Relevant bibliographies by topics / Helicopters Design and construction

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
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Academic literature on the topic 'Helicopters Design and construction'

Author: Grafiati
Published: 4 June 2021
Last updated: 14 February 2022

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Journal articles on the topic "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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Dissertations / Theses on the topic "Helicopters Design and construction"

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Kim, Ho-Sik. "Conceptual design optimization for military helicopter maneuverability and agility." Diss., Georgia Institute of Technology, 1997. http://hdl.handle.net/1853/11969.

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Tai, Jimmy C. M. "A multidisciplinary design approach to size stopped rotor/wing configurations using reaction drive and circulation control." Diss., Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/13460.

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Tatossian, Charles A. "Aerodynamic shape optimization via control theory of helicopter rotor blades using a non-linear frequency domain approach." Thesis, McGill University, 2008. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=112586.

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This study presents a discrete adjoint-based aerodynamic optimization algorithm for helicopter rotor blades in hover and forward flight using a Non-Linear Frequency Domain approach. The goal is to introduce a Mach number variation into the Non-Linear Frequency Domain (NLFD) method and implement a novel approach to present a time-varying cost function through a multi-objective adjoint boundary condition. The research presents the complete formulation of the time dependent optimal design problem. The approach is firstly demonstrated for the redesign of a NACA 0007 and a NACA 23012 helicopter rotor blade section in forward flight. A three-dimensional inviscid Aerodynamic Shape Optimization (ASO) algorithm is then employed to validate and redesign the Caradonna and Tung experimental blade. The results in determining the optimum aerodynamic configurations require an objective function which minimizes the inviscid torque coefficient and maintains the desired thrust level at transonic conditions.
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Baker, Andrew Paul. "The role of mission requirements, vehicle attributes, technologies and uncertainty in rotorcraft system design." Diss., Georgia Institute of Technology, 2002. http://hdl.handle.net/1853/12476.

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Yue, Andrew. "H∞-design and the improvement of helicopter handling qualities." Thesis, University of Oxford, 1988. http://ora.ox.ac.uk/objects/uuid:4468a3ab-7297-4363-b605-b3e1f301d11b.

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This thesis presents the results of a study into the use of Hꝏ-optimization for the design of feedback control laws for improving the handling qualities of a Lynx helicopter. An important improvement to the Hꝏ-optimization procedure is the reduction in the number of iterative steps in the γ-iteration before convergence to the optimal γ. Some new algorithms are derived which significantly reduce the computation time for the γ-iteration. Both 2-block and 4-block cases are considered. Control laws are designed for precise control of pitch and roll attitude, yaw rate and heave velocity. Analysis of the raw helicopter showed the need for a stability augmentation system as the dynamic characteristics of the unaugmented helicopter do not comply with military helicopter handling qualities requirements. Results from current research on helicopter handling qualities were used as guidelines in order to define the required dynamic characteristics. A six-degree of freedom nonlinear simulation was used to analyse the helicopter dynamic time histories. A possible solution to the problem of incorporating helicopter handling qualities in the design of robust controllers is to use a two-degree of freedom controller structure. This is illustrated using both H2 and Hꝏ-optimization. A piloted simulation study to assess the effectiveness of advanced control laws was initiated at RAE, Bedford. The trials were carried out in the single seat cockpit flight simulator, at the Flight Research Division and represent the first ever real-time piloted simulation using a Hꝏ-controller.
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Visagie, Jonathan Gerhardus. "Stability and control characteristics of model helicopters." Thesis, Stellenbosch : Stellenbosch University, 2004. http://hdl.handle.net/10019.1/50102.

