Relevant bibliographies by topics / Helicopter

Academic literature on the topic 'Helicopter'

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Published: 4 June 2021
Last updated: 6 July 2024

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Journal articles on the topic "Helicopter"

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Trethewey, Diane. "Development of an index for quick comparison of helicopter costs and benefits." International Journal of Wildland Fire 16, no. 4 (2007): 444. http://dx.doi.org/10.1071/wf06108.

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A helicopter comparison index was developed to incorporate cost and benefit information for individual helicopters for large wildland fire suppression operations. The costs and benefits for individual helicopters are unique. Costs consist of daily availability and hourly flight rates. Benefits depend on the payload, which depends on the altitude and temperature of operation, weight of the helicopter, equipment on board, crew, and fuel. Because of the complexity of calculating payload, previous methods for deploying helicopters classified helicopters into three types according to their typical payload. The least expensive helicopter of the desired type was deployed. Because this classification system produces a broad range of benefits within each helicopter type, this method may not deploy the most efficient helicopter. The helicopter comparison index can be calculated at representative altitudes and temperatures before it is needed. As the work is done beforehand, the helicopters can be compared quickly when they are needed. The helicopter comparison index allows helicopters to be compared based on the efficiency of the individual helicopters rather than just their cost of operation. Evaluation of Type I helicopters shows that using the helicopter comparison index instead cost of operation has savings potential of 20 to 45 percent.
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Frey, Felix, Jakob Thiemeier, Constantin Öhrle, Manuel Keßler, and Ewald Krämer. "Aerodynamic Interactions on Airbus Helicopters' Compound Helicopter RACER in Cruise Flight." Journal of the American Helicopter Society 65, no. 4 (October 1, 2020): 1–14. http://dx.doi.org/10.4050/jahs.65.042001.

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With the pursuit of extending the flight envelopes of helicopters toward higher cruise speed, helicopter manufacturers increasingly have come up with nonconventional configurations in recent years. Among these, Airbus Helicopters' RACER (Rapid And Cost-Efficient Rotorcraft) is a compound helicopter equipped with a boxwing and lateral pusher rotors. In combination with the main rotor, these additional components determine the aerodynamic characteristics of the helicopter. Thereby, depending on the flight conditions, their individual performance is influenced by a variety of interactions. As the understanding of these interactions is vital for the evaluation of the overall system, the respective mutual influence of main rotor, wings, and lateral rotors is analyzed in this paper for cruise flight. For this reason, high-fidelity coupled aerodynamic simulations are conducted not only for the full RACER configuration but also for reduced setups omitting individual components to isolate the effect of these components on the helicopter's aerodynamic performance.
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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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Češkovič, Marek, Martin Schrötter, Róbert Huňady, Pavol Kurdel, and Natália Gecejová. "Unwanted Supplementary Vibrations of Helicopter Radio Communication Systems." Aerospace 10, no. 7 (July 13, 2023): 632. http://dx.doi.org/10.3390/aerospace10070632.

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A helicopter in flight can be considered an unstable dynamic system with many unwanted vibrations originating from multiple sources, such as the operation of the engines and individual components. These vibrations cause the degradation of the structural and functional components of a helicopter, thereby generally reducing the utility and technical efficiency of the aircraft. During the analysis of frequently recurring errors of medium-heavy helicopters, partial damage to antenna elements with vertical polarisation was detected. These damages provided the basis for the presented research, based on which supplementary vibrations caused by unwanted electromagnetic oscillations were revealed. These oscillations were detected in the process of communication between the helicopter crew and the ground ATC (air traffic control) station. This phenomenon’s existence and negative influence were confirmed via measurements and modal analysis, based on which an exact synergy between harmonic frequencies of the helicopter’s normal vibrations was discovered. The obtained results serve as a theoretical and practical basis for the future monitoring of this phenomenon, especially in the process of determining the “health status” of medium-heavy helicopters.
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Luong, Quoc Viet, Dae-Sung Jang, and Jai-Hyuk Hwang. "Semi-Active Control for a Helicopter with Multiple Landing Gears Equipped with Magnetorheological Dampers." Applied Sciences 11, no. 8 (April 19, 2021): 3667. http://dx.doi.org/10.3390/app11083667.

