Analysis Of Ballistic Characteristics And Research On Guidance Law For Simple Guided Rocket

As a kind of long-range fire suppression weapon,rocket is widely used in modern battlefields.With the improvement of the precision requirement of weapons and projectiles in modern battlefields,the development and use of simple guided rockets have become a new trend.In order to study the guidance design for uncontrolled rockets,the fin rocket and the simple guided rocket with fixed canard rudder were researched in this paper.The research contents included the aerodynamic characteristics,ballistic characteristics,firing dispersion and guidance law of the rocket.The main research contents are as follows:The physical models of the uncontrolled fin rocket and the fixed canard rudder rocket were established.The external flow field of the fin rocket was simulated and the aerodynamic characteristics of the fixed canard rudder rocket were researched.The results show that the aerodynamic characteristics of the fin rocket accord with the aerodynamic law;Increasing the deflection angles of fixed canard rudders in a certain range is helpful to increase the lift and pitching moment of the rocket,but the drag too;When the ratio of length to diameter of the rocket reaches a certain value,the aerodynamic interference of the fixed canard rudder to tail fin disappeares,and the aerodynamic interference characteristics between the canard rudder and tail fin are also applicable to the situations of different relative angles between the canard rudder and tail fin.The 6-DOF motion equations of low-speed rolling rocket was established,and the external trajectory of the uncontrolled fin rocket was calculated,and the target shooting was simulated.The results show that increasing initial velocity can increase the range of the rocket slightly,and the range is maximal when the angle of firing is 45 degrees,and the external trajectory performance of the rocket is good;The variation in a small range of the initial velocity has little effect on the dispersion of the impact point.CEP of the rocket is minimal and the firing dispersion is best when the firing angle is 45 degrees,and the dispersion of the impact point of the rocket satisfies the normal distribution law and the dispersion ellipse law.With the establishment of the relative motion equation of proportional guidance,the guidance trajectory characteristics of rocket using our proposed guidance law were analysied.The results show that the application of the proportional guidance law to the terminal guidance of the uncontrolled rocket can highly improve its firing accuracy;The application of the proportional guidance law with gravity compensation can effectively improve the guided trajectory performance and reduce the required overload of the terminal guidance of the guided rocket;The proportional guidance law with over-gravity compensation can increase impact angle of the rocket,and with the increase of the over-gravity compensation item,the required overload of terminal guidance will increase too.