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Thesis (MScEng)--University of Stellenbosch, 2004.
ENGLISH ABSTRACT: A need exists for the development of an unmanned rotorcraft capable of autonomous flight, as would be required for the survey of high voltage electricity supply lines. A program was initiated at the University of Stellenbosch in December 2002 in order to develop such an aircraft. The first goal of this thesis was the development of software that could calculate the stability and control derivatives of a model helicopter. These derivatives could then be used in the formulation of an appropriate helicopter control strategy. The second goal of the thesis was an investigation of the stability and control characteristics of model helicopters. The trim settings of the helicopter were required in the calculation of the stability and control derivatives. A computer program was developed to determine the trim settings of a helicopter in forward flight. Another program was developed to calculate the stability and control derivatives, using the results of the trim analysis. The trim analysis was based on the assumption of negligible coupling between the longitudinal and lateral modes of motion. The method proposed by Bramwell (1976) was used to perform the trim analysis. The stability and control derivatives were calculated by obtaining the trim settings from the trim analysis. These derivatives were then used to solve the roots of the characteristic equations of the longitudinal and lateral modes of motion. The stability of the helicopters were investigated firstly by examining the stability derivatives and secondly through root-loci analyses. The most important results were the following: • The root-loci analyses indicated that a helicopter without a horizontal stabiliser suffered from instability of the phugoid mode. It was also found that the short-period motion of these helicopters was heavily damped. Fitting a horizontal stabiliser to these helicopters caused the phugoid motion to become stable even at low speeds. This was achieved at the cost of a reduction in short-period motion damping. • The periods of the lateral and longitudinal motions were smaller than those found on full-scale helicopters. This was attributed to the small mass and inertia properties of the model helicopters. An increase in speed is generally accompanied by an increase in the stability of the helicopters. This could be attributed to the effective operation of the tail surfaces at higher speeds. • The axial climbing speed of a helicopter is influenced by the rotor speed. A low rotor speed allows higher climbing velocities at a given power setting. This was due to lower induced power losses at low rotor speed, assuming that no blade stall occurs. • The rotor speed does not influence the incremental amount of power (M:,) required to achieve a certain climbing velocity, due to the fact that the profile power losses are constant for a certain rotor speed. • The simplified horseshoe-vortex theory can be used to analyse the downwash angle at the horizontal stabiliser if the helicopter is in high-speed forward flight.
AFRIKAANSE OPSOMMING: Daar is tans 'n vraag na die ontwikkeling van onbemande rotor-vlerk vliegtuie wat die vermoë beskik om hulself te beheer. Hierdie tipe vliegtuie sal gebruik word om byvoorbeeld hoë-spannings elektrisiteitverskaffingsdrade na te gaan. 'n Program is in Desember 2002 by die Universiteit van Stellenbosch begin om sulke vliegtuie te ontwikkel. Die eerste doel van hierdie tesis was om sagteware te ontwikkel wat die stabiliteit- en beheerafgeleides van 'n model helikopter kon bereken. Hierdie afgeleides kan dan gebruik word om 'n gepaste helikopter beheerstrategie saam te stel. Die tweede doel van die tesis was om die stabiliteit- en beheerseienskappe van model helikopters te ondersoek. Die berekening van die stabiliteit- en beheerafgeleides van die helikopter berus op die beheerinsette benodig om die helikopter in ewewig te hou (trim). 'n Rekenaarprogram is ontwikkelom hierdie beheerinsette vir 'n helikopter in voorwaartse vlug te bereken. 'n Ander program is ontwikkelom die stabiliteit- en beheerafgeleides te bereken met behulp van die ewewig beheerinsette. Die analise van die helikopter in ewewig berus op die aanname dat die grootte van die koppeling tussen die longitudinale en laterale beweginsmodusse weglaatbaar klein is. Die beheerinsette van die helikopter in ewewig tydens voorwaartse vlug is bereken deur van Bramwell (1976) se metode te gebruik. Die stabiliteit- en beheerafgeleides is bereken deur van hierdie beheerinsette gebruik te maak. Die afgeleides is gebruik om die wortels van die karakteristieke vergelykings van die longitudinale en laterale bewegingsmodusse te bereken. Die stabiliteit van die helikopters is eerstens beoordeel deur die stabiliteitsafgeleides te ondersoek en tweedens deur middel van 'n wortel-lokus analise. Die belangrikste resultate is as volg: • Die wortel-lokus analise toon dat 'n helikopter sonder 'n horisontale stabiliseerder phugoid-onstabiliteit (Iangperiode onstabiliteit) het. Die kort-periode beweging van hierdie helikopters het verder groot hoveelhede demping aangetoon. Die phugoid-beweging kon selfs teen lae snelhede gestabiliseer word deur 'n horisontale stabiliseerder aan te heg. Hierdie stabiliteit is egter bereik ten koste van die demping van die kort-periode beweging wat verminder is. • Die periodes van die longitudinale en laterale bewegings is kleiner gewees as vir volskaal helikopters. Dit kan toegeskryf word aan die klein massa en inersie van die model helikopters. • Die stabiliteit van die helikopter is in die algemeen verbeter soos die snelheid verhoog. Dit kan toegeskryf word aan die beter werking van die stert teen die verhoogde snelhede. • Die klimtempo van die helikopter word beïnvloed deur die hoofrotor snelheid. 'n Lae hoofrotor snelheid laat 'n hoër klimptempo toe teen 'n spesifieke drywinginset. Dit is as gevolg van die laer geïndusseerde drywingsverliese teen die laer hoofrotor snelheid. Daar word aanvaar dat die lugvloei oor die lem nie staak nie. • Die hoofrotor snelheid beïnvloed nie die inkrimentele drywing (M,,) wat benodig word om 'n sekere klimtempo te bereik nie. Dit is as gevolg van die konstante drywings verliese teen 'n sekere hoofrotor snelheid. • Die vereenvoudigde perdeskoenwerwel teorie kan gebruik word om die afspoel hoek by die horisontale stabiliseerder te bereken indien die helikopter in hoë-spoed voorwaartse vlug is.
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Davis, Joseph Hutson. "Design Methodology for Developing Concept Independent Rotorcraft Analysis and Design Software." Thesis, Georgia Institute of Technology, 2007. http://hdl.handle.net/1853/19721.

