Том 60, № 2 (2017)

In this paper, it is proposed the flight duration to be assessed by the potential value and the helicopter number. The data on the available power and the relative efficiency for a number of multicopter models are provided.

The discretization of the boundary value problem for laminated composite shells is based on the finite difference approach using the regular mesh with the constant grid step and the difference operators of the second order of accuracy. The dynamic relaxation method is proposed for the solution of the nonlinear problem. The evolutionary equations of the dynamic relaxation are constructed, and the optimum parameters of the converging linear iterative process are estimated.

A comprehensive approach is proposed that allows modeling the flight of helicopter over the entire range of flight speeds. We also consider a technique for optimizing the trajectory corresponding to the flight task taking into account the terrain and operating conditions.

The helicopter main rotor in forward flight is considered in this paper. The results for rigid blades and elastic blades are compared by the method of coupled simulation. The influence of the structural damping coefficient on the blade in-flight deformation is also considered.

The work comprises numerical investigation of the influence of the deflection angles of the trailing edges of longitudinal ribs on the gas-dynamic behavior of vane cascades of a thrust reverser located in the secondary flow of a bypass turbofan engine (BTFE). Verification of the numerical model was performed on the basis of experimental research.

This paper considers the problem of increasing the fuel efficiency of a diesel aircraft engine and decreasing the smokiness of its exhaust gases (EG) by means of the experimental determination of optimum compression ratio and combustion chamber dimensions. Necessity for matching of these parameters in a wide variation range of load and crankshaft speed was identified and proved.

The paper studies different types of dampers for rotor supports of gas turbine engines (GTE). The advantages of hydrodynamic dampers are shown. Hydrodynamic dampers for GTE rotor supports are studied. A new design and technique of calculation are proposed for an adjustable hydrodynamic damper.

The layout of the power plant on the wing of a twin-fuselage passenger aircraft with an odd number of engines is compared with the single-fuselage aircraft-prototype. The advantages of the twin-fuselage layout being proposed are revealed.

A mathematical model describing the temperature distribution in a non-cooled nozzle shell was constructed. Analysis of this model showed that the extreme temperatures are permissible for some modern and promising heat-resistant composite materials.

Numerical analysis of thermal conditions for a two-phase closed thermosyphon using the ANSYS FLUENT software package has been carried out. The characteristic temperature distribution, streamlines and velocity vectors for various heat loads have been obtained. The study has found the possibility of using the software package for analysis of the energy transfer processes at high thermal loads.

We consider the task of predictive information design allowed for improvement of flying qualities in precise tracking tasks, in particular for the landing of an aircraft, the dynamics of which is characterized by the transportation time delay.

The effect of detuning the partial frequencies of MEMS gyroscopes on its amplitudefrequency response is investigated. The formulated mathematical model allows defining requirements for the tolerances on gyros parameters, which determine the values of gyros partial frequencies, at the design stage of the sensor.

A novel processing scheme for cyclic production of composite folded structures from continuous sheet of prepreg is presented. A circular transformable mandrel is used as a shaping unit. A technique of calculating the shaping unit parameters is developed. It is based on the analysis of facility kinematics using a vector model of four-axis folded structures transformation process.

The paper presents the methods and algorithms for positioning the dynamic (moving) objects using the oblique-incidence ionospheric sounding by chirp signals. Full-scale experiments have been performed to determine a distance to an object and its location.

In this paper, it is shown that the optimal injection velocity in the plane critical point is the finite one at the arbitrary velocity distribution on the outer edge of the boundary layer.