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2019, vol. 67, iss. 4, pp. 768-789
Modeling the movement of a missile in the tubular guide of the starting installation
aNational Agricultural University, Sumy, Ukraine
bResearch Center of Rocket Forces and Artillery, Sumy, Ukraine
cState University, Sumy, Ukraine

emailshyikoa@ukr.net, apavlucenko22@gmail.com, obukhov.olexii@gmail.com, igor.kopl@gmail.com
Keywords: missile launcher; movable launcher; elastic model; launching tube; spatial portion of movement; interaction forces; angles of vectors; center of mass velocities; projectile axis angles
Abstract
The paper presents computational and mathematical model of the spatial motion of a rocket with centering bulges and a pin on the body in a thin walled tubular guide mounted on two fixed supports and equipped with a screw groove. The models take into account the interaction of the projectile with the inner surface of the guide tube at the locations of the drive pin and the centering bulge. The strength of the normal reaction of the inner surface of the guide is found as a reaction to the elastic deformation of the pipe caused by normal to its inner surface displacements of the centering thickening at the point of contact with the guide. In this case, the tubular guide is considered as an elastic thinwalled shell. To calculate the values of the shell stiffness coefficient along its length, the finite element method implemented in the ANSYS Mechanical software package is used. The translational component of the projectile motion is investigated on the basis of the theorem on the motion of the center of mass. The rotational component is investigated on the basis of the Lagrange equations of the second kind. The generalized parameters of the rotational motion are the yaw Ps and pitch th angles, the angle of attack a, the angle of slip b, and the angle of rotation of the projectile around the longitudinal axis ph. The aerodynamic angle of heel ga is found from the transition formulas for the adopted coordinate systems. The yaw velocity angle Ps, the pitch velocity angle th, and the aerodynamic roll angle ga as well as the first time derivatives of these angles are converted into the yaw angles ps and pitch y of the projectile axis and their derivatives in the starting coordinate system.
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