Bulat P. V., Dudnikov S. Yu., Prodan N. V., Chernyshov P. S.
Studies conducted between 2018 and 2021 as part of the Aeronet roadmap under the National Technology Initiative revealed a demand for a transport aircraft capable of operating on confined sites without prior preparation, featuring short or vertical take-off and landing (VTOL), and performing horizontal flight in the manner of a conventional airplane. A promising concept involves the use of a load-bearing fuselage composed of specialized propulsive (thrust-generating) airfoils, which–due to their geometry–feature considerable structural depth. This allows for convenient internal placement of cargo containers or a passenger cabin. The application of propulsive fuselage principles enables the development of nearly silent aircraft, as the velocity of the fan-driven jet, expelled for instance through the wing’s trailing edge, can be kept low. The article reviews developments in high-lift and thrust-generating airfoils designed for low-speed aircraft, airships, and transonic vehicles. It traces the evolution of the idea of using aerodynamic surfaces to generate thrust and provides an overview of current research in the field.
Pankratova V. V., Romanov I. V.
. This study examines the effect of boundary layer ingestion from the outer envelope of an airship into the propulsion system on the aerodynamic performance of the vehicle. The interaction between the propeller and the boundary layer on the hull of a soft-type airship is analyzed, with particular attention to various distances between the propeller and the aft section. Experiments were conducted at a freestream velocity of 30 m/s and propeller rotational speeds ranging from 500 to 1000 rpm. The objective of the research is to optimize the aerodynamic characteristics of the airship by leveraging the boundary layer to improve propeller efficiency. The paper presents the experimental model, the numerical simulation methodology, and preliminary results based on an empirical formula for determining propeller diameter, along with the findings of computational analyses. This research is relevant for specialists in aerodynamics, airship design, and the development of lighter-than-air flight systems.
Tretyakov N. K.
The article presents a methodology for assessing the impact of abnormal operation of control actuators – particularly those related to the onboard systems of an unmanned aerial vehicle (UAV) – on its aerodynamic stability. According to the proposed method, critical delay times in actuator response to input signals are determined, both in the absence and presence of unaccounted-for disturbance moments, beyond which the UAV loses stability. Additionally, the maximum permissible constant deviation of control actuators from the zero position is established. The article also outlines further steps for refining the methodology and extending it to other components of the automatic control system.
Siritsa F. V., Tirishchuk D. I.
In the design of aircraft, it is essential to consider the consequences of emergency situations, including impacts from conventional weapons such as small arms. To assess the penetration capability of striking elements from such weapons, a mathematical model of a direct circular conical impactor is applied, representing a bullet as a rigid cone. Two impact scenarios are analyzed: one in which the impactor length exceeds the target thickness and another where it is shorter. The model was verified using the ANSYS Autodyn simulation environment, which analyzes dynamic effects on structures. The deviation between the simulated and calculated results does not exceed 13.5%, which is considered acceptable for high-speed processes. The model’s reliability is demonstrated for thin-walled barriers typical of aircraft structural components. Future work will focus on the investigation of different materials and the development of methodologies for assessing aircraft vibration impact loads from conventional weapons.
Barannikov A. A., Veshkin E. A., Sudyin Yu. I., Mishunin N. N.
The article presents the results of work carried out by the Research Center “Kurchatov Institute” – VIAM in various areas related to the repair of structures made from polymer composite materials. It provides an overview of non-destructive testing methods, including those applied after repairs. The article highlights key repair techniques for polymer composite structures that are widely used in international practice, as well as domestically developed materials and equipment designed for such applications. Is-sues related to workforce training and professional development are also discussed, along with the solutions proposed and implemented by the Research Center “Kurchatov Institute” – VIAM.
Vashchenko А. N., Grigoriev M. N.