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Throughout the evolution of rotorcraft design, great advancements have been made in developing performance analysis and sizing tools to assist designers during the preliminary and detailed design phases. However, very few tools exist to assist designers during the conceptual design phase. Most performance analysis tools are very discipline or concept specific, and many are far too cumbersome to use for comparing vastly different concepts in a timely manner. Consequently, many conceptual decisions must be made qualitatively. A need exists to develop a single software tool which is capable of modeling any type of feasible rotorcraft concept using different levels of detail and accuracy in order to assist in the decision making throughout the conceptual and preliminary design phases. This software should have a very intuitive and configurable user interface which allows users of different backgrounds and experience levels to use it, while providing a broad capability of modeling traditional, innovative, and highly complex design concepts. As an illustration, a newly developed Concept Independent Rotorcraft Analysis and Design Software (CIRADS) will be presented to prove the applicability of such software tools. CIRADS is an object oriented application with a Graphical User Interface (GUI) for specifying mission requirements, aircraft configurations, weight component breakdowns, engine performance, and airfoil characteristics. Input files from the GUI are assembled to form analysis and design project files which are processed using algorithms developed in MATLAB but compiled as a stand alone executable and imbedded in the GUI. The performance calculations are based primarily upon a modified momentum theory with empirical correction factors and simplified blade stall models. The ratio of fuel (RF) sizing methodology is used to size the aircraft based on the mission requirements specified by the user. The results of the analysis/design simulations are then displayed in tables and Text Fields in the GUI. The intent for CIRADS is to become a primary conceptual sizing and performance estimation tool for the Georgia Institute of Technology rotorcraft design teams for use in the annual American Helicopter Society Rotorcraft Design Competition.
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Thériault, France. "Optimized design of a composite helicopter structure by resin transfer moulding." Thesis, McGill University, 2007. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=99795.

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This research project is partnership project involving industrial, university and government collaborators. The overall objective is to develop and enhance tools for use in Resin Transfer Moulding (RTM) design technology in order to re-design existing metallic parts using composite materials.
The specific objective of this work is to present preliminary research findings of the development of an optimized design of a leading edge slat (horizontal stabilizer component) from the Bell Model 407 Helicopter. The results presented here focus on the static stress analysis and the structure design aspects. The findings will serve as a basis for future design optimization as well as further developments in the use of RTM technology in re-designing metallic aeronautic components and can be considered to be "semi-optimized".
This research is based on extensive finite element analysis (FEA) of several composite material configurations, with a comparison made with the original metallic design. Different key criteria of the part design such as ply lay-up, bracket geometry, angle and configuration are tested using FEA technology with the objective of selecting the design which is minimizing stress concentrations. The influence of the modification of model-related parameters was also studied.
Preliminary comparative studies show that the slat configuration with half brackets opened towards the inside with an angle of 70 degrees (angle between the top of the airfoil and the side of the bracket) is the best option according to minimum stress concentration and structural flexibility. This choice is confirmed by other factors such as material savings and ease of processing.
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Johnson, Kevin Lee. "Prediction of operational envelope maneuverability effects on rotorcraft design." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/47601.

