Journal articles: 'Helicopters Design and construction'

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Bisták, Andrej, and Zdenka Hulínová. "Construction of ropeways in Slovakia in terms of pre-construction design using helicopters (case study)." MATEC Web of Conferences 263 (2019): 01002. http://dx.doi.org/10.1051/matecconf/201926301002.

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Ropeways usually provide access to locations inaccessible to other means of transport. Due to this fact, the construction of ropeways is extraordinarily taxing in terms of both, technology and logistics. The site location is often in terrain difficult to access, which often precludes deployment of common construction mechanisms in ropeway construction. In such case, it is advisable to deploy a transport mechanism independent of the terrain – a helicopter. Functioning as “flying cranes“, the helicopters have been used in construction industry in Slovakia for six decades now. Having amassed positive experience, even the “conventional“ construction industry of the time, especially its ropeway transport segment, started to use the benefits of helicopters, with helicopter deployment subsequently gaining ground and becoming the mainstream technological procedure. Ropeway construction can hardly be feasible without them even nowadays. Throughout the history of helicopter deployment in construction industry, a constant search of improving the efficiency of their work has been under way, necessitated by the helicopter’s sensitivitiy to weather conditions and work procedures alike. The paper presents an analysis of the factors affecting helicopter operation together with a proposed methodology of modeling their work in simulation models and the benefits of such approach.

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KACHEL, Stanisław, Robert ROGÓLSKI, and Jakub KOCJAN. "Review of Modern Helicopter Constructions and an Outline of Rotorcraft Design Parameters." Problems of Mechatronics Armament Aviation Safety Engineering 12, no. 3 (September 30, 2021): 27–52. http://dx.doi.org/10.5604/01.3001.0015.2427.

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This work contains the results of a modern helicopter construction analysis. It includes the comparison of almost seventy rotorcraft constructions in terms of size in line with EASA requirements – large and small helicopters. The helicopters are also divided because of a mission purpose. The proposed division for large aircrafts is: transport, multipurpose, attack and for small aircrafts: observation, training, and utility. The aircraft construction features are described. Average dimension values of airframes and rotors are shown. Helicopter rotor arrangements are presented in terms of an operational purpose. Next, the rotorcraft design inputs are described. The mathematical formulas for design inputs are given. The ratios are calculated and gathered for the compared aircrafts. Correlation between the analysed parameters is presented on charts. Design inputs are also presented in the paper as a function of MTOW. The function trends are determined to provide an evaluation tool for helicopter designers. In addition, the parameters are presented as possible optimisation variables.

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Singh, Anvinder, and Varun Sharma. "DESIGN ANALYSIS AND CONSTRUCTION OF ENERGY HARVESTING COAXIAL HELICOPTER." Aviation 17, no. 4 (December 24, 2013): 145–49. http://dx.doi.org/10.3846/16487788.2013.861230.

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With the growing need for technology, the tendency for errors has increased many times, which often results in loss of human lives. Our main aim of this paper is to show the implementation of a coaxial rotor aerial vehicle that can be controlled by a radio frequency transmitter. The helicopter is capable of manoeuvring in an area where real helicopters cannot. The area could be a flooded region, a place hit by an earthquake, or a building on fire. The main aim is to transmit video of that place to a base station by the camera attached to the helicopter. Various factors required to make a safe and successful coaxial helicopter are discussed and extensive flight testing proves that this flying machine is better in efficiency and performance than a traditional single rotor aerial vehicle. The relation of flight parameters like torque, induced power, rpm, pitch, and total power are discussed. A piezoelectric sensor is used to determine the vibrations occurring in the body so that they can be minimised. A successful attempt to convert the vibrations into a charge by piezoelectric energy harvesters is made.

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Davidson, Gary, Tim Roberts, and Darren Savoye. "Skid Helicopters on High-Speed Craft." Journal of Ship Production 21, no. 02 (May 1, 2005): 108–25. http://dx.doi.org/10.5957/jsp.2005.21.2.108.

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Helicopter decks are common throughout the commercial and military shipping industries and also the offshore industry. Construction in steel and aluminum is common. Helicopter decks on high-speed craft are not common. The first known helicopter deck installed on a high-speed craft was on an Incat wave-piercing catamaran, HSV X1, Joint Venture, which saw service during the recent Gulf war and is currently still in service with the US Army. Following successful construction and NAVAIR certification of Joint Venture, a more advanced aluminum deck, certified also by NAVAIR and Naval Sea Systems Command (NAVSEA), has been fitted to HSV 2 Swift, which is the latest Incat 98 meter "SeaFrame" HSC. HSV 2 Swift is in service with the US Navy. This paper will focus on the design challenge that came about on HSV 2 Swift in the design of the deck to land and park skid type helicopters as opposed to a helicopter with pneumatic tires. High-speed craft are by their nature innovative, and new solutions to old problems are constantly being experimented with to ensure that the tenets of high speed and high efficiency are optimized. Weight minimization is the most critical performance aspect of a high-speed craft, and conservative or simplified analysis is not practical or economic. A high-speed craft relies on accelerating through hump or critical speed to obtain the high operating speeds of around 40 knots and greater. The ability to operate above hump speed is absolutely reliant on the weight of the vessel. Unnecessary weight on the vessel that does not have absolute mission or operation justification adversely affects the ability to operate above hump speed. Aluminum creates additional and very different challenges compared to a design in traditional steel. Alternative details and construction techniques are required for successful design in aluminum in terms of fatigue and ultimate strength. One innovation common in high-speed craft is aluminum extrusion of a top hat form. The top hat offers big savings in terms of ultimate strength and reduction in mass while keeping weight to a minimum. To aid in verifying the design of the Helo deck extrusion on HSV 2 Swift (Incat Yard 061) for the AH-1 and UH-1 helicopters (H-1 series skid type helicopters), analysis and physical testing were carried out. There had been some doubt that conventional hand calculations were suitable for a top hat style extrusion. The analysis and testing proved that extruded aluminum sections of top hat design are suitable for the H-1 series helicopter skid loading and that permanent deformation was negligible at the design load and even at significantly above the design load. The physical test is also further evidence to support the use of welded 6000 series extrusion in high-speed military vessels. Original design of the deck extrusion revolved around class rules, linear static finite element analysis (FEA), and military codes. Later analysis involved nonlinear FEA, further military code calculations, first principles hand calculations based on available text, and physical testing.

