Information Technologies in the Design of Aerospace Engineering

The article describes the main features of the use of IT in the development of paragliders that allows, on the basis of a geometric model of a paraglider, to determine its main aerodynamic parameters, and flight simulation using certain aerodynamic parameters. The classification of paragliders is considered (basic types, types and classes). The necessity of automating the design of paragliders is substantiated. An overview of automated paraglider design systems is given, their main advantages and disadvantages are described. The main attention is focused on the problems of aerodynamic design and analysis. The analysis of the reliability of the calculated aerodynamic data is provided.

The general initial positions making basis of technical intention of the maneuverable multimode unmanned aerial vehicle, that determined forming the general configuration and the choice of key parameters are briefly outlined. The overview and reasoning of accepted design and technical decisions are carried out; the principles of their functioning are stated. Methodical features of aerodynamic designing in relation to complexification of the unmanned aerial vehicle of integrated configuration are revealed. Results of verification of design models by results of wind tunnel tests of scale model of analog of aerodynamic configuration are presented. The parametrical geometrical model of the airframe is created, and results of computational researches of alternative designing in selection process of key parameters of lifting system are given. The parametrical geometrical model of air-gas paths is created; the results of iteration cycle of profiling of submerged inlet device and ejector nozzle of step type are presented; the capability of functioning of system of the airframe with integrated power plant is shown.

Regulatory and technical documentation, design features and methods of transport category aircraft fuselage design analysis was performed and identified the need to update design methods and calculate the characteristics of the fuselage using parametric models and integrated design with CAD/CAM/CAE/PLM systems. Within the framework of the proposed method, parametric models of master geometry, aerodynamic flow and mass-inertial characteristics of the fuselage were created, taking into account the design features of transport aircraft. The proposed method was used to study the influence of geometric parameters of fuselage nose and tail sections on aerodynamic and mass characteristics of the fuselage, showing the efficiency of work with parametric models. The use of the method for regional aircraft fuselage design allowed to determine the rational configuration of the nose section of the fuselage and increase the fuel efficiency of the aircraft by 6.4%, reduce the aerodynamic drag of the fuselage by 10%, increase the viewing angle from the cockpit by 10%. Fuselage nose, center and tail sections main parameters determination method is presented. Main theoretical characteristics for determination of optimal parameters of fuselage and its cargo cabin for the transport aircrafts are described. According to the method master-geometry of fuselage of transport aircraft was developed with high accuracy.

In this chapter, the ways to improve the accuracy of blind estimation of noise characteristics in multichannel images are considered. The main idea is to process several channel images jointly in order to suppress the influence of image content. The focus is a method based on the analysis of parameters of DCT coefficients’ distributions obtained for different spatial frequencies in 8 × 8 pixel blocks. Several modifications of this method for color and hyperspectral images are described. Based on the results of numerical simulation obtained for a large database of test images, as well as according to the results of testing on real remote sensing images, it is shown that joint processing of images with high levels of inter-channel correlation allows decreasing the estimation bias by up to several times.

A complex dynamic system is a set of objects (subsystems) with successive modes of their operation, which is described at different time intervals by different differential equations and some finite connections for joining the trajectories of composite parts. Known examples of the practical use of such composite dynamic systems are aerospace systems (AKS) such as “MAX”, “Hotol”, “Zanger”, “Hermes”, “XL-20”, “Hope”, “Clipper”, which are used as an air launch platform for launching satellites and delivering cargo to Earth and space orbits, a rocket launch system for the simultaneous launch of dozens of satellites, as well as a system for group use of unmanned aerial vehicles. The trajectories of such complex dynamic systems in the modern scientific literature are called branched, as they consist of areas of joint motion of components (subsystems) and areas of their individual movement to the target on individual branches of the trajectory. The application and development of existing and promising VTS dictates the need for operational synthesis of trajectories for this type of system, as allowed by both computing and telecommunications. Problems of operational optimization of the management process of these complex technical systems are recognized in the world as relevant from a scientific and practical point of view. This paper considers the synthesis of algorithms for optimal control of a group of unmanned aerial vehicles and a launch vehicle when launching a group of navigation satellites into orbit.

In the section “Using Krotov’s functions for the prompt synthesis trajectory of intelligent info-communication robot” proves sufficient conditions for optimal control of a deterministic compound dynamic system, which is considered as a model. Info-communication robot performs intellectual actions in automatic or semi-automatic mode to collect information and transmit it to the control center. Mobile sensors are considered as information elements of info-communication robot. Telecommunication aero platform is considered as a telecommunication element. The proved conditions could be considered as a theoretical basis for the algorithm’s construction of weak artificial intelligence—intelligence of action, which allow to prompt calculate the trajectories of the constituent elements of info-communication robots in conditions of uncertainty. Sufficient optimality conditions are proved by using the Krotov’s modified expansion principle and the invariant immersion method in combination with the Krotov’s function method and are formulated as a Krotov’s modified expansion principle for deterministic compound dynamical systems. The expansion principle formulated for compound dynamic systems with the scheme of trajectory branches in the form convenient for construction of computational algorithms containing central and lateral branches, without interaction of subsystems after division and also formulated the expansion principle for the simplest compound dynamic system with consideration of subsystems interaction. Model example of a branched trajectory calculation of info-communication robot is given. The practical significance of the obtained conditions is that on their basis it is possible to develop computational procedures for the prompt calculation of optimal branched trajectories of infor-communications robots.