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Military helicopter operations require precise maneuverability characteristics for performance to be determined for the entire helicopter flight envelope. Historically, these maneuverability analyses are combinatorial in nature and involve human-interaction, which hinders their integration into conceptual design. A model formulation that includes the necessary quantitative measures and captures the impact of changing requirements real-time is presented. The formulation is shown to offer a more conservative estimate of maneuverability than traditional energy-based formulations through quantitative analysis of a typical pop-up maneuver. Although the control system design is not directly integrated, two control constraint measures are deemed essential in this work: control deflection rate and trajectory divergence rate. Both of these measures are general enough to be applied to any control architecture, while at the same time enable quantitative trades that relate overall vehicle maneuverability to control system requirements. The dimensionality issues stemming from the immense maneuver space are mitigated through systematic development of a maneuver taxonomy that enables the operational envelope to be decomposed into a minimal set of fundamental maneuvers. The taxonomy approach is applied to a helicopter canonical example that requires maneuverability and design to be assessed simultaneously. The end result is a methodology that enables the impact of design choices on maneuverability to be assessed for the entire helicopter operational envelope, while enabling constraints from control system design to be assessed real-time.
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Suhr, Stephen Andrew. "Preliminary Turboshaft Engine Design Methodology for Rotorcraft Applications." Thesis, Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/14128.

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In the development of modern rotorcraft vehicles, many unique challenges emerge due to the highly coupled nature of individual rotorcraft design disciplines therefore, the use of an integrated product and process development (IPPD) methodology is necessary to drive the design solution. Through the use of parallel design and analysis, this approach achieves the design synthesis of numerous product and process requirements that is essential in ultimately satisfying the customers demands. Over the past twenty years, Georgia Techs Center for Excellence in Rotorcraft Technology (CERT) has continuously focused on refining this IPPD approach within its rotorcraft design course by using the annual American Helicopter Society (AHS) Student Design Competition as the design requirement catalyst. Despite this extensive experience, however, the documentation of this preliminary rotorcraft design approach has become out of date or insufficient in addressing a modern IPPD methodology. In no design discipline is this need for updated documentation more prevalent than in propulsion system design, specifically in the area of gas turbine technology. From an academic perspective, the vast majority of current propulsion system design resources are focused on fixed-wing applications with very limited reference to the use of turboshaft engines. Additionally, most rotorcraft design resources are centered on aerodynamic considerations and largely overlook propulsion system integration. This research effort is aimed at bridging this information gap by developing a preliminary turboshaft engine design methodology that is applicable to a wide range of potential rotorcraft propulsion system design problems. The preliminary engine design process begins by defining the design space through analysis of the initial performance and mission requirements dictated in a given request for proposal (RFP). Engine cycle selection is then completed using tools such as GasTurb and the NASA Engine Performance Program (NEPP) to conduct thorough parametric and engine performance analysis. Basic engine component design considerations are highlighted to facilitate configuration trade studies and to generate more detailed engine performance and geometric data. Throughout this approach, a comprehensive engine design case study is incorporated based on a two-place, turbine training helicopter known as the Georgia Tech Generic Helicopter (GTGH). This example serves as a consistent propulsion system design reference highlighting the level of integration and detail required for each step of the preliminary turboshaft engine design methodology.
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Books on the topic "Helicopters Design and construction"

1

Scarborough, Kate. Helicopters. New York: Barron's, 1994.

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Prouty, Raymond W. Military helicopter design technology. Malabar, Fla: Krieger Pub. Co., 1998.

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Military helicopter design technology. Coulsdon, Surrey, U.K: Jane's Defence Data, 1989.

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White, Graham. 3600 HP split torque helicopter transmission: Final report. Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1985.

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Konstantinovich, Martynov Apollinariĭ, and Sovetskoe nat͡sionalʹnoe obʺedinenie istorikov estestvoznanii͡a i tekhniki. Komissii͡a po razrabotke nauchnogo nasledii͡a B.N. I͡Urʹeva., eds. Trudy nauchnykh chteniĭ, posvi͡ashchennykh pami͡ati akademika V.N. I͡Urʹeva, Moskva, 12-14 noi͡abri͡a 1984 g.: Teoreticheskie osnovy vertoletostroenii͡a i proektirovanii͡a vertoletov. Moskva: [s.n.], 1986.

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Zhang, Chenglin. Zhi sheng ji zong ti she ji. Bei jing: Guo fang gong ye chu ban she, 2006.

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Bakhov, O. P. Aėrouprugostʹ i dinamika konstrukt͡s︡ii vertoleta. Moskva: "Mashinostroenie", 1985.

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V, Mikheev S., ed. Konstrukt︠s︡ii︠a︡ vertoletov. Moskva: Izd-vo MAI, 2001.

