Abstract
The complex control system of the helicopter-type aircraft is considered, its design is described depending on the requirements for the aircraft and interaction with the interfaced onboard equipment. The main elements of the system are the subsystems of remote and automatic control of the helicopter. In the process of developing such a system, much attention is paid to ensuring a high level of reliability and maintaining the functions necessary for the safe completion of the flight. Therefore, the main requirement for an integrated management system is the probability of its failure in backup management with improved stability of the control object is not higher than 10-9. The authors of the article conducted the analysis of the integrated management system on accutanecost in conditions of failure of the elements included in its composition. In the course of the analysis the assessment of fault safety of subsystems of remote and automatic control is carried out. At the same time, for each system, the influence of obvious and not obvious failures on the change in the controllability of the aircraft and the safety of its flight was considered. Also, the analysis of the system in the conditions of failure of the on-Board equipment of the device. Special attention is paid to the study of the dynamics of the Executive mechanism of the system in the conditions of failure of the onboard hydraulic power supply system. The paper presents the results of studies of changes in the force, speed and quality factor of the electrohydraulic drive at various failures of hydraulic power lines on Board the aircraft. The obtained results can be used in the process of designing complex control systems, studies of electrohydraulic drives and development of methods for parrying the consequences of failures of the helicopter’s onboard equipment with respect to the complex control system, including the creation of algorithms for reconfiguring the system and the logic of controlling the functioning of its elements.
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