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Cai, Guowei, Lin Feng, Ben M. Chen, and Tong H. Lee. "Systematic design methodology and construction of UAV helicopters." Mechatronics 18, no. 10 (December 2008): 545–58. http://dx.doi.org/10.1016/j.mechatronics.2008.05.011.

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Balakchina, O., and V. Shalenny. "Design organization and construction implementation of the installation and reconstruction technology using helicopters." IOP Conference Series: Materials Science and Engineering 913 (September 12, 2020): 042039. http://dx.doi.org/10.1088/1757-899x/913/4/042039.

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Soldatkin, V. M., V. V. Soldatkin, A. V. Nikitin, and E. O. Ariskin. "Measuring System of Air Parameters of the Helicopter with a Stationary Receiver a Flow, Ion-Label and Aerometric Measurement Channels." Mekhatronika, Avtomatizatsiya, Upravlenie 19, no. 11 (November 8, 2018): 744–52. http://dx.doi.org/10.17587/mau.19.744-752.

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It is shown that the known limitations on the measurement of air parameters on board the helicopter due to significant aerodynamic disturbances introduced by inductive flows of vortex column of main rotor. This determines the need to create the means of measurement, taking into account the aerodynamics and dynamics of the helicopter flight. The known direction of overcoming these limitations is the use for measuring the information of aerodynamic field of vortex column of main rotor and its perception by means of the stationary multi-functional aerometric receiver. However, the need to protect a large number of full-pressure tubes installed in the flow channel of the multifunctional aerometric receiver, strict requirements for the identity and stability of the characteristics of the large number aerometric channels, complicate the design, reduce reliability, increase cost, inhibit the use of the air parameters measurement system on helicopters of various classes and purposes. Principles of construction, functional scheme, features of perception of primary information of measuring system of air parameters of the helicopter with the stationary receiver of a stream, ion-label and aerometric measuring channels are showed. Algorithms for processing primary information at various stages and flight modes, including: in the parking lot before the launch of the power plant and when rotating the rotor, when taxiing and maneuvering on the earth’s surface, on takeoff and landing modes and when flying at low speeds, at flight speeds, when the stationary receiver of primary information leaves the zone of the vortex column of the rotor using ion-label and aerometric measuring channels, are presented. It is shown that the proposed approaches to the construction, models and algorithms for processing the primary information of the measuring system air parameters of helicopter with ion-label and aerometric measurement channels allow to determine the speed and direction of the wind vector, altitude-velocity parameters of motion relative to the environment and atmospheric parameters in a wide range of helicopter operation, which determines its competitive advantages in solving problems of piloting and provide the flight safety of helicopters of different classes and purposes.

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Soldatkin, V. M., and V. V. Soldatkin. "Research of Methodological Errors of the Air Data System of Aircraft with Stationary Included Receiver of Incoming Air Flow." Mekhatronika, Avtomatizatsiya, Upravlenie 20, no. 8 (August 8, 2019): 504–12. http://dx.doi.org/10.17587/mau.20.504-512.

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It is shown that the known limitations on the measurement of air parameters on board the helicopter due to significant aerodynamic disturbances introduced by inductive flows of vortex column of main rotor. This determines the need to create the means of measurement, taking into account the aerodynamics and dynamics of the helicopter flight. The known direction of overcoming these limitations is the use for measuring the information of aerodynamic field of vortex column of main rotor and its perception by means of the stationary multi-functional aerometric receiver. However, the need to protect a large number of full-pressure tubes installed in the flow channel of the multifunctional aerometric receiver, strict requirements for the identity and stability of the characteristics of the large number aerometric channels, complicate the design, reduce reliability, increase cost, inhibit the use of the air parameters measurement system on helicopters of various classes and purposes. Principles of construction, functional scheme, features of perception of primary information of measuring system of air parameters of the helicopter with the stationary receiver of a stream, ion-label and aerometric measuring channels are showed. Algorithms for processing primary information at various stages and flight modes, including: in the parking lot before the launch of the power plant and when rotating the rotor, when taxiing and maneuvering on the earth’s surface, on takeoff and landing modes and when flying at low speeds, at flight speeds, when the stationary receiver of primary information leaves the zone of the vortex column of the rotor using ion-label and aerometric measuring channels, are presented. It is shown that the proposed approaches to the construction, models and algorithms for processing the primary information of the measuring system air parameters of helicopter with ion-label and aerometric measurement channels allow to determine the speed and direction of the wind vector, altitude-velocity parameters of motion relative to the environment and atmospheric parameters in a wide range of helicopter operation, which determines its competitive advantages in solving problems of piloting and provide the flight safety of helicopters of different classes and purposes.

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Szafran, Krzysztof, and Marcin Michalczyk. "Various Types of The Rotorcraft Design in the Context of Aerospace Regulations." Transactions on Aerospace Research 2018, no. 1 (March 1, 2018): 146–53. http://dx.doi.org/10.2478/tar-2018-0010.

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Abstract In the next article on synthesis of regulations, the authors presented the general legal requirements for rotorcraft, which is limited to US regulations, because the vast majority of world regulations are based on them. The Institute of Aviation in Warsaw has developed requirements concerning the construction and operation of rotorcraft in Poland. These requirements constitute an important contribution to the regulations of the Civil Aviation Authority which are in force in the air space of the Republic of Poland. This paper presents the legal situation of rotorcraft and compares the requirements for helicopters and gyroplane. The conclusions highlighted the differences that arise from regulations between helicopters and rotorcraft. The authors have suggested the necessity to separate provisions for the group of windmills, which is implemented in the regulations of the Civil Aviation Authority. The presented work is the second of a planned series of publications in which authors intend to bring some of the issues to the reader about the design aspects of aircraft in selected global aviation regulations.

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Гребеников, А. Г., И. А. Воронько, Ю. В. Дьяченко, В. В. Коллеров, И. В. Малков, В. А. Урбанович, and Н. И. Москаленко. "КОНСТРУКТИВНО-ТЕХНОЛОГІЧНІ ОСОБЛИВОСТІ МЕТАЛЕВИХ ЛОПАТЕЙ НЕСУЧОГО І РУЛЬОВОГО ГВИНТІВ ВЕРТОЛЬОТА." Open Information and Computer Integrated Technologies, no. 87 (June 30, 2020): 5–51. http://dx.doi.org/10.32620/oikit.2020.87.01.