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V, Mikheev S., Tishchenko M. N, and Sovetskoe nat͡sionalʹnoe obʺedinenie istorikov estestvoznanii͡a i tekhniki. Komissii͡a po razrabotke nauchnogo nasledii͡a B.N. I͡Urʹeva., eds. Trudy vtorykh nauchnykh chteniĭ, posvi͡ashchennykh pami͡ati akademika V.N. I͡Urʹeva, Moskva, 23-24 marta 1987 g.: Proektirovanie i konstrukt͡sii vertoletov. Moskva: IIET AN SSSR, 1988.

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Leishman, J. Gordon. The helicopter: Thinking forward, looking back. College Park, Md: College Park Press, 2007.

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Book chapters on the topic "Helicopters Design and construction"

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Monreal, J., G. Giannopoulos, F. Santafe, J. Vantomme, F. Buysschaert, and P. Hendrick. "Design Construction and Testing of a Smart Actuated Helicopter Blade." In Experimental Analysis of Nano and Engineering Materials and Structures, 387–88. Dordrecht: Springer Netherlands, 2007. http://dx.doi.org/10.1007/978-1-4020-6239-1_192.

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Maisel, Jordana L., Edward Steinfeld, Megan Basnak, Korydon Smith, and M. Beth Tauke. "Construction." In Inclusive Design, 97–124. New York : Routledge, 2017. | Series: PocketArchitecture : technical design series: Routledge, 2017. http://dx.doi.org/10.4324/9781315712437-4.

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Raptis, Ioannis A., and Kimon P. Valavanis. "Nonlinear Tracking Controller Design for Unmanned Helicopters." In Intelligent Systems, Control and Automation: Science and Engineering, 103–35. Dordrecht: Springer Netherlands, 2011. http://dx.doi.org/10.1007/978-94-007-0023-9_7.

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Chappell, David. "Design." In Construction Contracts, 90–102. Fourth edition. | Abingdon, Oxon; New York: Routledge, 2021.: Routledge, 2020. http://dx.doi.org/10.1201/9781003080930-10.

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Chappell, David. "Design." In Construction Contracts, 90–102. Fourth edition. | Abingdon, Oxon; New York: Routledge, 2021.: Routledge, 2020. http://dx.doi.org/10.4324/9781003080930-10.

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Mosley, W. H., J. H. Bungey, and R. Hulse. "Composite construction." In Reinforced Concrete Design, 350–73. London: Macmillan Education UK, 1999. http://dx.doi.org/10.1007/978-1-349-14911-7_13.

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McLean, Will, and Pete Silver. "Construction Technology." In Environmental Design Sourcebook, 66–97. London: RIBA Publishing, 2021. http://dx.doi.org/10.4324/9781003189046-3.

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Soutsos, Marios, and Peter Domone. "Concrete mix design." In Construction Materials, 249–58. Fifth edition. | Boca Raton : CRC Press, [2017]: CRC Press, 2017. http://dx.doi.org/10.1201/9781315164595-25.

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Dodd, Graham. "Design and applications." In Construction Materials, 453–58. Fifth edition. | Boca Raton : CRC Press, [2017]: CRC Press, 2017. http://dx.doi.org/10.1201/9781315164595-45.

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Houben, Hugo, and Hubert Guillard. "10. Design Guidelines." In Earth Construction, 244–303. Rugby, Warwickshire, United Kingdom: Practical Action Publishing, 1989. http://dx.doi.org/10.3362/9781780444826.010.

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Conference papers on the topic "Helicopters Design and construction"

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Rodriguez, Jonathan, Luc Gaudiller, Simon Chesne, and Paul Cranga. "Control of a Helicopter Main Gearbox Active Suspension System." In ASME 2014 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/detc2014-34278.

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This paper considers the control of a helicopter gearbox electromagnetic suspension for a complete multibody model of the structure. As the new generation of helicopters includes variable engine RPM during flight, it becomes relevant to add active control in their suspension systems. Most of active system performances derive directly from the controller construction, its optimization to the system controlled and the disturbances expected. An investigation on a FXLMS control algorithm has been made to optimize it in terms of narrow band disturbance rejection. In this paper an active suspension based on DAVI principle is evaluated. Firstly, a multibody model is set up to estimate realistic acceleration levels inside the cabin. Then multiple controllers are tested, minimizing vibrations on different parts of the helicopter structure. The simulations tend to prove that it is possible to implement an effective active suspension with a low power actuator and obtain a significant vibration reduction level for a frequency bandwidth centered at the natural frequency of the original DAVI.
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Humphrey, T. Charles, Neil Bose, Christopher Williams, and Michael Snow. "Design and Fabrication of a Collective and Cyclic Pitch Propeller." In ASME 2004 23rd International Conference on Offshore Mechanics and Arctic Engineering. ASMEDC, 2004. http://dx.doi.org/10.1115/omae2004-51313.

