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.

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.

A methodology for the decomposition of complex technical systems of weapons and military equipment and their properties has been developed to increase the accuracy of the assessment of characteristics during tests. General information about operational characteristics of military technical systems, which are controlled during tests and features of their assessment are provided.

The main purpose of the article is to consider the simulation of the natural oscillations of the air assault rappelling system “Kanat-1”. The object of consideration is a set of removable onboard equipment for rappelling air assault "Kanat-1" for landing from the cargo hatch of Mi-8 helicopters. Air assault rappelling system is an oscillating system that has certain natural frequencies of oscillation of the item, which depend on the number of paratroopers on the rope and their placement on it. The airframe of the Mi-8 helicopter has its own frequencies within the ranges of 3.1 - 3.3; 8 - 9; 15 - 17 Hz with which, and their divisibles the natural frequencies of the item should not coincide. In real operating conditions, determining the natural frequencies of the elements of the item under load is problematic. A system of dynamic models is built which allows determining the natural frequencies of air assault rappelling system oscillations at arbitrary placement of up to three paratroopers weighing up to 140 kg each, which can be hung simultaneously on one of the ropes in constant motion while moving the points of contact with the rope. In general, at the maximum load on the rope (three paratroopers), the mathematical model represents a system of three second-order differential equations. Eight variants for loading the rope with paratroopers are considered. The obtained oscillation frequencies of the air assault rappelling system do not coincide with the oscillation frequencies of the helicopter airframe which proves the effectivity of the air assault rappelling system. Recommendations for regulation of frequency characteristics of air assault rappelling system by replacement of a fastening element of a rope to a traverse are developed.

The article considers the problem of improving the methods of testing to determine the flight characteristics of helicopters, taking into account the requirements of European criteria for certification of airworthiness of military aircraft. To ensure interoperability with NATO standards, new standard methods for obtaining and evaluating the flight performance of helicopters have been developed. On the example of determining fuel consumption in assessing the range and duration of the flight considered the basic principles of development of advanced standard techniques. The test methods are based on the use of experimental planning theory using first- and second-order plans. Based on the mathematical theory of experimental planning, regression models of flight technical characteristics of helicopters are compiled and all coefficients of these models are determined. On the basis of the received regression models flight technical characteristics in all range of the used parameters of flights of helicopters of various categories, types and models are calculated. For example, the results of nomogram calculations for determining the kilometer fuel consumption of a helicopter while flying at different speeds in different altitude and climatic conditions are presented. The use of modeling provides increased reliability and accuracy in determining the flight characteristics of helicopters and significantly reduces the cost of testing. Developed advanced techniques, which are adapted to European standards, allow to cover all customer requirements, ie to determine and assess the flight characteristics of helicopters according to the requirements of both national and foreign customers.