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Analysis of the foreign and domestic work experience, manufacturing and operation of the helicopters with metal blades of the main (MR) and tail (TR) rotors is performed. General requirements for the helicopter MR and TR blades design are formulated. Structural arrangement of the helicopter MR metal blade is reviewed, features of the construction materials for the metal blades are noted. Features of the MR and TR metal blades design with the pressed spar and aluminum honeycomb core are given. Parametric modeling technique of the helicopter MR metal blade is presented. The manufacturing rout technology and the method of the surface strengthening of the metal blade tip are presented. The scheme and the manufacturing rout technology of the pressed aluminum spar are given; the geometrical twist features, the surface strengthening and the assembling of the spar with the blade tip are re- viewed. The features of the electric-heating patch bonding on the spar leading edge are shown. Following technological steps of the blade metal rear area manufacturing are reviewed: the rolled aluminum foil degreasing; the aluminum honeycomb structures manufacturing; the aluminum honeycomb core butt milling. The features of the blade rear area assembling and metal blade assembling by bonding in the jig are presented; the content of works outside of the jig for metal blade of the helicopter main rotor is given.

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Kutt, Filip, Krzysztof Blecharz, and Dariusz Karkosiński. "Axial-Flux Permanent-Magnet Dual-Rotor Generator for a Counter-Rotating Wind Turbine." Energies 13, no. 11 (June 2, 2020): 2833. http://dx.doi.org/10.3390/en13112833.

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Coaxial counter-rotating propellers have been widely applied in ships and helicopters for improving the propulsion efficiency and offsetting system reactive torques. Lately, the counter-rotating concept has been introduced into the wind turbine design. Distributed wind power generation systems often require a novel approach in generator design. In this paper, prototype development of axial-flux generator with a counter-rotating field and armature is presented. The design process was composed of three main steps: analytical calculation, FEM simulation and prototype experimental measurements. The key aspect in the prototype development was the mechanical construction of two rotating components of the generator. Sturdy construction was achieved using two points of contact between both rotors via the placement of the bearing between the inner and outer rotor. The experimental analysis of the prototype generator has been conducted in the laboratory at the dynamometer test stand equipped with a torque sensor. The general premise for the development of such a machine was an investigation into the possibility of developing a dual rotor wind turbine. The proposed solution had to meet certain criteria such as relatively simple construction of the generator and the direct coupling between the generator and the wind turbines. The simple construction and the lack of any gearbox would allow for such a system to be constructed relatively cheaply, which is a key aspect in further system development.

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Picanço Cruz, Eduardo, Carlos Navarro Fontanillas, Karen Possoli, and Martius Vicente Rodriguez y Rodriguez. "Association of Borda's method and analytic hierarchy process (AHP) for the acquisition of helicopters by the Brazilian Navy." Revista Gestão da Produção Operações e Sistemas 15, no. 4 (November 24, 2020): 23–47. http://dx.doi.org/10.15675/gepros.v15i4.2432.

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Purpose – A combination of the Analytic Hierarchy Process (AHP) and the Borda’s Method as a suggestion for collective decision-making. By harmonizing the cardinal scale, resulting from the AHP, with the Borda’s Method, it is expected that the evaluations of the alternatives for new helicopters maximize the individual opinions in the construction of a collective decision. Design/methodology/approach – Qualitative and quantitative. The agents involved in the project of acquisition of helicopters for General Usage and Small Capacity for the Brazilian Navy were interviewed, ten pilots and six military engineers from Aeronautics Board of the Brazilian Navy in Rio de Janeiro. The data were treated by combining the cardinal scale resulting from the AHP with the method proposed by Borda. Findings – Analyzing the MGP’s obtained by AHP, it was possible to ascertain that judgment inconsistencies did not affect the result. It is considered that both methods are capable to promote a helpful decision aid inside the BN in the decision upon the purchase of an aircraft to substitute and enhance their naval aviation fleet. It is also considered that both methods can be applied in similar situation of decisions between mutually exclusive alternatives. Originality/value – The usage of hybrid decision aids (created by the combination of methods) in a multicriteria analysis helps organizations make the best use of available resources, especially in complex decision scenarios. This study helps decision-makers to reflect about the process’ tolerance limits. Keywords - Collective decisions; Multicriteria; Borda's Method; Analytic Hierarchy Process.

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Kłysz, Sylwester. "Transformation Of The S-N Curves For Al 2024 Alloy." Journal of KONBiN 32, no. 1 (December 1, 2014): 19–36. http://dx.doi.org/10.2478/jok-2014-0028.

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Abstract The article compared the results of high cycle fatigue tests in samples of aluminum alloy 2024-T4, which is used in aircraft construction, especially for highly loaded structural elements, including for plating and fuselage frames and girders rotor blades of helicopters - with results available in the literature. The tests were performed on cylindrical samples, of a parallel and perpendicular orientation relative to the "direction of embodiment" or the rolling direction of the blank sheet metal with a coefficient of asymmetry cycle R = −1. Material for the study was collected from the production line design elements PZL-130 Orlik TC-II. There have been a description of the analytical results in the form of Morrow equations. The results were referred to the respective curves contained in a database of material U.S. Department of Transportation Federal Aviation Administration. There have been a presentation the transformation method of S-N curves for different stress ratio R, stress concentration factors Kt and safety factors βN and βσ.

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Kraskowski, Marek. "EXPERIMENTAL ANALYSIS OF THE HELICOPTER DITCHING." Rocznik Bezpieczeństwa Morskiego XIV (November 2, 2020): 1. http://dx.doi.org/10.5604/01.3001.0014.6226.

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The paper presents the method and results of the model tests of helicopter ditching, aimed at adaptation of the helicopter's construction for marine mis-sions. The experiment, realized by Maritime Advanced Research Centre S.A. (CTO) required elaboration of dedicated measurement stand, and solving a number of specific technical problems resulting from the necessity of assuring the repeatability, and required accuracy of the measurements and scalability of the results. Such kind of experiment is not a standard task of a hydrodynamic model testing institution, so it brings an innovation in the testing methodology. The paper presents the details of the test stand and the model itself with rotating rotor, design of the experiment, as well as an overview of the results and main conclusions

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Safaee, Ahmad, Seyed Zeinolabedin Moussavi, and Mohammad Bagher Menhaj. "Design and Construction of Monocopter and its Nonlinear Control Using Photo Diode Array." U.Porto Journal of Engineering 4, no. 2 (October 31, 2018): 34–41. http://dx.doi.org/10.24840/2183-6493_004.002_0003.

