Development of a Launch Vehicle Control Algorithm at the Initial Flight Part in Case of one of the Engines

Authors: Trifonov M.V., Altshuler A.Sh., Bobronnikov V.T. Published: 17.02.2019
Published in issue: #1(124)/2019  

DOI: 10.18698/0236-3941-2019-1-16-29

Category: Aviation and Rocket-Space Engineering | Chapter: Aircraft Dynamics, Ballistics, Motion Control  
Keywords: launch vehicle, launch complex safety, engine failure, emergency displacement, optimal regulator, quadratic criterion

The object of study is the control system of the launch vehicle (LV) at the initial phase of flight when an emergency situation occurs due to failure of one jet engine. It is assumed that when the situation occurs, the LV has to be "allocated" from the launch pad in a horizontal direction along a certain trajectory to the pre-selected area, avoiding a collision with the of great importance constructions of the launch complex, to perform further procedures for the liquidation of the LV. The aim of the study is to develop an optimal regulator of the LV control system, providing the implementation of an emergency flight of the LV. For the formation regulator this paper proposes a modified version of the Letov's method of analytical design of regulators (ACOR) problem solution. The peculiarity of the formulation of the problem as the ACOR problem is the dependence of the system outputs from the input control variables. The efficiency of the control is evaluated using the integral-terminal quadratic criterion. The motion of the LV at the considered flight phase is described by simplified linearized equations. The performances of the proposed optimal regulator is confirmed by compareson of simulation results obtained with the simplified and the detailed spatial models of the LV controllable motion


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