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Helicopters achieve three-dimensional flight using a rotor capable of both collective and cyclic pitch. It was proposed that this type of propulsion system could propel and maneuver an underwater vehicle. A collective pitch and cyclic pitch propeller (CPCPP) was designed and developed as a full scale-working prototype for autonomous underwater vehicle (AUV) propulsion. This paper discusses the design and construction aspects of the CPCPP.
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Ossa-Gomez, Camilo, Miad Moarref, and Luis Rodrigues. "Design, construction and fly-by-wireless control of an autonomous Quadrotor helicopter." In 2011 4th Annual Caneus Fly by Wireless Workshop (FBW). IEEE, 2011. http://dx.doi.org/10.1109/fbw.2011.5965559.

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Mateer, R., S. A. Scott, I. Owen, and M. D. White. "Superstructure Aerodynamics of the Type 26 Global Combat Ship." In 14th International Naval Engineering Conference and Exhibition. IMarEST, 2018. http://dx.doi.org/10.24868/issn.2515-818x.2018.038.

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The Type 26 City class Global Combat Ship is the latest design of UK frigate. Construction of the first ship, HMS Glasgow, began in July 2017 and the expectation is that it will enter service in the mid-2020s as a replacement for the Royal Navy’s Type 23 Duke class frigates. The main contractor for the design and construction of the ship is BAE Systems Maritime – Naval Ships. The Type 26 superstructure is characterised by its smooth sloping surfaces that are continuous along the ship from the fore deck to the flight deck. The tumblehome design reduces the ship’s radar cross-section, as does the minimisation of curved surfaces and internal corners. The Type 26 also has a bulky mast, also with flat sloping sides, while the funnel casing around the gas turbine exhaust uptake is located aft of the main mast and relatively low on the superstructure. In comparison, the earlier Type 23 has a much more fragmented superstructure with few geometric features for reduced radar reflection; it also has a more slender mast from which the anemometers are mounted, and the exhaust uptakes are higher. Overall the aerodynamics of the stealthy Type 26 frigate will be very different to the previous Type 23, and this will affect the operational envelope of the ship’s helicopters. Recognising the importance of superstructure aerodynamics to the ship design, the University of Liverpool has been working closely with colleagues from BAE to ensure that the air flow over the ship was considered as the superstructure design evolved. The paper will describe how, within the design cycle, Computational Fluid Dynamics (CFD) has been used to analyse the unsteady flow over the full-scale ship. It will show how CFD, together with helicopter flight dynamics modelling, was used to inform design options for the superstructure geometry ahead of the landing deck. CFD was also used to inform options for locating the ship’s anemometers and has been used to predict the dispersion of the ship’s engine exhaust gases and the air temperature distribution in the vicinity of the flight deck.
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Ouillette, Joanne J. "Designing the Future DDG 51 Class Computer Aided Design." In ASME 1993 International Computers in Engineering Conference and Exposition. American Society of Mechanical Engineers, 1993. http://dx.doi.org/10.1115/edm1993-0105.