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Monocopter is a single-wing rotary flight system which has the capability of hovering. This flyer includes two dynamic parts in which more efficiency can be expected rather than other Micro UAVs due to the extended area of wing compared to its frame. Low capital cost and simple mechanism rather than other systems such as helicopter are the most important specifications of this flight system. In this paper, a model of monocopter flight system has been designed and implemented. Then, a new method of monocopter control and the related hardware has been designed and constructed using photo diode array in order to define position angle of flight system. Designers and constructors have to build a digital compass with the related advantages and disadvantages for this purpose. In the next stage, the optimized flight sample was redesigned and reconstructed and the dynamic parameters of flying were set due to existed hardware restrictions. Then, different experimental tests have been carried out after hardware installation of the control system. So, the controllable flying has been implemented using this control system.

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Ранченко, Геннадий Степанович, Анна Григорьевна Буряченко, Вячеслав Михайлович Грудинкин, and Всеволод Владимирович Данилов. "БАЗОВОЕ ИСПОЛНЕНИЕ РЕГУЛЯТОРА АВИАДВИГАТЕЛЯ И ЕГО МОДИФИКАЦИИ." Aerospace technic and technology, no. 8 (August 31, 2020): 160–65. http://dx.doi.org/10.32620/aktt.2020.8.21.

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It is shown that the creation of a unified electronic control and control equipment for aircraft gas turbine engines is one of the determining trends in the experimental design work of enterprises developing components of aircraft equipment. The results of the creation of some helicopter and aircraft engine controllers (turboshaft and turboprops) in JSC Element are presented. The basic model for them was the regulator RDC-450М (category A component product according to AP-21 classification), which was developed for the AI-450M family of turboshaft engines of Мi-2M and Mi-2MSB and in 2014 received the APPLIANCE DESIGN APPROVAL. There is given information concerning the mass-produced regulator RDTs-450M rework to meet the new requirements specified by the engine designer as the results of certification tests of the AI-450M engine and state tests of the Mi-2M and Mi-2MSB helicopters. It is shown that the rework was carried out taking into account the maximum possible “modifiability” of the regulator, which is the maximum ease of its adaptation in the future to new requirements, including requirements for working with other types of engines, including turboprops. The modular principle of constructing the functional structure and design of the regulator is described; its structural scheme is given. Data are given on the results of equivalent cyclic tests of the regulator RDTs-450M, which was modified to meet the new requirements, and on subsequent work on its adaptation to monitor and regulate the modes of turboprop aircraft engines AI-450C (including its modifications) and MS-500V-02S. Information is given on the newly developed regulators RDTs-450M-S, RDTs-450M-S-1, RDTs-450M-S-T-P, RDTs-450S-500, among which there is an engine regulator designed for an unmanned aerial vehicle. It is noted that the modular design assumes the presence of a significant number of board-to-board connections, and the prospects of increasing the reliability of regulator having a modular design by using the technology of flexible-rigid boards are described.

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Shahmiri, Farid. "Twin-rotor hover performance examination using overlap tests." Aircraft Engineering and Aerospace Technology 89, no. 1 (January 3, 2017): 155–63. http://dx.doi.org/10.1108/aeat-02-2015-0032.

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Purpose The aim of this paper was to experimentally examine twin-rotor hover performance for different rotor overlap ratios at practical rotor loading. Design/methodology/approach The methodology was formed based on data measurements for a designed twin-rotor test model and development of hover performance mathematical models. Thus, measurements were made using a central composite test plan, and then mathematical models for thrust power required power loading (PL) and figure of merit (FM) as functions of collective pitch tip speed; rotor overlap ratio was obtained. In the present paper, the test model consisted of two three-bladed rotors with a diameter of 220 mm and a blade aspect ratio of 16.05. The blades were of a rectangular planform with NACA 0012 cross sections and had no twist or taper. The model was built such that the rear rotor was fixed on the fuselage, and the front rotor could move longitudinally for tests up to about 40 per cent overlap ratio in hover. Findings The best hover aerodynamic efficiency (maximum PL of 14.6 kg/kW) was achieved for non-overlapped rotors at a low value of disc loading (DL) and also at FM of 0.6 at that DL. This result was in agreement with blade element momentum theory predictions. Practical implications Results for the twin-rotor test model can be generalized for actual tandem helicopters through the Reynolds number transformation technique and also some modifications. Originality/value Design and construction of the twin-rotor test model and experimental measurements of hover performance based on an optimal test plan were performed for the first time.

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Suebsomran, Anan. "Heading Control of a RC Helicopter by Fuzzy Logic." Applied Mechanics and Materials 278-280 (January 2013): 1466–72. http://dx.doi.org/10.4028/www.scientific.net/amm.278-280.1466.

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This research aims to control the heading of a small RC helicopter based on fuzzy logic control approach. Control of such a vehicle is normally nonlinear system. To be linear system, the mathematical model of this system would be archived and its parameters. From such difficulty of obtaining mathematical model and parameters, thus in this propose we develop the heading control of a small RC helicopter by using fuzzy logic control, which is overcome the unmodeling of such vehicle, for objective of developed control system. The performance of system is specified to control in time domain design specification. The rule based construction for designing the fuzzy system is related to input and output membership function for inference fuzzy system. Second order response time is specified, and error e and delta error (e) are conditionally assigned for constructing the rule of fuzzy inference system using Mamdani reasoning scheme. Defuzzification method applies the center of gravity (COG) method to computation the output to compensate the error and delta error signal. Finally the result of experiment reveals that the tracking of control of desire heading command and feedback signal is archived via the desired control performance in heading control of a small RC helicopter system.

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Xia, Yong Jun, Qian Miao, and Ke Xin Huang. "Design and Application of the Butt Auxiliary Device for the Erection of Steel Tower Using Helicopter." Applied Mechanics and Materials 387 (August 2013): 319–22. http://dx.doi.org/10.4028/www.scientific.net/amm.387.319.

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The erection construction technology of steel tower of overhead transmission line using helicopter has higher requirements to the butt auxiliary device. According to the GE1 steel tower of the QingZang AC/DC interconnection project Geermu converter station earthling line, the butt auxiliary device is developed. The butt auxiliary device includes a guiding device, horizontal-direction caging device and vertical-direction caging device and solve the problems as follows limiting in air, docking, perching and temporary supporting. The successful engineering application show that the butt auxiliary device is safety and reliable and has perfect function, simple structure and convenient installing and removing. This provides reference for the design of the butt auxiliary device to other types steel tower of transmission line.

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Al-Fatlawi, Alaa, Károly Jármai, and György Kovács. "Optimization of a Totally Fiber-Reinforced Plastic Composite Sandwich Construction of Helicopter Floor for Weight Saving, Fuel Saving and Higher Safety." Polymers 13, no. 16 (August 15, 2021): 2735. http://dx.doi.org/10.3390/polym13162735.

