Description: The subject matter of the article is the processes of synthesis of the optimally distributed structure of aircraft flight and navigation complex for solved applied problems of improving the effectiveness of functioning in conditions of destabilizing impacts. The goal is to develop a method for improving the effectiveness of optimally distributed structure of aircraft flight and navigation complex in conditions of unpredictable destabilizing impacts. The tasks to be solved are: 1) to develop a method of optimal distribution of structure of aircraft flight and navigation complex on the indicators of functional stability in order to limitation the cost; 2) to select an effective algorithm for optimization it; 3) mathematical modeling of optimal structures selected for the study of aircraft flight and navigation complex. The methods used are: mathematical optimization models, method of synthesis of aircraft flight and navigation complex using the mathematical methods of the structure optimization by the maximum criterion of the functional stability parameter with a limitation of the system construction cost. The following results were obtained: 1) there were substantiated set of criteria acceptable to the estimation of various variants of the system construction (quality indicators) of aircraft flight and navigation complex with determination of the advantage criterion; 2) choice of optimization method; 3) definition of the area of effective options based on consideration of the whole set of criteria, reflecting the requirements for the flight and navigation complex system; 4) the choice of optimal options regarding to a set of criteria with the definition of a rational variant by applying a priority advantage criterion with an additional definition of the stability reserve, as well as the area of stability in the phase space of aircraft flight and navigation complex system parameters. The scientific novelty of the results obtained is as follows: it was improved the method for increasing the effectiveness of aircraft flight and navigation complex in conditions of destabilizing impacts thorough realization of the synthesis of its optimally distributed structure by applying methods of optimization by the maximum criterion of the functional stability parameter with a limitation of cost. Unlike the existing ones, this proposed method allows to choose from a variety of acceptable options a compromised and at the same time the most rational one considering possible extraordinary situations under conditions of destabilizing impacts by taking into account the probabilistic nature of the power as a plurality of connections between elements of flight and navigation complex system.
Keywords: flight and navigation complex, destabilizing impacts, functional stability, synthesis of optimally distributed structure