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Abstract The DDG 51 Class of AEGIS guided missile destroyers is the Navy’s premier surface combatant. Named for famed World War II hero. Admiral Arleigh Burke, these ships represent state-of-the-art technology. This 504 foot, 8,300 ton destroyer has been designed with improved seakeeping and survivability characteristics and carries the sophisticated AEGIS Weapon System. Derived from the Greek word meaning “shield”, AEGIS ships are the “shield of the fleet”. The Navy has commissioned the first two ships of the class. They have performed beyond expectation in rigorous at-sea trials designed to fully test combat capability. The DDG 51 Class ships are replacing retiring fleet assets. In a decreasing Department of Defense (DoD) budget environment, however, acquisition costs must be reduced to continue to build capable warships. The Navy’s Destroyer Program Office is pursuing the implementation of Computer Aided Design (CAD) and Computer Aided Manufacturing (CAM) technology to reduce costs without reducing ship’s capability. Under Navy direction, the ship construction yards, Bath Iron Works and Ingalls Shipbuilding, are aggressively pursuing the transition to CAD-based design, construction, and life cycle support This effort also involves General Electric, the Combat System Engineering Agent. Building a three dimensional (3D) computer model of the ship prior to construction will facilitate the identification and resolution of interferences and interface problems that would otherwise go undetected until actual ship construction. This 3D database contains geometry and design data to support system design. Accurate construction drawings, fabrication sketches, and Numerical Control (NC) data can be extracted directly from the database to support construction at each shipyard. At completion of construction, a model representing the “as built” configuration will be provided as a lifetime support tool for each ship’s projected 40 year life. The transition to CAD-based design and construction has applied fundamental concepts of the DoD’s Computer Aided Acquisition and Logistic Support (CALS) initiative. In addition to creating a 3D database representing ship design, the shipyards have developed a neutral file translator to exchange this data between Computervision and Calma CAD systems in operation at Bath Iron Works and Ingalls Shipbuilding respectively. This object oriented transfer capability ensures data is shared rather than duplicated. The CALS concepts of concurrent engineering and computer aided engineering analysis are being applied to design an upgrade to the ship that features the addition of a helicopter hanger. The CAD models are used as an electronic baseline from which to assess proposed modifications. Optimizing the design before the first piece of steel is cut will reduce construction costs and improve the quality of the ship.
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Park, Joo Shin, R. Krishna Kishore, Yeong Su Ha, and Ki Bok Jang. "Structural Engineering of Aluminum Helideck Structure Based on the NORSOK Requirement." In ASME 2016 35th International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/omae2016-55062.

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Recently, the numbers of large offshore structures and fixed jacket type platforms are rapidly increasing for oil and gas companies. Generally, a shuttle vessel or helicopter is used to access offshore structures such as a fixed platform, floating platform, jack-up rig and so on. The helideck structure should be installed in these offshore structures for landing and taking-off of the helicopter. The helideck structure comprises of pancakes, girders using aluminum materials and supporting steel structures. The helideck structure should be designed to accommodate a safe landing area suitable for the largest and heaviest helicopter that is anticipated to land on the helideck. The helideck and its supporting structure are safety critical elements as a result of their role in emergency evacuation, as well as during normal operations. The codes and standards applicable for the structural design of the helideck will be determined by where the helideck is to be operated and the national jurisdiction governing the installation or vessel of which the helideck will become part. International standards such as ISO(International Organization for Standardization) codes, Eurocodes, or national standards, e.g. BS(British Standards)5950, NORSOK N-004 or AISC(American Institute of Steel Construction) may be specified for detailed design. The objective of this study is to present the results of structural analysis and design that has been performed for a 28.54 meter diameter octagonal standard aluminum helideck with support truss & lower steel support structure of jackup drilling rig based on the NORSOK requirements. The supporting structure is designed to provide the adequate resistance to the external force produced by the design helicopter and environmental conditions.
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Idahosa, Uyigue, and Vladimir Golubev. "On Noise Control in Turbomachinery Using an Automated Multidisciplinary Design Optimization System." In ASME 2005 International Mechanical Engineering Congress and Exposition. ASMEDC, 2005. http://dx.doi.org/10.1115/imece2005-81789.

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In this work, we review our recent efforts to develop and apply an expanding database of aerodynamic and aeroacoustic prediction technologies for exploring new conceptual designs of propulsion system turbomachinery components optimized for high-efficiency performance with minimum noise radiation. In this context, we first discuss construction of our automated, distributed, industry-like multi-disciplinary design optimization (MDO) environment used in all the studies. The system was developed on the basis of commercially available optimization modules, and involves a user-friendly interface that provides an easy link to user-supplied response analysis modules. We address various issues in the automated optimization procedure with focus on turbomachinery design, including proper geometry parameterization, algorithms selection, and transparent interconnections between different elements of the optimization process. In a benchmark study testing the performance of the system in application to aero/acoustic optimization, we consider a problem of optimal blade design to minimize fan noise, a dominant source of sound radiation both in high-speed fan applications (such as high-bypass-ratio turbofans, propellers of turboprop and IC engines in general aviation, and helicopter rotors) and low-speed ones (including applications in automotive, computer, air-conditioning and other industries). Two approaches are investigated, with the first relying on commercial CFD software coupled with an unstructured mesh generator, and the second employing a panel-based aerodynamic code integrated with an integral acoustic solver. Success of various optimization algorithms (including gradient-based and evolutionary) in finding global minima of the objective function for a noise metric in both unconstrained and constrained optimization processes is examined.
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Farhood, Mazen, and Eric Feron. "An LPV Approach to Obstacle-Sensitive Trajectory Regulation." In ASME 2009 Dynamic Systems and Control Conference. ASMEDC, 2009. http://dx.doi.org/10.1115/dscc2009-2772.

