Vol 59, No 4 (2016)

A task of minimizing the guide length of a ground catapult was set in order to ensure the mobility for unmanned aircraft systems. A scheme with reusable supply of the working fluid into the pneumatic drive cylinder was proposed. A method of parametric optimization of dynamic performance for a catapult was formulated. The method and models were verified with respect to the basic integral indicators.

In this paper, we consider an example of estimating and comparing the efficiency of different concepts for a high-altitude unmanned aerial vehicle (UAV) under diversity of efficiency criteria.

This paper considers a beam with a technological longitudinal section on the level of the gravity center of the cross section that is loaded by a vertical concentrated force. We study the structure durability depending on the load amplitude and the initial crack length.

This paper considers the axisymmetric transverse vibrations of aircraft nonuniform structural elements that are introduced by a thermal shock. Analytical solutions have been obtained and their numerical analysis has been performed.

A method of finding the aircraft optimal route by means of task-oriented replacement of the functional being optimized is proposed.

In this paper, we consider a task of efficiency improvement for the aircraft flight altitude stabilization by the nonlinear effects in control laws and angle of attack limiting.

An approach that can be used for modeling the situation of unanticipated yaw is presented. A software is developed that allows us to obtain the helicopter equilibrium attitude at an arbitrary speed and consider the helicopter dynamics under influence of a certain disturbing factor.

A method of imitating the helicopter flight on a flight simulator is proposed for the vortex ring state hover flight. Algorithms of artificial neural networks are used for the modeling. The method allows modeling the characteristics of the main rotor's loading during a dangerous descent of the helicopter.

A calculation method is proposed for estimating the mode, when the thrust reverser jet starts reattaching to the engine nacelle in the presence of an approaching flow.

A combined method for calculating the trajectories of suspended particles in the hydrodynamic velocity fields is proposed. The method utilizes capabilities of existing CFD codes and parallel computing on a computer with a graphics card that supports CUDA technology. The software package that implements the method is described.

This paper presents the results of the model studies of the reverse jet distribution limits in the air cross-flow, performed in the wind tunnel, as well as the conditions of the jet’s ingestion into the engine air intake in the context of aircraft configuration, when the engines are the input of engines.

This paper considers the problem of reducing the nitrogen oxide emissions in exhaust gases (EG) of the diesel aircraft engine by exhaust gas recirculation (EGR). The main directions in improving a working process of diesel engines with EGR system were formulated.

Based on analyzing the operating conditions for high speed rolling bearings of aircraft engines in a medium of low viscosity fuel components, we substantiated a combined model of calculating the bearing life with respect to two criteria of efficiency, namely, the contact fatigue resistance and wear resistance of their working surfaces. An algorithmic procedure and special features of calculating the durability with respect to these criteria were shown.

The paper describes a technique of the integrated research into thermal radiation of heterogeneous combustion products. We have examined the dependence of optical properties, radiation characteristics, and emission characteristics on the key determinant factors and parameters at the nozzle exit of a model rocket microengine. We have compared the experimental spectrum with the calculated spectrum taking into consideration the radiation scattering from the combustion chamber on the condensate particles (the spotlight effect). The correction value for thermodynamic temperature has been found out.

We consider the problem of measuring the altitude and speed parameters aboard a helicopter, as well as ways to improve the noise stability and accuracy of measuring at low and nearzero flight speeds at the expense of using the air flow data of the main rotor vortex column, the principles of complexation and filtering.

This paper examines how the forming accuracy of the compressor blisk aerodynamic surfaces depends on the number of controlled movements by a cup mill during the processing that is needed to solve the problem of identifying the selection of equipment and manufacturing strategies in the production of the most complex, time-consuming and expensive parts in engine manufacturing.

The paper describes the validation methods of the novel domestic CAE system calculation of the composition materials for example of the laminated plates when calculating natural frequencies.

Approaches to forecasting and ensuring the intrasystem electromagnetic compatibility of the UAV avionics are proposed.

The method proposed allows the two-component jet-jet gas nozzles with outer mixing to be efficiently designed with a required accuracy for practice.

This paper describes a technique of measuring the geometric parameters of products by using the software-based laser coordinate measuring systems. The required parameters and measurement procedures are defined.