The problem of flight tsafety , without regard to swift scientific and technical progress in industry of aviation equipment, become exceptionally sharp in our time. The statistical processing of empiric data is an actual task in monitoring of process of exploitation of propulsion MODULE of the Armed Forces of Ukraine and determination of tendencies of technical service and repair, directions of modernisation of armament and military equipment. The article considers the approach of the systems to the evaluation of reliability and safety of flights in relation to accomplishment of combat missions and preventionof aviation accidents. A methodological approach to the mathematical processing of statistical information for the period 2016-2019 on malfunctions was developed. The quantitative evaluation of their level is conducted on the generally accepted standardized indexes (statistical and probabilistic), specific methodology was here used. Index "parameter of failure flow" that characterizes the level of operating reliability and index "level of accident rate" that characterizes safety of flights were used in this methodology on ІСАО recommendation. Certain trends of changes of these indexes, the “upper control limit of reliability" and the considered conception of acceptable level of safety performance ( ALoSP) are expected for future periods for the different types of helicopters. On the base of operating data, the prognosis indexes expected, "upper control limit of reliability" on 2020 for the specific types of helicopters. As expected, according to obtained results, for all types of helicopters the mean value of this index will make not more than 4,3 failures per 100 flight hours. In accordance to conception of "acceptable level of "ALoSP" it is possible to distinguish three levels or "triggers" of flights safety : Acceptable level (Acceptable), special purpose level (Target), Critical level (Alert). These "triggers" are calculated taking into account the mean value of statistical sets of data about failures (for the last 3 years) and standard deviation that gives an opportunity to define the necessary additional measures of management to provide safety of flights. Authors came to the conclusion that conception of ALoSP is suitable for the evaluation of efficiency to provide flights safety of aviation of the Armed Forces of Ukraine with implementation of necessary adaptation to the existent terms of application of UKR aviation.

The article is devoted to the simulation of parachuteless airdrop system from helicopters during tests. The issue of testing the equipment strength for parachuteless airdrop is considered in detail. Simulated mathematical modeling of the structural strength characteristics of the parachuteless airdrop system was performed. An assessment of the power strength elements of the removable on-board equipment for parachuteless airdrop design from helicopters is given.

The article provides information on the concept of assessing the resource of power elements of the design of a specialized armored vehicle during testing and its adjustment to the standards of NATO member states. It involves the implementation of simulated mathematical modeling with an evaluation of the static and dynamic characteristics of the vehicle's power structure. When simulating fatigue damage of a structure, the hypothesis of a linear damage summation rule is used to more reliably determine the life of a vehicle. During field tests the use of modern hardware and software for measuring the actual characteristics of loading a car when driving on different types of roads is proposed.

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The actual problem of the strength properties evaluation of a special armored vehicle "NOVATOR" designed for the transportation of personnel and special cargo is considered. When an armored vehicle roll-over, the strength of the capsule must ensure the preservation of living space for the crew. To evaluate the strength of the capsule when vehicle rolls-over, in the program Solid Works a spatial model of the fabricated hull of the armored capsule, taking into account the materials of all parts, was developed. Calculations of the stress-strain condition of the capsule and its frame are performed. To analyze the stress-strain condition of the armored vehicle capsule due to static and dynamic loads the finite element method was used, which is implemented in the program SolidWorks Simulation. Simulation of the structural strength by different types of loads was performed in order to adequately evaluate the strength of the capsule. The results of calculations and simulation of the capsule design showed its insufficient strength, which can lead to significant spatial deformations of the capsule hull and the threat to human life. It does not meet the requirements of UNECE Regulation №66 for motor vehicles to transport people in terms of the strength of their superstructure. To ensure the required strength of the capsule the analysis of design flaws was performed. The main causes of strength loss and location of critical stresses and strains by sensing the model are identified. Recommendations were given to the manufacturer to increase the strength of the capsule and provide the necessary safety margin of the structure.