Vol 60, No 1 (2017)

A method of the controlled separation of nanosatellites from the carrier rocket by means of the pulsed magnetic field is described. Schemes of the separation device for group launch of satellites and results of exploratory experiments are given. A possibility of practical implementation of the method is considered.

The paper presents an approximate solution of a problem on dynamic behavior of a wing leading edge assembly discretely reinforced by a system of ribs and coated with thermal protection coating.

The paper presents an improved technique and the results of strength analysis for the aircraft structural elements with a structural defect like an arbitrary shape delamination.

We solve the problem of increasing the accuracy of finite-element analysis for the strains of thin-walled open cross section bars eccentrically reinforcing the flat sheet.

We present the results of analytical research of flight dynamics for a flight vehicle that is controlled by the adjustable center of mass in the vertical symmetry plane. The roll oscillations, which appear perpendicular to the symmetry plane due to technological errors, are eliminated by means of control rocket engines, for which a control law is assigned.

The problem of lateral motion stabilization is analytically solved for the fourth-order model of aircraft motion using the method of output signal control synthesis that is based on the control object decomposition. Numerical simulation data are presented.

With the aim of enhancing the simulation of flow processes and dynamics of aircraft motion, the analysis of the appropriate equations and search for new similarity criteria are carried out. New relations are obtained for the equations of aircraft motion allowing for experiments with overweight models under certain conditions.

The paper considers the special features of estimating microaccelerations aboard the Foton-M no. 4 spacecraft, which are connected with the decision on cancelling the spacecraft injection from the reference orbit into the operating one.

A technique for calculating the two-phase flows in the pneumatic injector of the aircraft engine is developed based on solving the model problem, namely, on verification of the two-phase flow model by means of solving the problem of liquid column disintegration under the effect of an incident airflow. We determine the turbulence models that satisfactorily describe the biphase flow processes.

The paper describes a device and a technique of forming the information processing algorithms used in the integrated acoustic monitoring system for jet fuel tanks, intended for monitoring the level, density and mass of liquid products.

The complexity has been evaluated for the devices determined on the basis of the structural pattern proposed, which are implemented on the distributed programmable-architecture computing systems.

A three-step computational technique for calibrating the magnetometers is proposed based on the functional minimization by means of a discrete Newton algorithm. A comparative analysis reveals that the technique proposed allows us to correct the data necessary for determining the azimuth by the Earth’s magnetic field.

The paper deals with solving the problem on calculating the flight loads using a three-dimensional aerodynamic model. An algorithm and an example of calculation are presented.

The paper considers the problems of intelligent control for aircraft engine manufacturing process in accordance with the requirements of GOST R ISO 9004-2010 and the solutions being accepted to change the technological process, its structure and executive program for technological equipment. An approach is proposed to constructing the intellectual environment of technological preparation based on the use of decision support systems and quality assurance of the production process.