Research On Guidance And Control System For Rolling Missile With A Strap-down Seeker

With the development of military technologies, the research demands for low-cost and high-precision rolling missiles are increasing, which brings the rolling missile guidance and control technologies to wider notice in both academia and industry. In the modern war, the improvement of tactical and technical index together with the reduction of manufacturing cost has made higher requirements to the guidance and control systems of rolling missiles. The low-cost strap-down seeker, without acquiring the angular rate of sight, can only measure the angle of sight. Meanwhile, rolling missile also has the rotation coupling characteristics, which cause the cross link effects between longitudinal and lateral movements, therefore missile engineers and researchers should waste no time utilizing these features of rolling missiles to design guidance and control systems and thus improve the hitting accuracy.This paper takes the design of guidance and control system for rolling missiles as application background, and relative studies have been conducted, including the plan of guidance and control system and related key technologies. At first, an introduction about the research purpose and significance of rolling missiles is stated, and investigations and analyses of current domestic and international research situations are given. Next, on account of the characteristics of rolling missiles, the coordinate systems and angles relations are newly defined. With these basic conditions, the kinematics and dynamics models of rolling missiles have been established and longitudinal and lateral ballistic schemes have been designed. Then the rolling missiles guidance system is analyzed. Three guidance methods capable for strap-down seeker are put forward, and the study focus is strap-down proportional guidance method whose law is deduced in detail. Also the aerodynamic data for rolling missiles are calculated, the rudder model is given, and the missile body transfer functions are derived. Aiming at the coupling feature of rolling missiles, two available decoupling methods are created and independent control systems for three channels are designed. Finally, the simulated analyses of missile rotation characteristics and control system and integrated simulation investigations of SDOF are fulfilled respectively. The simulations results show that the proposed control system for rolling missiles is effective and correct.The results of this study can provide some references to the design of rolling missiles guidance and control system, which also have strong theoretical significance and engineering application value.