A Study On Aerodynamic Configuration And Control Strategy Of Single Group Rudder Control Rocket

A simple low cost control system was designed aims at a rocket, and the system components and working mechanism was elaborated Aiming in this paper. Two aerodynamic rudders was used to control the pitch and yaw of the rocket in this system, it is simpler and easier comparing with four aerodynamic rudders. From the point of increasing the lift-drag ratio determined its configuration form is canard configuration, the rudder wing and the tail is〝--+〞aerodynamic configuration. According to rocket flight characteristics and the related theory of shape design, preliminary design three kinds of rudders and installation sites on the rocket. The aerodynamic parameters of the rocket with rudder and without rudder was estimated by classic aerodynamic theory, And the external flow field of the rocket was simulated and studied by fluid dynamics simulation software.The 6DOF rigid body ballistic model for the rudder-control rocket was established according to analyzing forces and torques when the rocket flew. The effects of the rudder placement,the rudder angle and the control time on control ability and ballistic performance was studied by exterior ballistic simulation. Taking account of the control ability and stabilization of the rocket, the control strategy of variable rudder angle was proposed, and the maximum longitudinal control ability is 3/8 times that of the non-control range, the maximum lateral control ability is 1/4 times that of the range.Simulated the control accuracy of the rudder by using Monte Carlo method, and calculated the intermediate deviation and dispersion of rocket impact point distribution caused by the rudder angle error and the control time error.The results of this paper provide some guide significance for overall design,aerodynamic configuration and control strategy of the rudder-control rocket.