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The analytical and experimental studies of the aircraft’s supersonic air intakes have been carried out. An integrated approach to the gas-dynamic designing of aircraft’s supersonic air intakes that eliminates the scale effect problem of a wind tunnel with a small-sized testing area is proposed. The designing approach accelerates the development process and reduces the resource intensity due to the rational distribution of tasks between numerical and physical experiments. The results of the unique tests of the scaled ramjet’s air intake physical model in the supersonic wind tunnel are presented.

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The purpose of this paper is to develop a method for forming the shape of compact ground launching devices (GLDs) unmanned aerial vehicles (UAVs), which includes three stages. Firstly, the choice on the basis of the theory of dimension and similarity of the closest analogue of the design object based on world experience gained in this field. Secondly, the creation of a comprehensive model of the working process of GLD and a universal method for its numerical implementation. Thirdly, the solution to the problem of optimizing the dynamic characteristics of GLD. At the described stages of the formation of the shape of an GLD UAV, a statistical analysis of the technical perfection of known analogues of UAV launch systems, methods of the theory of similarity and dimension in mechanics, methods of numerical simulation of the working process, and also methods of conditional parametric optimization are used. The undoubted importance of the problem of the equivalent development of the components of the UAS, consisting of an aircraft and a launch system (catapult). The traditionally non-priority status of GLD in the general cycle of the complex design program is also known. A systematic solution to this problem lies in the mainstream of creating common approaches, one of which is contained in this article. The proposed method of forming the appearance of compact GLDs UAV can be extended to a wide class of starting systems containing a thermal expansion machine and a mechanical component. In the presented form, the method is not applicable to systems of air, aerodrome and manual launch of UAVs. A method has been developed for the formation of the shape of GLD based on the energy relations of the criterion type between useful functions and the corresponding costs, with subsequent verification numerical studies of the launch processes based on specially created technology of a computational experiment, as well as optimization of the dynamic characteristics of GLD. The method of forming the shape of compact GLD is universally applicable to any type of catapults, regardless of the type of transmission and drive, since many particular forms of organization of the working process are generalized using the criteria of energy perfection, a comprehensive physical and mathematical model and normalization of the starting overload.

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