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The application of fiber-reinforced plastic (FRP) composites as structural elements of air vehicles provides weight saving, which results in a reduction in fuel consumption, fuel cost, and air pollution, and a higher speed. The goal of this research was to elaborate a new optimization method for a totally FRP composite construction for helicopter floors. During the optimization, 46 different layer combinations of 4 different FRP layers (woven glass fibers with phenolic resin; woven glass fibers with epoxy resin; woven carbon fibers with epoxy resin; hybrid composite) and FRP honeycomb core structural elements were investigated. The face sheets were composed of a different number of layers with cross-ply, angle-ply, and multidirectional fiber orientations. During the optimization, nine design constraints were considered: deflection; face sheet stress (bending load, end loading); stiffness; buckling; core shear stress; skin wrinkling; intracell buckling; and shear crimping. The single-objective weight optimization was solved by applying the Interior Point Algorithm of the Matlab software, the Generalized Reduced Gradient (GRG) Nonlinear Algorithm of the Excel Solver software, and the Laminator software. The Digimat-HC software solved the numerical models for the optimum sandwich plates of helicopter floors. The main contribution is developing a new method for optimizing a totally FRP composite sandwich structure—due to its material constituents and construction—that is more advantageous than traditional helicopter floors. A case study validated this fact.

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Sergienko, A., V. Chupryna, and R. Kholodnyi. "MODELING OF THE FRAME STRENGTH OF THE MISSILE AND BOMBING GEAR OF THE Мi-8МСБ-В HELICOPTER IN THE TEST PROCESS." Наукові праці Державного науково-дослідного інституту випробувань і сертифікації озброєння та військової техніки, no. 3 (May 28, 2020): 112–20. http://dx.doi.org/10.37701/dndivsovt.3.2020.14.

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The problem of ensuring the frame strength of missile and bombing gear of the Ми-8МСБ-В helicopter pylon in the course of testing is considered. The methods of calculation of the frame strength at maximum load are developed to solve this problem; as well as modeling of design for the main operating modes of the helicopter is conducted. Previously, on the basis of force factors the loading coefficients of the helicopter on its operational modes are determined, particularly in combat use (dive with a volley of missiles and bombing). While conducting modeling the advanced methods of calculating the design of the frame strength parameters were applied, i.e. the analytical manual calculation and computational programs of computer-aided design (CAD). Manually calculating the forces and stresses in the framework (using cut nodes) the frame was idealized as rod model with hinged connections of the elements in the nodes A system of equations for each node was formed, which were solved in MathCAD. In the automated calculation of forces and stresses in the design of the frame the finite element method was implemented, which is used in WinMachine programs and SolidWorks Modeling. The mathematical modeling of the frame was made at the maximum anticipated in-flight loads for determination the critical force and the maximum stress in the construction elements. In addition, the analysis for the redundant deformation was carried out. Performed calculations, mathematical and simulation modelling proved that the necessary strength requirements are met for all the elements of the frame under its maximum load in all flight operational modes.

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Bobrov, V. T., V. M. Bobrenko, and A. V. Gulshin. "ACOUSTIC EXPRESS METHOD FOR MEASURING ELASTIC METAL CONSTANTS OF HIGH-LOADED CONSTRUCTIONS WORKING IN EXTREME CONDITIONS. PART 1." Kontrol'. Diagnostika, no. 264 (June 2020): 46–63. http://dx.doi.org/10.14489/td.2020.06.pp.046-063.

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A review of contingencies related to the failure of potentially hazardous equipment of the aviation and space-rocket complexes showed that they lead to explosions, fires, deaths and destruction of infrastructure. The causes of accidents and disasters are errors in the selection of technical solutions and materials during design, imperfection of algorithms and software for flight control systems, malfunctions in on-board computers and security systems, navigation systems, engine failure, defects in components and assemblies. Examples of accidents and disasters related to technical failures leading to a violation of the tightness of the aircraft fuselage and depressurization of spacecraft are given. It is shown that the main types of damage to the units are corrosion damage, fatigue and metal wear. The conclusion is made about the negative impact of the “human factor” regarding the adoption of erroneous decisions, failure to comply with regulatory requirements and actions in extreme situations. There is a risk of fatigue cracks and degradation of the properties of stringer metal, landing gear struts, wing tail trim, fuel tanks, engine pylon flanges, and imperfect methods, equipment, and technology for monitoring fatigue defects of critical components and mechanisms of aircraft, helicopters, and space systems. It is shown that modern achievements are poorly used in research and development of physical methods and diagnostics of elastic constants of metals working under high pressure, their changes in conditions of wide temperature drops, cosmic vacuum, vibration and other influences. It is proposed to combine efforts with scientists and experts in the field of strength, resource assessment and operational safety of aviation and space technology.

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Bobrov, V. T., V. M. Bobrenko, and A. V. Gulshin. "ACOUSTIC EXPRESS METHOD FOR MEASURING ELASTIC METAL CONSTANTS OF HIGH-LOADED CONSTRUCTIONS WORKING IN EXTREME CONDITIONS. PART 1." Kontrol'. Diagnostika, no. 264 (June 2020): 46–63. http://dx.doi.org/10.14489/td.2020.06.pp.046-063.

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A review of contingencies related to the failure of potentially hazardous equipment of the aviation and space-rocket complexes showed that they lead to explosions, fires, deaths and destruction of infrastructure. The causes of accidents and disasters are errors in the selection of technical solutions and materials during design, imperfection of algorithms and software for flight control systems, malfunctions in on-board computers and security systems, navigation systems, engine failure, defects in components and assemblies. Examples of accidents and disasters related to technical failures leading to a violation of the tightness of the aircraft fuselage and depressurization of spacecraft are given. It is shown that the main types of damage to the units are corrosion damage, fatigue and metal wear. The conclusion is made about the negative impact of the “human factor” regarding the adoption of erroneous decisions, failure to comply with regulatory requirements and actions in extreme situations. There is a risk of fatigue cracks and degradation of the properties of stringer metal, landing gear struts, wing tail trim, fuel tanks, engine pylon flanges, and imperfect methods, equipment, and technology for monitoring fatigue defects of critical components and mechanisms of aircraft, helicopters, and space systems. It is shown that modern achievements are poorly used in research and development of physical methods and diagnostics of elastic constants of metals working under high pressure, their changes in conditions of wide temperature drops, cosmic vacuum, vibration and other influences. It is proposed to combine efforts with scientists and experts in the field of strength, resource assessment and operational safety of aviation and space technology.

