Based On The Concatenated Meteor Rocket Engine Tail Control Technology Design

Based on concatenated "meteor" missile solid rocket booster to derive newremote in ship to air missile as the research background, in helping to solve theengine before the separation, the derived type of ship to air missile aerodynamicparameter calculation and the stability of the new ship to air missile roll channelcontrol problem. The main content of research includes the following aspects:First of all, the new ship to air missile combat mission, the way choose ofpropellant and explosive design booster diameter. Then calculate the added boosterafter the physical parameters of the missile. Then on missile aerodynamiccharacteristics and quality analysis and determine the structure size of rotating tail,and the derived type of ship to air missile mathematical modeling.And calculate derived type of ship to air missile aerodynamic parameters, usingGAMBIT software mesh of the derived missiles in a reasonable manner, and byusing the FLUENT software GAMBIT software division good grid to calculate. Tocalculate the basic aerodynamic parameters of the missile.Later for fixed wing roll and the induced roll torque control torque analysis,main consideration is produced by washing under the induction of roll torque, thecross rotary wing-elastic body after combination, studies the induced flow fieldanalysis is derived to calculate the induced roll moment coefficient and the inducedexpression of roll torque. And according to the specifications and parameters ofmissile in this paper, the induced roll moment coefficient with different attack Angleand the induced roll torque curve along with the change of rudder Angle.And establish the rotary wing dynamic model is derived and analyzed themagnus moment generated by rotating the tail of the effect on the stability of themissile attitude. Presents a new type of ship to air missile roll channel controllerdesign scheme of roll channel control model is established, using classical controltheory to design PID controller, and through the Simulink simulation analysis,calculation and simulation of pitch and yaw magnus moment, missile flight trajectory, the speed and torque curve of effect on the missile...