MISSILE MOVEMENT CONTROL SYSTEM STABILITY RESERVE

Abstract

The requirement to ensure the necessary stability factor of the rocket's rotational motion is one of the most important. It is known, the parameters of the rocket as a control object during the flight depend on the point of the trajectory and fuel consumption, that is, the stabilization system is time-varying. In the available sources, due attention is not paid to the development of a mathematical apparatus for determining the quantitative assessment of its stability factor.
 The purpose of the work is to substantiate the possibility of establishing a section of the trajectory on which the non-stationary system is matched by an equivalent system with
 constant parameters. This reduces the level of complexity of algorithms for the study of dynamic characteristics the margin of stability.
 The mathematical model of the stabilization system is adopted in the form of a linear differential equation with time-varying parameters of the control object without taking into account the inertia of the executive device and other disturbing factors. The effect of the deviation of the parameters from their average values ​​for a certain part of the trajectory is considered as a disturbance that makes it possible to move from an approximate stationary model to a non-stationary one without increasing its order.
 Using the example of a time-varying system for stabilizing the rocket rotational motion in the yawing plane, the possibility of using the Laplace transformation to determine the indicators of the stability factor by amplitude and the stability factor by phase is shown.
 The obtained results can be used in the design of a stabilization system with time-varying parameters.
 The next stage of the research is an assessment of the level of complexity of the calculation algorithm when increasing the order of the mathematical model of the control object.