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Due to their extensive use in various applications, helicopters need to be able to land in a variety of conditions. Typically, a helicopter landing gear system with skids or passive wheel-dampers is designed based on only one critical touchdown condition. Thus, this helicopter landing gear system may not perform well in different landing conditions. A landing gear system with magnetorheological (MR) dampers would be a promising candidate to solve this problem. However, a semi-active controller must be designed to determine the electrical current applied to the MR damper to directly manage the damping force. This paper presents a new skyhook controller, called the skyhook extended controller, for a helicopter with multiple landing gears equipped with MR dampers to reduce the helicopter’s acceleration at the center of gravity in off-normal landing attitude conditions. A 9-DOF simulation model of a helicopter with multiple MR landing gears was built using RECURDYN. To verify the effectiveness of the proposed controller, co-simulations were executed with RECURDYN and MATLAB in different initial pitch and roll angles at touchdown. The main simulation results show that the proposed controller can greatly decrease the peak and rms acceleration of the helicopter’s center of gravity compared to a traditional skyhook controller and passive damper.
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Thomson, D. G., and R. Bradley. "The use of inverse simulation for preliminary assessment of helicopter handling qualities." Aeronautical Journal 101, no. 1007 (September 1997): 287–94. http://dx.doi.org/10.1017/s0001924000066148.

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AbstractThis paper describes a method for using inverse simulation to obtain a preliminary assessment of helicopter handling qualities. Formal descriptions of standard manoeuvres, defined to establish the handling qualities of military helicopters, are used to drive an inverse simulation of a subject helicopter. The simulation generates the controls and states of the helicopter as it executes the manoeuvre and the results may be used to calculate values of quickness, a parameter defined to measure responsiveness. Initial results reveal that in the context of inverse simulation quickness is independent of vehicle configuration when, as specified in the requirements, the quickness is based on the helicopter's kinematic states. An alternative quickness parameter, associated with the control displacements required to fly the manoeuvre is shown to be capable of discriminating between the pilot workload involved in flying two different configurations through the same manoeuvre.
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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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Szilvássy, László. "Why Does the Attack Helicopter Have More Survival Ability than the Armed Utility Helicopter?" Repüléstudományi Közlemények 34, no. 3 (2022): 167–80. http://dx.doi.org/10.32560/rk.2022.3.11.

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The author highlights the difference between attack and armed utility helicopters and supports this with professional arguments. He also presents the most common weapon systems of combat helicopters. Points out that an armed transport helicopter or multipurpose helicopter cannot substitute attack helicopters at all.
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Orhan, Ilkay. "Estimation of helicopter emission and greenest helicopters for London." Aircraft Engineering and Aerospace Technology 93, no. 8 (July 26, 2021): 1333–45. http://dx.doi.org/10.1108/aeat-03-2021-0082.

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Purpose This study aims to estimate the greenest helicopters and the emission amount based on the helicopter movement within the London Heathrow and London city control zone. Design/methodology/approach The helicopter flight data recorded by the UK’s specialist aviation regulator Civil Aviation Authority and the helicopter type with engine emission data from the Federal Office of Civil Aviation (FOCA) were used for calculation. Based on the approach adopted, the greenest and the most environmentally friendly helicopters were identified for a light-duty helicopter with single-engine, a light-duty helicopter with twin-engine and a heavy-duty helicopter with twin-engine. Findings Comparing a flight consisting of landing and take-off cycle, and 1-h phase based on helicopters emissions in the FOCA database, B06 with DDA250-C20R single-engine in the light utility, A109 with PT6B-37 twin-engine in the light utility, and the A139 helicopter with the PT6C-67C twin-engine in the high utility has been identified as the most environmentally friendly helicopter. Practical implications This study provides the opportunity to compare between the best and the worst helicopter with engine type according to the emission values released to the environment. Originality/value This study raises awareness of the emission levels caused by helicopter in urban air transport in developed countries in terms of environmental and human health. It also provides justification for the authorities to encourage the development and use of green engines and technologies.
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Oktay, Tugrul, Harun Celik, and Ilke Turkmen. "Constrained control of helicopter vibration to reduce motion blur." Aircraft Engineering and Aerospace Technology 90, no. 9 (November 14, 2018): 1326–36. http://dx.doi.org/10.1108/aeat-02-2017-0068.

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Purpose The purpose of this paper is to examine the success of constrained control on reducing motion blur which occurs as a result of helicopter vibration. Design/methodology/approach Constrained controllers are designed to reduce the motion blur on images taken by helicopter. Helicopter vibrations under tight and soft constrained controllers are modeled and added to images to show the performance of controllers on reducing blur. Findings The blur caused by vibration can be reduced via constrained control of helicopter. Research limitations/implications The motion of camera is modeled and assumed same as the motion of helicopter. In model of exposing image, image noise is neglected, and blur is considered as the only distorting effect on image. Practical implications Tighter constrained controllers can be implemented to take higher quality images by helicopters. Social implications Recently, aerial vehicles are widely used for aerial photography. Images taken by helicopters mostly suffer from motion blur. Reducing motion blur can provide users to take higher quality images by helicopters. Originality/value Helicopter control is performed to reduce motion blur on image for the first time. A control-oriented and physic-based model of helicopter is benefited. Helicopter vibration which causes motion blur is modeled as blur kernel to see the effect of helicopter vibration on taken images. Tight and soft constrained controllers are designed and compared to denote their performance in reducing motion blur. It is proved that images taken by helicopter can be prevented from motion blur by controlling helicopter tightly.
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Dissertations / Theses on the topic "Helicopter"

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Perkins, Keith M. "Implementing realistic helicopter physics in 3D game environments." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02sep%5FPerkins.pdf.