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The paper focuses on the control of vehicular systems along trajectories in the presence of obstacles. We design parameter-dependent controllers which guarantee closed-loop stability and performance of the vehicle’s regulation loop. In addition, the control strategy changes depending on the position of the vehicle in the obstacle environment so that the critical outputs are given the most attention. We also provide a fast and easy-to-implement algorithm for online controller construction. Last, the proposed approach is applied to a three-degree-of-freedom helicopter.
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Hosking, Nathan S., and Zahra Sotoudeh. "Converting Helicopter Rotor Blades From D-Spar to C-Spar: Allowing for Aeromorphing Structures." In ASME 2014 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/imece2014-36966.

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Modern helicopter blades are designed as thin-walled hollow structures in form of either C-spar or D-spar cross-sections. With the advent of new materials hollow designs have been implemented to reduce the overall weight of the structure. A D-spar is a rotor blade cross-section that is hollow in nature with a single vertical spar used to carry a large portion of the stresses otherwise carried by the skin [1]. The vertical spar is normally located between the leading edge and half of the chord length. The remaining volume aft of the vertical spar can either be hollow or filled with a honeycomb structure. The honeycomb structure increases the cross-sectional stiffness. Figure 1. shows an example of a common D-spar with a honeycomb structure aft of the vertical spar [2]. Due to new manufacturing methods the D-spar has now become common place in helicopter design [3]. A C-spar cross-section is very similar to the D-spar cross-section in design and construction. The C-spar cross-section does not have the honeycomb structure and the spar. The structural load is offset by more lamina layers towards the leading edge of the cross-section [4,5]. The thin-walled structure is comprised of many layers of composite materials such as fiberglass or carbon fibers. There has been extensive research into D-spar cross-section while there is a lack of studies for C-spar cross-sections [1,3,4].
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Duque, Earl, Lakshmi Sankar, Suresh Menon, Olivier Bauchau, Steve Ruffin, Marilyn Smith, Krishan Ahuja, et al. "Revolutionary Physics-Based Design Tools for Quiet Helicopters." In 44th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-1068.

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Reports on the topic "Helicopters Design and construction"

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CORPS OF ENGINEERS WASHINGTON DC. Construction: Design and Construction Evaluation (DCE). Fort Belvoir, VA: Defense Technical Information Center, February 1996. http://dx.doi.org/10.21236/ada404141.

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Sankar, Lakshmi N., and Kenneth S. Brentner. Revolutionary Physics-Based Design Tools for Quiet Helicopters, Phase I-B Extension. Fort Belvoir, VA: Defense Technical Information Center, September 2008. http://dx.doi.org/10.21236/ada508845.

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Fanella, David A., Amaldo T. Derecho, and S. K. Ghosh. Design and construction of structural systems. Gaithersburg, MD: National Institute of Standards and Technology, 2005. http://dx.doi.org/10.6028/nist.ncstar.1-1av1.

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Slocum, Alexander H., Laura A. Demsetz, David H. Levy, and Bruce Schena. Design Methodology for Automated Construction Machines. Fort Belvoir, VA: Defense Technical Information Center, December 1987. http://dx.doi.org/10.21236/ada207386.

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Collins, James J. Design and Construction of Genetic Applets. Fort Belvoir, VA: Defense Technical Information Center, May 2003. http://dx.doi.org/10.21236/ada417910.

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Jackson, J. G. Y-12 Sustainable Design Principles for Building Design and Construction. Office of Scientific and Technical Information (OSTI), November 2008. http://dx.doi.org/10.2172/969028.

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CORPS OF ENGINEERS WASHINGTON DC. Engineering and Design. Construction with Large Stone. Fort Belvoir, VA: Defense Technical Information Center, October 1990. http://dx.doi.org/10.21236/ada402849.

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McNeese, L. E. ORNL engineering design and construction reengineering report. Office of Scientific and Technical Information (OSTI), January 1998. http://dx.doi.org/10.2172/631227.

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Janet E.R. Mcllvaine, David Beal, and Philip Fairey. INTERIOR DUCT SYSTEM DESIGN, CONSTRUCTION, AND PERFORMANCE. Office of Scientific and Technical Information (OSTI), October 2001. http://dx.doi.org/10.2172/823970.

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Schwartztrauber, K. Modular Design/Phased Construction Alternative Evaluation Report. Office of Scientific and Technical Information (OSTI), May 1999. http://dx.doi.org/10.2172/763136.

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