One of the perspective directions of the development to modern aviation is connected with designing and producing unmanned aerial vehicles (UAV) of various functionalities for applying in military and civilian spheres. The syntheses of UAV control systems, regardless of their type and purpose presumes the creation of adequate mathematical models, first of all adequate aerodynamic mathematical models. In the paper results that forms and justify the aerodynamic mathematical model and as well as the results of building a general mathematical model of the longitudinal movement of the perspective UAV are presented. In the article on the basis of the analysis of the reasons of involvement in performance of research and development works the basic risks of the indirect factors and possible negative scenarios of performance of projects of creation of samples of aviation equipment are defined. Based on the results of the analysis of risk-forming factors, the risk indicators of the projects of creation (modernization) of aircraft models are substantiated. A methodical approach to the criterion assessment of risk indicators at the stages of research and development work on the development (modernization) of aircraft is proposed

During the design and construction of new products, it is necessary to evaluate their effectiveness and technical thoroughness already at the preliminary design stage. For unmanned aerial vehicle systems (hereinafter referred to as UAVs), one of the areas of such assessment can be the ratio of the overall tactical and technical requirements to the estimated flight and technical properties of the prospective model to the characteristics of the best analogues. However, such estimates are associated with a high degree of uncertainty in the early stages of UAV design. There is a question of a priori evaluations with the use of multicriteria approaches arises. At the same time, the use of multicriteria methods of evaluation of complex technical systems, such as UAVs requires the use of large amounts of data with significant time consumption, so the search for comprehensive evaluation indicators, as proposed in this article, is considered to be relevant. This article deals with the complex evaluation of the technical efficiency of unmanned aerial vehicles equipped with turbojet propulsion system (hereinafter — turbojet). For this purpose, the composition and content of the relevant methodological apparatus for assessing efficiency and a comprehensive indicator of technical excellence of unmanned aerial vehicles with turbojet engines are substantiated. In contrast to existing approaches, the obtained comprehensive indicator allows to evaluate UAVs on the minimum necessary information about its flight data, which allows to use the proposed methodological apparatus for assessing UAVs already at the design stages. In accordance with the proposed methodological apparatus, the actual comparative assessment of the UAV group with turbojets was carried out. A differential scale for evaluating the technical perfection of UAVs has been constructed. This approach, in the opinion of the authors, will allow to increase the reliability of comparative evaluations of UAVs with turbojets for the minimum required amount of output data.

A launch from a ramp is applied in order to increase the effectiveness of unmanned aircraft. To attain this goal, the kinematic parameters of movement during a UAV launch from a ramp are analyzed, formulas to determine these parameters are formulated, and a method for calculating rational geometrical parameters of a ramp, which provides a safe lift-off of a UAV with the specified flight data, is used. This paper considers the advantages of a UAV launch from a ramp and the development of algorithms that help to calculate the characteristics of a UAV launch from a ramp.

The paper presents one of the perspective directions of the development to modern aviation, which is connected with designing and producing unmanned aerial vehicles (UAV) of various functionalities for applying in both military and civilian spheres. The syntheses of UAV control systems, regardless of their type and purpose presumes creation of adequate mathematical models, first of all adequate aerodynamic mathematical models. In the paper results that forms and justify the aerodynamic mathematical model and as well as the results of building a general mathematical model of the longitudinal movement of the perspective UAV are presented. Also factors that forms the mathematical model on given aerodynamic, geometric, mass and inertial data for a hypothetical perspective altitude long-range UAV are submitted. Assessment of the impact of these data on the dynamic, temporal, and logarithmic frequency response UAV also has been given in this paper.