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Thesis (M.S. in Modeling, Virtual Environments and Simulations)--Naval Postgraduate School, September 2002.
Thesis advisor(s). Includes bibliographical references (p. 79-80). Also available online.
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Peitso, Loren E. "Visual field requirements for precision nap-of-the-earth helicopter flight." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02sep%5FPeitso.pdf.

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Thesis (M.S. in Modeling, Virtual Environments and Simulation)--Naval Postgraduate School, September 2002.
Thesis advisor(s): Rudolph P. Darken, Joe Sullivan. Includes bibliographical references (p. 65-66). Also available online.
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Kulakowski, Walter W. "Exploring the feasibility of the virtual environment helicopter system (VEHELO) for use as an instructional tool for military helicopter pilots." Thesis, Monterey, California. Naval Postgraduate School, 2004. http://hdl.handle.net/10945/1394.

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The requirement for low-level navigation flight conducted between 200 and 500 feet above ground level is something unique to the military helicopter pilot. Each novice helicopter pilot is introduced to this skill early and in a limited number of flights or flight hours. A low situational awareness (SA)is historically noted among the novice pilots during their first few flights within this flight regime. To that end, this thesis continues with the work conducted earlier to develop a trainer that places the pilot in an immersive and familiar cockpit environment for training through the use of chromakeyed technology as employed in the Virtual Environment Helicopter System (VEHELO). The pilot will then be able to learn and exercise required piloting tasks and multi-place aircraft communications as authentically and as meticulously as in actual flight. The focus of this thesis is to continue validation of the ChrAVE/VEHELO system. This will be accomplished by comparison of data obtained from data collected by pilots flying the ChrAVE and flying the actual aircraft during initial navigational training flights. Additionally this thesis will attempt to show that the latest version of the system has a previously unrecognized ability to improve pilot performance. The system is capable of teaching novice pilots the important skill of Crew Resource Management (CRM) and the appropriate communication skills. The original Chromakey Augmented Virtual Environment (ChrAVE) helicopter flight simulation system was developed to substantiate the feasibility of having embedded trainers for helicopters. Both the ChrAVE and VEHELO are comprised of commercial off the shelf (COTS) equipment in a mobile wheeled box. To determine the effectiveness of the ChrAVE as an instructional tool, the opinions of pilots and pilot instructors will be collected for analysis. The subject pilots will be tasked with numerous realistic piloting tasks. Empirical data will be collected and evaluated according to the low-level navigation performance thresholds set forth by Marine Medium Helicopter Training Squadron 164 (HMMT- 164) which is the CH-46E Model Manager.
US Marine Corps (USMC) author.
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Howard, Christopher B. Bradley Walter Lee. "Fatigue methodology for analysis of helicopter dynamic components." Waco, Tex. : Baylor University, 2008. http://hdl.handle.net/2104/5188.

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Carico, Dean. "Helicopter controllability." Thesis, Monterey, California. Naval Postgraduate School, 1989. http://hdl.handle.net/10945/27077.

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Olsson, Julia, and Sophie Nilsonne. "Helicopter money." Thesis, KTH, Fastigheter och byggande, 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-191551.

