Two-dimensional Correction Trajectory Correction Mechanism Design And Its Aerodynamic Missile Analysis

In modern war, the use of precision ammunition not only decides the victory orfailure of the war but also effectively decreases the casualty rate of common people. Thetrajectory correction projectile is one of typical representatives. One of the technicaldifficulties during the development is how to choose the correction implementingmechanism with high performance and low cost.First, based on the analysis and summary of the domestic and foreign presentsituation and tendency of the development of the trajectory correction projectile, thepaper states that the scheme of two-dimensional trajectory correction is confirmed; thecorrection mechanism is designed; the strength of main components is checked;three-dimensional virtual prototyping is established by applying Pro/E software.According to the principle of multibody system dynamics, the mathematical model ofthe correction mechanism is established. The ADAMS software is analyzed bycombining dynamics, and the kinematic analysis is carried out for a steering machine. Areal model machine is processed. The result shows that the operation of the modelmachine is smooth, and the strength of key parts is qualified, which provides theconditions for a real validation test.Secondly, according to the aerodynamic principle, different areas and installationlocations of the rudder blade and aerodynamic characteristics of different flight statesare analyzed and compared by applying the turbulence model theory and combining thecomputational fluid analysis software-Fluent in order to provide the reference forfurther optimized layout of the correction projectile.Finally, based on the theory of the external trajectory of the projectile, the force inthe flying course of the correction projectile on the external trajectory is analyzed, andthe trajectory equation of the duck rudder type correction projectile is established. Theparameter of the external trajectory of the correction projectile is calculated by applyingthe method of fourth order Runge-Kutta attitude algorithm and combining with theresult of aerodynamic characteristics. To obtain the correction capability of rudderblades of different areas on the different locations. The evidence is provided for the following control solution, simulated flight, etc.