm to find the optimal solution for the four design parameters including secondary flow chamber wedge angle,the secondary flow chamber oblique wall deflection angle,the front vacuum chamber width and the and the distance from secondary flow chamber to nozzle outlet.After using two algorithm to find the optimal solution,based on the structural parameters derived from the optimal solution,use Gambit to build the model and use Fluent simulate to obtain the thrust pitching angle δp.Compare the pressure distribution of the upper and lower walls,the velocity vector and the vortex distribution to analyze the optimized performance.