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This thesis has been conducted through a qualitative research method in order to explain the concept of helicopter money and how to implement it in Sweden in line with present law. Milton Frideman was the first to coin the concept of helicopter money. His theory was that a permanent increase of the monetary base via money transferring to households would increase the aggregate demand and consequently result in an increase of the inflation level. Further Ben Bernanke has developed this theory to not only include transferring money to households but to the government in order to enable an increase in public spending and increase of inflation. Helicopter money is a form of direct monetary financing, which is illegal in Sweden today. There are ways to implement it though by doing an implicit transfer to the government through purchases of treasury bonds that are held in infinity. Helicopter money therefore requires cooperation between the government and the Riksbank. In order for helicopter money to be a sufficient tool the money that are being transferred needs to be consumed. Helicopter money has the unique quality that it’s irredeemable. Which result in an asymmetric treatment of the money, which mean that households never have to repay these money and therefore the consumption propensity rises. Helicopter money also weakens the currency, which results in an increase of inflation. Transferring money to the households would probably increase the inflation level but it also entails risks. If we on the other hand transfer the money to the government we can be absolutely certain that inflation will rise. The best way to implement helicopter money in order to achieve a higher inflation and at the same time taking present law into account is therefore to make an implicit transfer to the government. A good communication and explanation of the intentions are of great importance in order to retain the trust of the government and institutions.
Denna uppsats har genom en kvalitativ undersökning redogjort för begreppet helikopterpengar samt vilka förutsättningar som krävs för att implementera det i Sverige med hänsyn till rådande lagstiftning. Helikopterpengar bygger på en teori av Milton Friedman och innebär en permanent ökning av penningmängden via en transferering till hushållen vilket resulterar i en ökad aggregerad efterfråga och stigande inflation. Begreppet har utvecklats av bland annat Ben Bernanke som menar på att en transferering av helikopterpengarna likväl kan ske till staten för att öka offentliga utgifter och på det sättet driva upp inflationen. Helikopterpengar är en typ av direkt monetär finansiering som är förbjuden i Sverige med dagens lagstiftning. Det går dock att praktiskt tillämpa helikopterpengar genom att göra en indirekt transferering till staten genom köp av statsobligationer som hålls för evigt. Helikopterpengar kräver alltså ett samarbete mellan staten och Riksbanken. För att helikopterpengar ska få önskad effekt bygger det på att pengarna konsumeras. Helikopterpengar innebär en asymmetrisk behandling av pengarna vilket gör att hushållen inte behöver betala tillbaka pengarna i framtiden och konsumtionsbenägenheten ökar. Helikopterpengar urholkar kronans värde vilket leder till en svagare valuta som i sin tur också bidrar till en ökad inflation. En transferering till hushållen skulle med stor sannolikhet ge effekt på inflationsnivån men medför även risker. Genomförs däremot en transferering till staten kommer inflationen med säkerhet att öka då staten kan se till att varje krona spenderas. Bästa sättet att implementera helikopterpengar för att få störst effekt med hänsyn till rådande lagstiftning är alltså att göra en indirekt transferering till staten. Det är även viktigt att kommunicera intentionerna på ett pedagogiskt sätt för att marknaden ska behålla förtroendet för pengar och institutionerna.
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Ference, Edward W. "Case study of the development of the Apache attack helicopter (AH-64)." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02Dec%5FFerence.pdf.

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Thesis (M.S. in Program Management)--Naval Postgraduate School, December 2002.
Thesis advisor(s): Michael W. Boudreau, Richard G. Rhoades. Includes bibliographical references (p. 63-65). Also available online.
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Zhao, Jinggen. "Dynamic Wake Distortion Model for Helicopter Maneuvering Flight." Diss., Georgia Institute of Technology, 2005. http://hdl.handle.net/1853/7103.

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A new rotor dynamic wake distortion model, which can be used to account for the rotor transient wake distortion effect on inflow across the rotor disk during helicopter maneuvering and transitional flight in both hover and forward flight conditions, is developed. The dynamic growths of the induced inflow perturbation across the rotor disk during different transient maneuvers, such as a step pitch or roll rate, a step climb rate and a step change of advance ratio are investigated by using a dynamic vortex tube analysis. Based on the vortex tube results, a rotor dynamic wake distortion model, which is expressed in terms of a set of ordinary differential equations, with rotor longitudinal and lateral wake curvatures, wake skew and wake spacing as states, is developed. Also, both the Pitt-Peters dynamic inflow model and the Peters-He finite state inflow model for axial or forward flight are augmented to account for rotor dynamic wake distortion effect during helicopter maneuvering flight. To model the aerodynamic interaction among main rotor, tail rotor and empennage caused by rotor wake curvature effect during helicopter maneuvering flight, a reduced order model based on a vortex tube analysis is developed. Both the augmented Pitt-Peters dynamic inflow model and the augmented Peters-He finite state inflow model, combined with the developed dynamic wake distortion model, together with the interaction model are implemented in a generic helicopter simulation program of UH-60 Black Hawk helicopter and the simulated vehicle control responses in both time domain and frequency domain are compared with flight test data of a UH-60 Black Hawk helicopter in both hover and low speed forward flight conditions.
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Law, N. "Integrated helicopter survivability." Thesis, Cranfield University, 2011. http://dspace.lib.cranfield.ac.uk/handle/1826/6518.

