Blended Control System Design for Missile with Tail and Lateral Thrust

• Main Authors: Wang,Yen-Chang, 汪言璋
• Other Authors: Lin,Ching-An
• Format: Others
• Language: zh-TW
• Published: 2014
• Online Access: http://ndltd.ncl.edu.tw/handle/47385830808422806230

碩士 === 國立交通大學 === 電控工程研究所 === 103 === This thesis investigates the control about blended control for missile actuator with tail and lateral thrust. Tail controller changes angle of attack to generate lateral force by aerodynamic. To achieve requirements of steady-state and transient performance, tail controller is designed with proportional-integral controller with angular velocity feedback. Because of limits for degree of the tail as well as non -minimum phase dynamics, transient response of tail control may not meet the needs of interception. So anti-tactical missile, such as the Patriot III , often combining the lateral thrust actuators in the final stages of terminal guidance to improve the ability to intercept . Concept of blended control design is considering tail control as the main controller, and lateral thrust as auxiliary controller to increase angle of attack rapidly. In this thesis, we propose two blended control designs. First is considering the input of linear tail control as match disturbance, and be designed with sliding mode control for lateral thrust controller. Second is considering the lateral thrust as a single-input control, and be designed with sliding mode control for missile model that contains tail-only controller. Simulations of guidance show the capabilities of interception for blended control. Obviously, combing lateral thrust actuators can improve system response.