Research On Flight Control Of Rolling Rocket With Cruciform Configuration Canards

The rocket missile is a kind of low-costing non-guided munition with simple structure, which canbe used to attack some moving or motionless targets such as military fortification, tank, armoredvehicle and so on. The rolling projectile scheme of rolling rocket can decrease the thrust eccentricityof rocket engine, pneumatic asymmetry and mass eccentricity on the influence of ballistic spread. Thegyroscopic effect of rolling also makes the flight of projectile stable. The rolling rocket can becontrolled in longitudinal and lateral direction with a couple of canard because of rolling, which isalso called single channel control. In order to improve the accuracy and efficiency of control, twocouples of canard can be used to realize the double channel control. The coupling and other effectcaused by rolling projectile make the flight control more complicated than non-rolling missile. Theresearch object is rolling rocket with cruciform configuration canards in this thesis. The detail contentas follows:Firstly, the periodic mean control force and its control principle of rolling rocket are analyzed. Thetype of control signal is confirmed. The trajectory mathematic model of rolling rocket is built throughthe analysis of its force and moment. The time varying linear model and transfer function are acquiredwith method of linearization of small disturbanceThen the shape and size of canard rudder are confirmed according to flight condition andperformance. The motor is chosen based on the hinge moment and power. The system of electricsteering gear model is built and simulated. The influence of linear electric steering engine’scharacteristic saturation on control performance is analyzed.In addition, the characteristic of coupling system and its coupling factors are analyzed. Thedecoupling control law of forward feedback compensation is designed. The coupling of motion andcontrol of rolling rocket is decoupled. The result of simulation indicates that the overload loop isdecoupled. It makes the foundation of continued research on control law of revised trajectory.At last, the PID controller of rolling rocket’s revised trajectory in longitudinal and lateral directionis designed. The parameters of PID controller are optimized online by the use of fuzzy controlalgorithm. The controllers designed in this thesis are verified to meet the control accuracy requirementof rolling rocket through the completed trajectory numerical simulation. The research in this thesis hasimportant reference value for the further engineering realization.