This article analyzes the Chinese experience in organizing the development and production of a fundamentally new type of civil aircraft – passenger unmanned aerial vehicles (UAVs) – from a logistical perspective. The emergence of this class of civil aircraft in China is the result of the extensive expertise of Chinese engineers in designing and manufacturing cargo UAVs, as well as both cargo and passenger aircraft equipped with electric propulsion systems. Of particular interest is a critical review of the efforts to identify an effective design solution for a passenger UAV platform, as developed by the AutoFlight company. For Russian leaders in aerospace projects, the Chinese experience in organizational, financial, and marketing support-combined with technical analysis-offers valuable and practically applicable insights.
Karpikov Yu. A., Kireev A. N., Orlov S. B., Trokhov D. A.
Unmanned aerial vehicles (UAVs) equipped with electric propulsion systems are becoming increasingly widespread across various applications. Improving the transport efficiency of such aircraft is a pressing challenge. One promising approach involves reducing the required power output of the propulsion system during takeoff by launching the UAV from a moving vehicle. Ballistic modeling allows for the assessment of performance improvements enabled by this method. Based on the results of numerical simulations, the study explores the potential for enhancing the mass efficiency of UAVs and achieving longer flight ranges compared to conventional runway-based takeoff methods.
Gessen P. A., Lizin A. I., Pavlova V. A., Saenko V. D., Sudakov A. A., Tupikov V. A.
This article explores modern computer vision algorithms applied to the terminal guidance of aerial vehicles. The focus is on approaches that implement 3D reference-to-scene matching for final orientation. Two methods are considered: comparison of a partially reconstructed 3D model with a reference model, and projection of the reference model into image space for subsequent comparison. Both deterministic and neural network-based algorithms for 3D model reconstruction are discussed in the context of terminal guidance. Particular attention is given to image matching algorithms under dynamically changing environmental conditions. The article also highlights a navigation approach based on terrain map and real-scene matching using neural network architectures, such as GeoGAN.
Dryaglev А. O.
This article presents a mathematical justification for modeling internal and external disturbances affecting the sensitive elements of two-stage float gyroscopes, aimed at implementing a novel method for autonomously determining the systematic components of angular velocity drift in a three-axis gyroscopic stabilizer. The approach eliminates the need for additional information sources or modifications to the de-sign of the inertial navigation system. The proposed software and methodological framework for the initial alignment of inertial systems significantly improves operational efficiency by reducing alignment time and increasing the accuracy of gyroscope drift estimation, particularly under conditions where satellite-based radio navigation corrections are unavailable.
Rysin A. I.
The paper presents algorithms for integrated processing of navigation data to determine the position of an object. A particle filter–based algorithm has been developed and tested using real flight data from a helicopter equipped with a standard onboard avionics suite. The feasibility of position correction using information from a digital elevation model (DEM) has been demonstrated. A comparative assessment of coordinate accuracy was conducted using data from various sources.
Gorskiy E. B., Subkhangulov R. I.
The article considers an integrated approach to flight testing of on-board radio navigation and landing equipment, which is determined by the widespread usage of information and measurement systems, automation of processing flight test data combining methods and means of processing and analyzing various equipment into a unified technological cycle. The application of GNSS-based trajectory measurement tools for the characteristics evaluation of on-board equipment is described. Examples of error estimates for the on-board equipment of the ILS, VOR/DME, and a low-altitude radio altimeter are given.
Huseynov O. A.
This study investigates the energy consumption of a fixed-wing unmanned aerial vehicle (UAV) during maneuvering. The focus is on a descent mode in which the UAV, powered by solar cells mounted on its wings, decreases altitude–effectively operating in increasingly dense atmospheric conditions. A control function for flight speed as a function of air density along the flight trajectory is introduced. To determine the optimal form of this function, an optimization criterion is formulated as a target functional equal to the average power required to perform the maneuver. Solving the optimization problem yields the optimal functional dependence of speed on air density, 𝑣 = 𝑓(ρ), which minimizes the average integrated power consumption. The results indicate that for a solar-powered UAV performing a descent maneuver, the optimal flight mode corresponds to adjusting the flight speed according to a specific function of air density, which increases as altitude decreases.