Vertical movement control landing system demonstrator

The article provides an approach to the design of the demonstrator control system, which serves to test the engines, control algorithms and navigation of the aircraft at the landing stage. The use of such demonstrators allows you to test individual components of equipment, evaluate the capabilities of the technologies used, develop and verify design techniques and determine the required parameters of the components to obtain the desired properties of the product as a whole. The mechanical design of the demonstrator is a complex system of moving parts relative to each other. The main approach to the synthesis of control systems of such systems is digital modeling. To this end, the article provides a derivation of the dynamic equations of motion of the demonstrator parts based on the use of Lagrange equations of the 2nd kind. When compiling the model, the characteristics of the rocket engines used, fuel consumption regulators, sensors, synthesized regulators and features of the digital implementation of the control system were also taken into account. The results of modeling the movement of the demonstrator at the stage of lifting and landing are presented. The simulation was performed using the Simulink software system. At the modeling stage, the parameters of the regulator were determined, which ensures the vertical movement of the rocket engine platform without overshooting with a minimum steady-state error in the upper position. The simulation results allow us to conclude about the quality of the demonstrator's movement for the implementation of the movement of the demonstrator platform at the stages of simulated takeoff and landing of an aircraft. The entire material of the article is illustrated with the necessary graphic material, references to literary sources confirming the possibility and quality of using certain scientific approaches and technologies are provided.