P. V. Bulat, S. Yu. Dudnikov, N. V. Prodan, P. S. Chernyshov
This paper presents a historical review of key mathematical models and the evolution of direct, inverse, and mixed methods for designing high-lift profiles featuring surface air suction and blowing through slotted nozzles. It traces the development of approaches to solving inverse ill-posed boundary value problems in aerodynamics. Inverse ill-posed methods for designing aerodynamic profiles are discussed in the context of developing transport aircraft with a lifting propulsive fuselage and low-aspect-ratio wings.
A. A. Gordeev, D. E. Donovsky, D. A. Kaymakov, A. E. Yurchenko
This paper presents the results of determining the rotational and unsteady aerodynamic force and moment derivatives using the LOGOS software suite and a panel method-based tool for rapid aerodynamic analysis. Numerical simulations were performed for the Standard Dynamics Model (SDM). The obtained derivatives are compared with wind tunnel test data and with results from other computational tools available in open sources.
I. Ya. Baranov, A. V. Koptev
Continuous operation of X-3 ion thrusters, with a thrust of 5.4 N and a power output of 100 kW, can significantly reduce the flight time to Mars. However, conventional power sources based on solar panels have several limitations. This paper explores a concept for generating electric power to drive ion propulsion systems via laser-initiated hydrogen–boron nuclear fusion, which proceeds without neutron emission. The feasibility of initiating the hydrogen–boron reaction using a compact, commercial femtosecond fiber laser is substantiated. The paper outlines the conditions under which the hydrogen–boron reaction can be efficiently achieved with a single laser-powered energy source rated at approximately 100 kW. The use of multiple laser-based energy sources of this kind would enable the simultaneous operation of several ion thrusters.
Yu. S. Afonina, O. K. Ovchinnikova, E. Yu. Yaroshevskaya
This paper presents a mathematical model of processes in an external heat supply engine (gamma-type Stirling engine). A virtual model was developed to illustrate the mechanics of engine operation alongside a description of the associated thermodynamic processes. A key feature of the study is the inclusion of heat losses inherent in real engine operation and the visualization of both the engine’s mechanical motion and thermodynamic cycles depending on the energy input intensity.
A. Yu. Andryushkin, Yu. N. Ivanova, E. S. Nikiforova
To ensure aircraft quality, dimensional analysis is performed on units and assemblies, and the assembly method is selected based on the level of interchangeability. The number of assembly units in the manufacturing batch and the number of links in the dimensional chain affect the assemblability of components. For calculating multi-link dimensional assembly chains, the use of a probability-theoretic method is recommended. This paper proposes a methodology for estimating the probability of a favorable dimensional combination of elements within the assembly chain. The method accounts for the number of assembly units in the batch, as well as the confidence intervals of the true mean and the true standard deviation of the size of each chain link. A sample calculation of a multi-link assembly chain is presented, demonstrating that the probability of a favorable dimensional combination increases with the number of units in the manufactured batch.
N. D. Maksimenko, Yu. A. Nabokov, E. N. Nikulin
This paper presents the results of finite element modeling of the volumetric stamping process of a glass-type part using solid-state and shell calculation models. The analysis of the stress-deformable state of the 11YUA steel billet during the deep drawing operation is performed. The results obtained by modeling the technological process are presented in diagrams of normal and tangential stresses in the Cartesian coordinate system. The simulation of the deep drawing process was carried out to evaluate the stresses that occur in the workpiece at the time of drawing with initial and boundary conditions that coincide with the real ones. The simulation was carried out in the LS-DYNA numerical simulation package.
G. O. Baranov
The purpose of this work is to summarize the experience of using qualified tolerances with minimum material and interaction requirements in the design of parts obtained by cutting, as well as to analyze the possibilities of assigning qualified tolerances with minimum material and interaction requirements in accordance with actual standards. The article provides examples of parts on which the influence of each of the above requirements when assigning qualified tolerances is considered. This article is recommended for understanding the feasibility of assigning qualified tolerances with the above requirements.
A. V. Khitrina, D. A. Kolyvanova
This paper addresses the problem of reducing the overall dimensions of aircraft by means of folding lifting surfaces. It outlines the main technical requirements for the deployment system of aerodynamic surfaces and presents its structural diagram, which may include a power actuator, a damper or deployment speed regulator, a transmission mechanism, and locking devices. Numerical simulation results confirm the operability of the developed mechanism and its individual components.
А. I. Tsybriy, А. V. Guskov
This paper analyzes the launch process of unguided aircraft rockets from an airborne carrier, breaking it down into stages and identifying the associated physical phenomena, the parameters of which exert different types of impact on the carrier (aircraft). The main stages during which the carrier is subjected to loads are examined. During the rocket’s ignition and its movement along the launch rail, the carrier experiences mechanical loads. As the rocket exits the launcher and until it moves beyond the effective range of the exhaust jet, the carrier is exposed to high-temperature combustion products of solid propellant. Once the rocket moves further away, its impact on the car-rier ceases. The analysis provides a basis for further calculations aimed at improving aviation weapon systems.
D. I. Tirishchuk, F. V. Siritsa
Recent advances in radar homing head technology have significantly improved the accuracy and effectiveness of interceptor missiles against aerial targets. This is especially critical in the context of protecting aircraft, where appropriate countermeasures are needed to reduce the likelihood of interception by hypothetical enemy missile defense systems. This article presents a reinforcement learning–based strategy for deploying decoys to enhance the probability of aviation strike assets penetrating hostile air and missile defense systems, as well as to improve their survivability during engagement. The strategy involves coordinated actions of decoys trained using MADDPG (Multi-Agent Deep Deterministic Policy Gradient) and MATD3 (Multi-Agent Twin Delayed Deep Deterministic Policy Gradient) algorithms. The decoys operate under a leader–follower architecture, employing various formation patterns to ensure effective intra-group coordination. The approach enables dynamic situation assessment across multiple parameters, including deployment zones of decoys, interceptor missile launch vectors, and the maximum velocities of both decoys and interceptor missiles operated by the hypothetical adversary’s integrated air and missile defense systems.