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A high level of survivability is important to protect military personnel and equipment and is central to UK defence policy. Integrated Survivability is the systems engineering methodology to achieve optimum survivability at an affordable cost, enabling a mission to be completed successfully in the face of a hostile environment. “Integrated Helicopter Survivability” is an emerging discipline that is applying this systems engineering approach within the helicopter domain. Philosophically the overall survivability objective is ‘zero attrition’, even though this is unobtainable in practice. The research question was: “How can helicopter survivability be assessed in an integrated way so that the best possible level of survivability can be achieved within the constraints and how will the associated methods support the acquisition process?” The research found that principles from safety management could be applied to the survivability problem, in particular reducing survivability risk to as low as reasonably practicable (ALARP). A survivability assessment process was developed to support this approach and was linked into the military helicopter life cycle. This process positioned the survivability assessment methods and associated input data derivation activities. The system influence diagram method was effective at defining the problem and capturing the wider survivability interactions, including those with the defence lines of development (DLOD). Influence diagrams and Quality Function Deployment (QFD) methods were effective visual tools to elicit stakeholder requirements and improve communication across organisational and domain boundaries. The semi-quantitative nature of the QFD method leads to numbers that are not real. These results are suitable for helping to prioritise requirements early in the helicopter life cycle, but they cannot provide the quantifiable estimate of risk needed to demonstrate ALARP. The probabilistic approach implemented within the Integrated Survivability Assessment Model (ISAM) was developed to provide a quantitative estimate of ‘risk’ to support the approach of reducing survivability risks to ALARP. Limitations in available input data for the rate of encountering threats leads to a probability of survival that is not a real number that can be used to assess actual loss rates. However, the method does support an assessment across platform options, provided that the ‘test environment’ remains consistent throughout the assessment. The survivability assessment process and ISAM have been applied to an acquisition programme, where they have been tested to support the survivability decision making and design process. The survivability ‘test environment’ is an essential element of the survivability assessment process and is required by integrated survivability tools such as ISAM. This test environment, comprising of threatening situations that span the complete spectrum of helicopter operations requires further development. The ‘test environment’ would be used throughout the helicopter life cycle from selection of design concepts through to test and evaluation of delivered solutions. It would be updated as part of the through life capability management (TLCM) process. A framework of survivability analysis tools requires development that can provide probabilistic input data into ISAM and allow derivation of confidence limits. This systems level framework would be capable of informing more detailed survivability design work later in the life cycle and could be enabled through a MATLAB® based approach. Survivability is an emerging system property that influences the whole system capability. There is a need for holistic capability level analysis tools that quantify survivability along with other influencing capabilities such as: mobility (payload / range), lethality, situational awareness, sustainability and other mission capabilities. It is recommended that an investigation of capability level analysis methods across defence should be undertaken to ensure a coherent and compliant approach to systems engineering that adopts best practice from across the domains. Systems dynamics techniques should be considered for further use by Dstl and the wider MOD, particularly within the survivability and operational analysis domains. This would improve understanding of the problem space, promote a more holistic approach and enable a better balance of capability, within which survivability is one essential element. There would be value in considering accidental losses within a more comprehensive ‘survivability’ analysis. This approach would enable a better balance to be struck between safety and survivability risk mitigations and would lead to an improved, more integrated overall design.
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Sadownick, Ronald 1960. "Helicopter configuration optimization." Thesis, Massachusetts Institute of Technology, 2000. http://hdl.handle.net/1721.1/82683.

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Thesis (S.M.)--Massachusetts Institute of Technology, System Design & Management Program, February 2001.
This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.
Includes bibliographical references (leaf 102).
by Ronald Sadownick.
S.M.
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Books on the topic "Helicopter"

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Authority, Civil Aviation, ed. Helicopter health monitoring: Bristow Helicopters Ltd : operational trial of helicopter health monitoring techniques. London: Civil Aviation Authority, 1993.

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BUCHair Helicopters 1995: [Global Helicopter Database Listing]. 4th ed. Surrey: BUCHair(U.K.) Ltd, 1995.

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Parsont, Meg. Helicopter. New York: Abbeville Kids, 1999.

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Oxlade, Chris. Helicopter. Parsippany, NJ: Silver Press, 1997.

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Helicopter. Oxford: Heinemann Library, 2007.

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Oxlade, Chris. Support helicopter pilots. New York: Crabtree Pub., 2012.

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Oxlade, Chris. Support helicopter pilots. New York: Crabtree Pub., 2012.

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Christopher, Chant. Bell UH-1. Sparkford, Yeovil, Somerset: Haynes, 1985.

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Modern fighting aircraft: AH-1 Cobra. London: Salamander, 1987.

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Richardson, Doug. Modern fighting aircraft: AH-64. London: Salamander Books, 1987.

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Book chapters on the topic "Helicopter"

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Sinn, Hans-Werner. "Helicopter Money." In Economic Ideas You Should Forget, 129–30. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-47458-8_55.

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Brockmann, T. H. "Helicopter Applications." In Theory of Adaptive Fiber Composites, 5–18. Dordrecht: Springer Netherlands, 2009. http://dx.doi.org/10.1007/978-90-481-2435-0_2.

