Analysis Of Pneumatic Characteristics And Trajectory Simulation Of A Certain Type Of Satellite Guidance

Artillery as "the god of war" has a long history of the ground war is one of the main army concomitant suppressive fires. Artillery of projectile in reducing spread of the premise, how to greatly improve the accuracy of its combat, the first hit and the first to reach the purpose of damage, has been favored by the world. Currently, the conventional weapons’ guidance technology has become the major military power in the world competing research focus.This research is based on a simple satellite-guided mortar shells, studying the aerodynamic characteristics of the projectile, and the dynamic characteristics of the missile and projectile trajectory correction pulses. Details are as follows:1. Engineering calculations. According to the project empirical formula, combining theoretical knowledge of projectile aerodynamics and the bullet-shaped structure, the projectile’s flight conditions, write a program to calculate the projectile’s aerodynamic parameters. Aerodynamic characteristics of the three pre-selected programs given on a comparative and analysis, combined with particle trajectory simulation results to choose a plan that best meet the design requirements of this article as a basis for follow-up research.2. Numerical simulation of the flow field and aerodynamic characteristics analysis. ICEM conducted using projectile mesh drain field, using FLUENT to simulation calculation the flow field, get the projectile aerodynamic parameters. According to the simulation results and analysis variation of projectile aerodynamic parameters under different conditions.3. Aerodynamic parameter fitting. Using nonlinear least squares fitting the numerical simulation of aerodynamic parameters, aerodynamic projectile parameters obtained with a bivariate (angle of attack, Ma number) changes fitting formula.4. Dynamic characteristic analysis. Establishment of rolling projectile’s body transfer function based on small perturbation theory, that analysis projectile’s body at pulse stability of engine operating conditions. According to the structure and projectile missile aerodynamic parameters calculated intrinsic angular frequency and design projectile speed, according to the design speed, and analysis of the size of the tail oblique angle.5. Trajectory simulation. According the aerodynamic parameters and combining the structural parameters of the projectile, design muzzle velocity, pulse power analysis and others simulation projectile trajectory correction pulse.