Aerodynamic Configuration Research Of Normal Configuration Guided Rocket

The traditional rocket is a kind of nonguided weapon with poor accuracy and short range, it obviously cannot meet the need of modern war. Guided rocket is a kind of precision guided munitions with low cost, which adds INS and satellite navigation system on the basis of traditional rocket, making the rocket shoot further and more accurately. In order to make the guided rocket have good maneuverability, controllability, stability, guided rocket generally uses aerodynamics configuration with multiple groups of wing, thus higher requirements are put forward on the design of aerodynamics configuration. For the study of configuration effects on the aerodynamic characteristics, this paper carried out research work on rocket model through wind tunnel experiment and numerical calculation.First of all, wingless configuration rocket models with two different kinds of nose shape are designed, the variation of each aerodynamic parameters over angle of attack, mach number, rudder angle are gotten through wind tunnel experimental, and aerodynamic differences caused by different nose shapes are analyzed. The results show that the ogival nose shape model have smaller drag coefficient, larger normal force coefficient and better lift-drag characteristics, but the pressure center of the double conical nose shape model is larger, its stability is better than the ogival nose shape model’s.Secondly, normal configuration rocket model with three different sizes of rudder-fin spacing are designed, the variation of each aerodynamic parameters over angle of attack, mach number are respectively gotten though the method of numerical calculation when tail rudder is not manipulated, rolling control, pitching control, and aerodynamic differences caused by different rudder-fin spacing are analyzed. The results show that, the smaller rudder-fin spacing can play the role of antidrag, especially in subsonic and transonic range. When the rudder-wing spacing decreases, the normal force coefficient of the model decreases, but the fore-wing is backward, making the model have a better stability moment. When the tail rudder is rolling control, the effects of the smaller rudder-fin spacing on rolling control characteristic is more pronounced, resulting in the decrease of rolling moment coefficient. When the rudder is pitching control, the larger of the rudder-fin spacing, the smaller effects on the pressure center of tail rudder from fore-wing, the position of the pressure center changes gently, this is helpful to the design of rudder fulcrum.The results of study on the aerodynamic configuration of guided rocket in this paper have practical significance and reference value.