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Sverdlov, S. Z. "Estimation of the Time of Flight of an Electric Unmanned Helicopter Based on the Minimum Set of Parameters." Proceedings of Higher Educational Institutions. Маchine Building, no. 5 (710) (May 2019): 67–72. http://dx.doi.org/10.18698/0536-1044-2019-5-67-72.

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This article deals with the problem of forecasting the time of flight of an electric unmanned helicopter utilizing the minimum set of known parameters: the diameter and number of rotors and the flight mass. By solving this problem, it is possible to estimate the capabilities of an unmanned helicopter (multicopter), without having its full technical characteristics, which are often unavailable. In addition, when starting to design an aircraft, it is important to assess its key parameters necessary to achieve a given duration of flight, while preferably utilizing the minimum set of such parameters. Assessment methods are developed based on the statistics of the specific capacity of the batteries used for the construction of the aircraft class in question, and the analysis of the specific energy per weight, which is based both on theoretical studies and the consideration of known analogues. The obtained formulas clearly express the dependence of the time of flight on the key factors influencing it. Estimation of the time of flight using the proposed methods, may be the first step in designing a multicopter.

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Tishchenko, Marat N., Vengalattore T. Nagaraj, and Inderjit Chopra. "Preliminary Design of Transport Helicopters." Journal of the American Helicopter Society 48, no. 2 (2003): 71. http://dx.doi.org/10.4050/jahs.48.71.

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Tishchenko, Marat N. "Mil Design Bureau Heavy-Lift Helicopters." Journal of the American Helicopter Society 42, no. 2 (April 1, 1997): 137–48. http://dx.doi.org/10.4050/jahs.42.137.

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Wojtas, Małgorzata, and Łukasz Czajkowski. "A Prototype Test Stand for Testing Insolated Rotor Systems." Journal of KONES 26, no. 3 (September 1, 2019): 257–64. http://dx.doi.org/10.2478/kones-2019-0081.

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Abstract The article discusses assumptions for a prototype test stand designed for testing rotors in the conditions of work at their nominal speed, in particular gyrocopter and helicopter rotors. In the work presents an overview of similar solutions of test stand presented in the available literature and solutions proposed by companies, such as Swangate International or Luftfahrttechnik GmbH. Beyond these solutions the article also contains test stand used so far at the Institute of Aviation, these solutions were prepared for testing one type of rotor (for example: only for gyroplane rotors). The article provides the steps of designing a new test stand, which one of the basic assumptions is that it will be a universal test stand, giving the possibility to test different types of rotors. The article discusses two concepts of the stand with electric engine as a drive, gives the advantages and disadvantages of each concept, and indicates the selected solution. In addition to design and applied drive solution of the stand, the measuring part and data acquisition were also discussed. Moreover, the article focus on the advantages of rotor testing using the presented solution, as well as problems encountered during tests, in particular related to construction free vibrations and resonance. Vibration and resonance of the test stand are very important aspect of the entire design process, because it affects the quality and safety of the tests.

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Crossley, William A., and David H. Laananen. "Conceptual design of helicopters via genetic algorithm." Journal of Aircraft 33, no. 6 (November 1996): 1062–70. http://dx.doi.org/10.2514/3.47058.

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Ko, Joon Soo, Sungsu Park, and Kyungmok Kim. "Design of Envelope Protection Algorithm for Helicopters." Journal of the Korean Society for Aviation and Aeronautics 23, no. 2 (June 30, 2015): 63–68. http://dx.doi.org/10.12985/ksaa.2015.23.2.063.

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Lee, Choong-Yun, Kwang-Ho Ko, Sung-Nam Jung, and Yung-Hoon Yu. "Preliminary design and cost estimation of helicopters." Journal of the Korean Society for Aeronautical Space Science 38, no. 4 (April 1, 2010): 309–14. http://dx.doi.org/10.5139/jksas.2010.38.4.309.

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Okyere, Emmanuel, Amar Bousbaine, Gwangtim T. Poyi, Ajay K. Joseph, and Jose M. Andrade. "LQR controller design for quad-rotor helicopters." Journal of Engineering 2019, no. 17 (June 1, 2019): 4003–7. http://dx.doi.org/10.1049/joe.2018.8126.

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Yeo, Hyeonsoo. "Design and aeromechanics investigation of compound helicopters." Aerospace Science and Technology 88 (May 2019): 158–73. http://dx.doi.org/10.1016/j.ast.2019.03.010.

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Bisták, Andrej, Zdenka Hulínová, and Michal Neštiak. "Simulation Modelling of Aerial Works and Its Role in the Preparation of Construction." Slovak Journal of Civil Engineering 29, no. 1 (March 1, 2021): 20–26. http://dx.doi.org/10.2478/sjce-2021-0004.

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Abstract The construction process is characterized by a diverse technological composition and the use of a wide range of construction machinery and mechanization. The amount of machinery increases with the complexity of the construction, which increases the demands concerning the preparation and overall organisation of the construction. The preparation of construction processes carried out by helicopters (aerial work) must respect the effect of randomly changing construction conditions as well as the specific working conditions of helicopters. The complexity of such a system can be modelled using simulation models. In the work presented, we designed and practically tested a simulation model of aerial work in the MATLAB software environment. An essential part of the simulation model is an algorithm designed on the basis of commercial numerical weather prediction models. We consider the outputs of the simulation to be reliable, because they are very close to the actual results achieved in the case of the implementation of construction of this type. The concept of the simulation model enables its wider use not only in the construction sector, but also in other branches of industry.

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Бровко, Пётр, Борис Карастелёв, and Юрий Якубовский. "Территориальные и отраслевые аспекты инновационного подхода технологического развития вертолётостроительного производства Дальнего Востока России." ИЗВЕСТИЯ ДАЛЬНЕВОСТОЧНОГО ФЕДЕРАЛЬНОГО УНИВЕРСИТЕТА. ЭКОНОМИКА И УПРАВЛЕНИЕ, no. 3 (2019): 115–25. http://dx.doi.org/10.24866/2311-2271/2019-3/115-125.