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Tingley, Suzanne Capek. "Helicopter Mom." In How to Handle Difficult Parents, 95–103. 2nd ed. New York: Routledge, 2021. http://dx.doi.org/10.4324/9781003235606-13.

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Ganguli, Ranjan, Dipali Thakkar, and Sathyamangalam Ramanarayanan Viswamurthy. "Introduction." In Smart Helicopter Rotors, 1–40. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-24768-7_1.

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Ganguli, Ranjan, Dipali Thakkar, and Sathyamangalam Ramanarayanan Viswamurthy. "Airfoil-Section Rotor Blades." In Smart Helicopter Rotors, 189–219. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-24768-7_10.

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Ganguli, Ranjan, Dipali Thakkar, and Sathyamangalam Ramanarayanan Viswamurthy. "Dynamic Stall Alleviation Using Active Twist." In Smart Helicopter Rotors, 221–49. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-24768-7_11.

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Ganguli, Ranjan, Dipali Thakkar, and Sathyamangalam Ramanarayanan Viswamurthy. "Mathematical Modeling." In Smart Helicopter Rotors, 41–70. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-24768-7_2.

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Ganguli, Ranjan, Dipali Thakkar, and Sathyamangalam Ramanarayanan Viswamurthy. "Preliminary Studies with Active Flaps." In Smart Helicopter Rotors, 71–80. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-24768-7_3.

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Ganguli, Ranjan, Dipali Thakkar, and Sathyamangalam Ramanarayanan Viswamurthy. "Flap Configuration and Control Law." In Smart Helicopter Rotors, 81–101. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-24768-7_4.

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Ganguli, Ranjan, Dipali Thakkar, and Sathyamangalam Ramanarayanan Viswamurthy. "Active Flap Controller Evaluation." In Smart Helicopter Rotors, 103–11. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-24768-7_5.

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Conference papers on the topic "Helicopter"

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Lotoa, R. T. "VIBRATION CHARACTERISTICS AND FAULT ANALYSIS OF HELICOPTER PEDALS." In Topics In Chemical & Material Engineering (TCME). Volkson Press, 2023. http://dx.doi.org/10.26480/smmp.01.2023.102.107.

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Helicopters have numerous rotating components, and the vibrations generated during flight are significant, which negatively affects the pilot’s flight control and physical and mental health. Therefore, vibration reduction and noise attenuation of helicopters are crucial research areas. Pilots complete flight missions through the flight control system, and the usability and comfort of the control system directly affect flight quality and safety. For a certain type of helicopter where excessive pedal vibration caused a “pedal-kick” fault, this paper employed a real-time vibration monitoring system to test and monitor the helicopter pedal vibration. Based on the flight test data, a spectral analysis was conducted on the helicopter pedal vibration signal to determine the abnormal vibration frequency. Then, by combining the comfort decrease limits and evaluation criteria for whole-body vibration exposure, the helicopter’s aft cabin pedal vibration was diagnosed for faults. The source of the pedal “kick” vibration was accurately located, and after implementing relevant measures, the fault was successfully resolved.
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Kumar, Anil, and Pinhas Ben-Tzvi. "An Inertial Sensor to Measure Wind Turbulence With RC Helicopters." In ASME 2017 Dynamic Systems and Control Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/dscc2017-5354.

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This paper presents a wireless sensor system developed to use RC helicopter dynamics to measure wind turbulence. Wind turbulence is a safety concern for naval helicopter operations due to typical scarcity of landing/takeoff area on naval vessels. Wind turbulence affects the dynamics of helicopters by creating uneven thrust on the rotor blades. The proposed telemetry system, when retrofitted on an RC helicopter, extracts these external disturbances in the helicopter’s dynamics and maps the wind conditions. This study focuses on learning the helicopter’s dynamics in controlled wind conditions using machine learning algorithms. The presented telemetry system uses sensors such as an Inertial Measurement Unit (IMU), optical trackers, and GPS sensors to measure the dynamics of the flying RC helicopter. The system also measures the pilot’s radio inputs to account for pilot inputs in the helicopter’s dynamics. The telemetry system is trained and tested in a large indoor facility where turbulent wind conditions were created artificially using large wind circulation fans.
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Frey, Felix, Jakob Thiemeier, Constantin Öhrle, Manuel Keßler, and Ewald Krämer. "Aerodynamic Interactions on Airbus Helicopters' Compound Helicopter RACER in Cruise Flight." In Vertical Flight Society 75th Annual Forum & Technology Display. The Vertical Flight Society, 2019. http://dx.doi.org/10.4050/f-0075-2019-14505.

