Abstract
Abstract The purpose of this study was to describe dynamics of missile based on bibliography, simplify the model to the easiest form, and verify it with the use of a designed laboratory stand. Next, a simple control system of the missile was designed. The stand is prepared for didactic purposes. A mathematical model was derived by applying Newton's second law together with the earth's coordinate system and the base coordinate system. Parameters of the actual rocket model were determined using the created laboratory stand. Synthesis of the rocket roll system was designed using Simulink PID Tuner application (MathWorks, Inc. Natick, Massachusetts, USA). A control system was based on a proportional-integral (PI) regulator. The designed control system was subjected to simulated tests in MATLAB Simulink (MathWorks, Inc. Natick, Massachusetts, USA).
Highlights
The purpose of this article is to show results of an engineer’s thesis
Summary and Conclusions The objectives of the study were to determine the mathematical model of the rocket and to synthesize the algorithms of angular motion of the rocket
The work was started by deriving the full mathematical model of the rocket and determining the equations of dynamics in angular motion
Summary
Algorithms are supposed to provide automatic control of specified roll speed of a given rocket. The step was to verify the applied mathematical model to the actual model. For this purpose, a laboratory stand was built, in which a flight of the rocket was simulated by providing a constant air flow, and rotation speed of the rocket and dynamic pressure of the air stream were examined. A control system was developed for the mathematical model of the rocket, and it was subjected to simulations tests. The first section focuses on obtaining equations for rocket’s general motion. The second section uses equations of general motion to obtain equations in lateral motion and in the end transfer function of a rocket in roll mode. The third section depicts deriving the dimensionless coefficients used in transfer function of a rocket
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