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В работе представлено обоснование необходимости пере-хода вертолётостроительного производства Дальнего Востока России на инновационный подход технологического развития, который позволит преодолеть влияние территориальных и отраслевых негативных факторов и закрепиться на динамичных рынках Азиатско-Тихоокеанского региона. Обозначены перспективы роста экономики России и вертолётостроения, в частности, за счет выхода на рынки Азиатско-Тихоокеанского региона. В качестве организационного инструмента, способствующего продвижению инновационных технологий в вертолётостроительном производстве, предлагается создание центра технологических компетенций. It was found that the far East of Russia has unique competitive advantages, the main of which is the neighborhood with the dy-namically developing countries of the Asia-Pacific region, the economic rate of which over the past decade exceeds the global average. The strategic task facing the Russian economy is inte-gration into consolidation in the markets of the Asia-Pacific region, as producers of high-tech products. This necessitates the development of high-tech industries in the Russian far East, which include helicopter construction. In the helicopter industry in Russia there is a lag the world's leading companies in the use of innovative technologies of design, production and after-sales service. In addition, the work found that there are several prob-lems in the industry: the limited size of the domestic market, the reduction of public funding for new developments, the lack of competence of staff to work in the global market. In the far East, this situation is complicated by the influence of negative regional factors: high costs in the economy, a long, outflow of population, remoteness from traditional markets and suppliers, the raw material nature of the economy. The paper substantiates the need for the transition of helicopter production in the Far East of the Russian Federa-tion to an innovative approach to technological development, which will overcome the influence of ter-ritorial and sectoral negative factors. The components of the proposed innovative approach are the introduction into production of products with high export potential, building cooperation with partners from the Asia-Pacific region, technological renewal of the production system, establishing cooperation with scientific and educational institutions, small and medium-sized businesses. A tool for the imple-mentation of a new approach to the technological development of helicopter production in the Far East of Russia will be the creation of a center Of technological competencies, which will allow for coopera-tion between the production enterprises of the region and scientific and educational institutions, which will contribute to the generation of new knowledge and its practical use in production activities The rapid introduction of innovative technologies will increase the competitiveness of the Russian helicopter industry, which will strengthen its position in the Asia-Pacific region.

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Krzymień, Wiesław, and Sławomir Cieślak. "Initial Analysis of Helicopter Impact on Hospital Helipads." Transactions on Aerospace Research 2019, no. 3 (September 1, 2019): 14–23. http://dx.doi.org/10.2478/tar-2019-0014.

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Abstract The need to quickly provide assistance to victims of accidents or seriously ill has created the need for the construction of helipads at selected hospitals. Their operation and the conditions of use are governed by regulation of the Ministry of Health on Hospital Emergency Ward (SOR) and rules required by the Civil Aviation Authority. The direct vicinity of the helipads causes impact of landing and departing helicopters on buildings, people and hospital equipment as well as the construction of the airfield. This article presents vibroacoustic impact of helicopters on helipads’ measurement methods and the results of the preliminary measurements to estimate the impact of Helicopter Air Rescue (LPR) on adjacent buildings and surroundings.

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Zhang, Ming, Yu Zhang, Zhifeng Qiu, and Hanlin Wu. "Two-Stage Covering Location Model for Air–Ground Medical Rescue System." Sustainability 11, no. 12 (June 12, 2019): 3242. http://dx.doi.org/10.3390/su11123242.

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This study tackled the multimodal facility location problem in emergency medical rescue. First, an intermodal setting was suggested, i.e., considering cooperation between ground ambulances and helicopters in emergency medical rescues. Specifically, four scheduling modes were structured: air only, ground only, air-ground combined mode if landing and take-off site for helicopters near the wounded is available, and air-ground transshipment if the landing and take-off site for helicopters near the wounded is not available. Second, a two-stage covering location model was proposed. In the first stage, a set-covering model was developed to achieve maximum coverage and minimal total construction cost of emergency rescue facilities. The optimal mixed allocation proportion of helicopters and ground ambulances was then obtained to guarantee cohesion between the hierarchical models and covering characteristics and the economic efficiency of location results. In the second stage, for given emergency locations, an emergency scheduling mode matrix was constructed for meeting response time and total rescue time constraints. The proposed model obtains optimal results in terms of coverage, construction cost, and rescue time. A case study of Beijing, China validated the feasibility and efficiency of the two-stage covering location model for multimodal emergency medical rescue network. The proposed air-ground rescue system and two-stage covering location model can be extended and also used for large-scale disaster rescue management.

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Bernard, M., K. Kondak, and G. Hommel. "Load transportation system based on autonomous small size helicopters." Aeronautical Journal 114, no. 1153 (March 2010): 191–98. http://dx.doi.org/10.1017/s0001924000003638.

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Abstract This paper is devoted to modelling and control algorithms for a slung load transportation system composed of one or multiple helicopters, where the load is coupled by the means of flexible ropes (see Fig. 1). The coupled helicopter system overcomes the payload limitation of a single small size helicopter, while keeping most of its advantages: small costs of operation, low maintenance costs and increased safeness. Therefore, the system can be utilised whenever the use of full size helicopters is impossible, too expensive or prohibited by law. We focus on the deployment and repairing of distributed sensor networks, using a transportation system based on multiple small size helicopters. A possible real world application is the deployment of fire fighting equipment, where space limitation of the fire trucks prohibits the application of bigger UAVs and using full size helicopters is too dangerous. The problem of load transportation using one or two full size helicopters (twin lift helicopter system), connected to the load by means of flexible ropes, has been discussed in the aerospace research community at least since 1960. We have shown in our previous work that there is a fundamental difference in the mathematical description between small and full size helicopters. Therefore, also the control design for the case of small size helicopters needs to be different. To our knowledge, the control of a slung load transportation system composed of multiple small size helicopters has not been studied until now. In this paper, the complete mechanical setup of the slung load transportation system based on one or more small size helicopters is presented. This includes a short description of the used UAVs, the additionally required sensors, and how the load is mounted. A model of one/multiple helicopters transporting a load is introduced. This model is used in a simplified form for the controller design and in full form for simulation. The controller for one and two helicopters, which is based on a state feedback controller, as well as the controller for three and more helicopters, which is based on a non linear controller, are explained in detail. Both controllers utilise an underlying non-linear orientation controller. We propose a feedback loop, based on forces measured in the ropes, to compensate for the influence of the rope. The controllers were tested in simulation and in real flight experiments. The world wide first flight experiment with three coupled helicopters was successfully conducted at the end of 2007.

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Peng, Chen, Bo Zhu, and Keqi Wei. "Design and Experimental Verification of Robust Motion Synchronization Control with Integral Action." Mathematical Problems in Engineering 2016 (2016): 1–14. http://dx.doi.org/10.1155/2016/7324508.

