Open AccessCONCEPT OF INTEGRATED AIRBORNE SYSTEMS FOR PROVIDING AIRCRAFT OPERATIONS SAFETY, INCLUDING SYSTEMS FOR MONITORING THE FUNCTIONAL STATE OF THE OPERATOR
Author(s) -
D. S. Koptev,
Ivan E. Mukhin,
Jsc Aviaavtomatika named after V. Tarasov
Publication year - 2020
Publication title -
t-comm
Language(s) - English
Resource type - Journals
eISSN - 2072-8743
pISSN - 2072-8735
DOI - 10.36724/2072-8735-2020-14-12-58-65
Subject(s) - airframe , systems engineering , engineering , aircraft maintenance , scope (computer science) , aviation , adversary , civil aviation , automation , aeronautics , computer science , aerospace engineering , computer security , mechanical engineering , programming language
The development of modern civil and military aircraft is characterized by a rapid increase in the degree of functionality due to the requirements of today and the expansion of the scope of tasks to be solved. In military aviation, this feature is due to a significant expansion of the area of combat employment in terms of the enemy's active opposition, and in civil aviation, it can be explained by a large-scale implementation of technical means of flight control automation and landing under the conditions of high flights traffic in urban areas. In this regard, there was a fundamentally important transition from the separate design of airframes and components to the design of aircraft systems (AS) which represent a single complex system that solves many interdependent and interrelated tasks. Of course, such systems need technical diagnostics, real-time performance testing, and forecasting the remaining resource. This paper presents and describes the main scientific and technical ways to develop and create integrated airborne systems for providing flight safety of aircraft, including systems for monitoring the functional state of the pilot. The article considers the main methods and means for diagnostics and prognostics of the technical condition of an airframe and the critical units of aircraft. Their comparative analysis is carried out and a block diagram of an integrated diagnostic system is proposed. The essence of this system is to implement the procedure for accumulating flight data on the parameters of critical components and units on board aircraft and using a rapid-analysis method that involves monitoring the dynamics of changes in the trend of the controlled parameters in relation to limit values in real-time mode.