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With the pursuit of extending the flight envelopes of helicopters towards higher cruise speed, helicopter manufacturers increasingly have come up with non-conventional configurations in recent years. Amongst these, Airbus Helicopters' RACER is a compound helicopter equipped with a boxwing and lateral pusher rotors. In combination with the main rotor, these additional components determine the aerodynamic characteristics of the helicopter. Thereby, depending on the flight conditions, their individual performance is influenced by a variety of interactions. As the understanding of these interactions is vital for the evaluation of the overall system, the respective mutual influence of main rotor, wings and lateral rotors is analysed in this paper for cruise flight. For this reason, high-fidelity coupled aerodynamic simulations are conducted not only for the full RACER configuration but also for reduced setups omitting individual components in order to isolate the effect of these components on the helicopter's aerodynamic performance.
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Frey, Felix, Manuel Keßler, Ewald Krämer, Jakob Thiemeier, and Constantin Öhrle. "Aerodynamic Interactions on Airbus Helicopters' Compound Helicopter RACER in Hover." In Vertical Flight Society 76th Annual Forum & Technology Display. The Vertical Flight Society, 2020. http://dx.doi.org/10.4050/f-0076-2020-16470.

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In recent years, helicopter manufacturers have developed an increasing number of non-conventional configurations in order to extend flight envelopes of helicopters towards higher cruise speed. Airbus Helicopters' approach is the compound helicopter RACER, which is equipped with a boxwing and lateral pusher rotors. As the combination of these components with the main rotor induces a variety of mutual interactions, influencing their individual aerodynamic performance depending on the flight conditions, the understanding of these interactions is vital for the evaluation of the overall system. For this reason, the respective mutual influence of main rotor, wings and lateral rotors is analysed in this paper for hover. With the help of high-fidelity coupled aerodynamic simulations for the full RACER configuration as well as for setups omitting individual components, first- and second-order interactions of these components are isolated and analysed for their effect on the helicopter’s aerodynamic performance.
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Leong, Michael. "Attack Helicopter Generations." In Vertical Flight Society 76th Annual Forum & Technology Display. The Vertical Flight Society, 2020. http://dx.doi.org/10.4050/f-0076-2020-16261.

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Attack helicopters have gone through several notable changes in development and capabilities throughout their history, changes which are continuing to this day. These changes can be captured in distinct generations of attack helicopters, with significant similarities to generations of fighter aircraft development. Understanding the technological development contained in each generation of attack helicopters gives a relative comparison of the capabilities contained in each and the technology trajectory of improvement. This paper will attempt to categorize attack helicopter development by generations, providing the various characteristics and rationale for each, as well as defining the implications of this development for current design and future attack helicopter improvements.
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Kumar, Anil, and Pinhas Ben-Tzvi. "Extraction of Impact of Wind Turbulence on RC Helicopters Using Machine Learning." In ASME 2016 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/detc2016-59384.

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This paper presents a new cost effective wireless telemetry system capable of estimating ambient air turbulence using RC helicopters. The proposed telemetry system correlates the RC helicopter’s flight dynamics with ship air wake patterns generated by cruising naval vessels. The telemetry system consists of two instrumentation units each equipped with aviation grade INS/IMU sensors to measure dynamics of the helicopter with respect to the concerned naval vessel. The presented telemetry system extracts ship air wake patterns by removing the helicopter dynamic effects from actual measurements. This paper presents a comprehensive comparison between popular machine learning algorithms in eliminating effects of pilot inputs from helicopter’s dynamics measurements. The system was tested on data collected in a wide range of wind conditions generated by modified YP676 naval training vessel in the Chesapeake Bay area over a period of more than a year.
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Fakhre, Ali, Vassilios Pachidis, Ioannis Goulos, Mahmood Tashfeen, and Pericles Pilidis. "Helicopter Mission Analysis for a Regenerated Turboshaft." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-94971.