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A robust attitude motion synchronization problem is investigated for multiple 3-degrees-of-freedom (3-DOF) helicopters with input disturbances. The communication topology among the helicopters is modeled by a directed graph, and each helicopter can only access the angular position measurements of itself and its neighbors. The desired trajectories are generated online and not accessible to all helicopters. The problem is solved by embedding in each helicopter some finite-time convergent (FTC) estimators and a distributed controller with integral action. The FTC estimators generate the estimates of desired angular acceleration and the derivative of the local neighborhood synchronization errors. The distributed controller stabilizes the tracking errors and attenuates the effects of input disturbances. The conditions under which the tracking error of each helicopter converges asymptotically to zero are identified, and, for the cases with nonzero tracking errors, some inequalities are derived to show the relationship between the ultimate bounds of tracking errors and the design parameters. Simulation and experimental results are presented to demonstrate the performance of the controllers.

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Krupadanam, A. S., A. M. Annaswamy, and R. S. Mangoubi. "Multivariable Adaptive Control Design with Applications to Autonomous Helicopters." Journal of Guidance, Control, and Dynamics 25, no. 5 (September 2002): 843–51. http://dx.doi.org/10.2514/2.4974.

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Lukina, N. F., L. A. Dementyeva, A. P. Petrova, and L. A. Anikhovskaya. "Gluing materials in the design of blades of helicopters." Proceedings of VIAM, no. 7 (2016): 7. http://dx.doi.org/10.18577/2307-6046-2016-0-7-7-7.

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Podratzky, Andreas, and Horst Bansemir. "Design and experimental characterization of modern helicopters rotor brakes." Aerospace Science and Technology 11, no. 5 (June 2007): 360–69. http://dx.doi.org/10.1016/j.ast.2007.01.008.

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Tiimus, Kristjan, and Mart Tamre. "Modular Multi-Rotor Helicopter Platforms." Solid State Phenomena 220-221 (January 2015): 110–15. http://dx.doi.org/10.4028/www.scientific.net/ssp.220-221.110.

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The results presented in this paper describe a practicable solution to multi-rotor platforms constructed and put together with standardized components to allow flexibility and customizability. The extensive utilization of universal parts supports an easy introduction of changes in case of necessary design alterations and speeds up the whole process when constructional changes are required. The research has been applied to a variety of special use multi-copters and has proven to be very useful. Further development will follow to secure subcomponents with necessary Ingress Protection ratings and even further optimize universal components. The constructional layout of multi-copters is relatively simple and usually consists of the main middle frame that houses control electronics, batteries and payload fastenings. Protruding boom arms have motors mounted in the tips and power cables running inside. The frame, payload and boom arms are generally fastened with hexagonal socket head cap screws, which means that assembling and disassembling takes a notable amount of valuable time when setting the UAV up on the field. For this reason, modularity and rapid assembling are needed.Fig. 1. Multi-rotors performing ice-bank and high-rise inspection

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Chuntul, Alexandr. "Ergonomic support for the development of modern and advanced systems “crew-helicopter-environment”." Ergodesign 2019, no. 4 (December 15, 2019): 147–55. http://dx.doi.org/10.30987/2619-1512-2019-2019-4-147-155.

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The problems of modern and perspective ergonomic helicopters’ design providing system’s "crew-helicopter-environment” reliable functioning are considered. It is shown that the practice’s requirements require increasing helicopters’ capacity and expanding the boundaries of their operation. The new developments’ forecast in the copyright patents’ implementation using ergonomic technologies are effected.

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Yin, Ze Yong, Bi Bo Fu, Tong Bo Xue, Yong Hong Wang, and Jie Gao. "Development of Helicopter Power Transmission System Technology." Applied Mechanics and Materials 86 (August 2011): 1–17. http://dx.doi.org/10.4028/www.scientific.net/amm.86.1.

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The helicopter power transmission system technology is the key technical area for improving the helicopter performance, reducing the noise/vibration level of helicopters and decreasing the cost of life cycle of helicopters. In this paper, the technical characteristics of the helicopter power transmission system are introduced first. Then, the development history and trend of the transmission configuration, the component and the design and analysis technique of the transmission system are described. The advanced material and process technology applied in the helicopter power transmission system are also described. Finally, the power transmission system technology used in the high speed helicopters is briefly presented.

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Sal, Firat. "Variance constrained trajectory tracking for tandem-rotor helicopters." Aircraft Engineering and Aerospace Technology 92, no. 3 (January 20, 2020): 398–403. http://dx.doi.org/10.1108/aeat-10-2019-0205.

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Purpose This paper aims to present novel results for trajectory tracking of tandem-rotor helicopters via variance-constrained controllers. Design/methodology/approach Regarding these purposes, linearized tandem-rotor helicopter models are benefitted. Findings Variance-constrained controllers are very beneficial for trajectory tracking of tandem-rotor helicopters while there exists variance bounds on outputs of interest. Practical implications Variance-constrained controllers can be used for cheaper tandem-rotor helicopter operations with high trajectory tracking quality. Originality/value Applying variance-constrained control strategy for tandem-rotor helicopters during trajectory tracking. This also causes less fuel consumption and green environment, and good trajectory tracking quality.

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Herr, Christiane M. "Design Is Construction, Construction Is Design." She Ji: The Journal of Design, Economics, and Innovation 5, no. 4 (2019): 367–69. http://dx.doi.org/10.1016/j.sheji.2019.11.007.

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Giovanetti, Eli B., and Kenneth C. Hall. "Optimum Design of Compound Helicopters that Use Higher Harmonic Control." Journal of Aircraft 52, no. 5 (September 2015): 1444–53. http://dx.doi.org/10.2514/1.c032941.

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Dai, Jiyang, and Jianqin Mao. "ROBUST FLIGHT CONTROLLER DESIGN FOR HELICOPTERS BASED ON GENETIC ALGORITHMS." IFAC Proceedings Volumes 35, no. 1 (2002): 73–78. http://dx.doi.org/10.3182/20020721-6-es-1901.00347.

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Klumpner, Christian, and Mohamed Rashed. "Design and evaluation of an energy storage system for helicopters." Journal of Engineering 2019, no. 17 (June 1, 2019): 3665–70. http://dx.doi.org/10.1049/joe.2018.8231.

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Lazzeri, L., and U. Mariani. "Application of Damage Tolerance principles to the design of helicopters." International Journal of Fatigue 31, no. 6 (June 2009): 1039–45. http://dx.doi.org/10.1016/j.ijfatigue.2008.05.010.

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Journal articles on the topic 'Helicopters Design and construction'

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