Process automatization of creating shape of anti-aircraft missile nose in AutoCAD software

The proper use of a large amount of energy from a rocket engine, transformed in a relatively short time, requires ensuring the most favorable movement conditions. Rocket armament designers therefore use optimization methods as widely as possible. Two issues play a major role in the search for optimal flight conditions. First of all, optimal control programs should be selected, including propulsion programs and rocket direction control programs, and secondly rocket shapes with the lowest aerodynamic resistance [6]. Basic criteria in rocket flight dynamics are the minimum time to reach the target and the minimum energy needed to travel the route to the target. When considering the motion of the projectile in the atmosphere, the minimum-time criterion does not take into account energy losses, which are the greater the faster the rocket's flight speed. Increasing the speed should result in a shorter flight time. This does not mean, however, that in the case of missiles controlled by a minimaltime program, energy losses play no role. However, the only way to reduce them is to reduce aerodynamic resistance. Therefore, searching for the shape of the body with the least aerodynamic resistance is one of the most important problems. The most favorable rocket hull contour can be sought for various ranges of flight speed. Different speed ranges correspond to different air reflection hypotheses. The search for the optimal nose contour can be reduced to minimizing pressure resistance without taking into account friction. However, friction resistance can only be considered when determining the most favorable nose extension. This approach is justified, because frictional forces as tangent to the stroke slightly affect its shape, but are important in determining the slenderness of the nose. The function describing the nature of the anti-aircraft rocket nose curve can be determined using a variation calculus. The task is to determine the contour resistance of the expanding part of the hull defined as the rotary body (fig. 1).