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The aim of the study presented in this paper, is to compare helicopters employing simple cycle turboshaft engines, with helicopters employing novel regenerated turboshafts. Two existing helicopter configurations, a Twin Engine Light and a Twin Engine Medium are compared against regenerated configurations. The reference installed engines of both helicopters are notionally optimized by incorporating a heat exchanger, which enables heat transfer between the exhaust gas and the compressor delivery air to the combustion chamber. This process leads to a lower fuel input requirement as well as higher overall thermal efficiency compared to the reference simple cycle engine. The benefits arising from the adoption of the heat exchanger for both configurations are firstly presented by conducting part-load performance analysis for each optimized engine against its reference simple cycle engine. The obtained results suggest substantial reduction in specific fuel consumption for a major part of the operating power range with respect to both helicopter configurations. The results also demonstrate that the heat exchanger effectiveness is a critical parameter in achieving further reductions in specific fuel consumption. The study is further extended to investigate mission fuel burn saving limits for both helicopter configurations under the simulated part-load performance conditions by conducting a heat exchanger tradeoff study. The weight estimation correlation for the heat exchanger is adopted from the previously reported studies of similar fashion and is simulated accordingly for both helicopter configurations. A multi-disciplinary simulation tool with an integrated range of capabilities applicable to helicopter performance evaluation and mission analysis is adopted to simulate various types of missions, targeting wide range of helicopter operations. The results of the mission analysis suggest that the regenerated counterpart configurations are capable of achieving significant reductions in mission fuel burn. However, the level of gain from mission fuel burn savings is dependent on the selected helicopter mission profile, the recuperator design effectiveness as well as the overall evaluation criteria. The results also conclude that while the amount of benefit is dependent on various parameters, there is always an optimum “saving” region for each mission that justifies the need for regeneration.
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F. Sansón, Lázaro, Victor A. de Campos, and Alain S. Potts. "Robust Model-Based Fault Detection and Isolation of a Six Degree of Freedom Helicopter." In Congresso Brasileiro de Automática - 2020. sbabra, 2020. http://dx.doi.org/10.48011/asba.v2i1.1048.

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Helicopters are high cost and safety systems with a strong control system designed to maintain the helicopter performance, stability, and flight qualities. However, there exist faults that negatively aect the helicopter desirable behaviour; therefore, fault detection and isolation must be done to early detect, isolate and eliminate these faults. Because of helicopters are strongly nonlinear systems, and are aected by uncertainties and by external disturbances aswind bursts, robust residuals generation is required to correctly detect and isolate faults in the helicopter actuators and sensors. This paper leads with the robust fault detection and isolation of a six-degree of freedom helicopter benchmark using the disturbance decoupling method and the unknown input observer robust residuals generator. A generalized observer scheme is employed for fault isolation purposes.
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Green, David, Dr Harrison, Dr Bayoumi, and Hamid Nouri. "An Innovative Approach for Establishing Power Train Inspection Intervals of Modern Helicopters." In Vertical Flight Society 75th Annual Forum & Technology Display. The Vertical Flight Society, 2019. http://dx.doi.org/10.4050/f-0075-2019-14654.

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Modern transmissions are the product of years of development. The newest materials and software are typically used to design helicopter power trains that are expected to safely endure operations traditionally characterized as representing composite worst-case usage, a level of usage severity that is well above the limits established in the OEM flight manual. In addition, the introduction of Helicopter Flight Data Monitoring programs has systematically constrained the actual usage to a level of severity that is substantially below that allowed by the OEM flight manual. Validation projects have enabled experience to be accumulated with a variety of helicopters and this has demonstrated that many helicopters are currently operating in a way that is best described as involving benign usage. This is partially because the assemblies are so robust and partially because some helicopter usage is systematically constrained to the flight profiles that are actually needed to accomplish the missions. This paper finds that a significant portion of most modern helicopter fleets actually experience benign usage. This finding supports the conclusion that helicopter OEMs can and should provide operators with the option to choose either the traditional inspection intervals for unmonitored operations or choose a set of longer supplemental inspection intervals for helicopters involved in monitored flight operations.
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Wang, Shengda, and Kourosh Danai. "A Forward Approach for Helicopter Track and Balance." In ASME 2002 International Mechanical Engineering Congress and Exposition. ASMEDC, 2002. http://dx.doi.org/10.1115/imece2002-33453.

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A method of helicopter track and balance is introduced that uses a forward-model to search for the appropriate blade modifications. This method uses an interval model to represent the ranges of effects of blade modifications on helicopter vibration, instead of exact values, in order to cope with the stochastic nature of aircraft vibration. The coefficients of the interval model are initially defined according to sensitivity coefficients between the blade modifications and helicopter vibration, but they are subsequently updated after each tuning iteration to improve the model’s estimation accuracy. The effectiveness of the proposed method is demonstrated through a simulation model that represents experimental vibration measurements of Black Hawk helicopters.
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Reports on the topic "Helicopter"

1

Pogorzelski, Ronald J., and Vaughn P. Cable. Helicopter Rotor Antenna. Fort Belvoir, VA: Defense Technical Information Center, June 2001. http://dx.doi.org/10.21236/ada395307.

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Fries, Joseph. Helicopter Trim Analysis. Fort Belvoir, VA: Defense Technical Information Center, June 1996. http://dx.doi.org/10.21236/ada310293.

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Brandyberry, M. D. Helicopter Crash Frequency. Office of Scientific and Technical Information (OSTI), March 1990. http://dx.doi.org/10.2172/656442.

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Johnson, Norman T. Why Aren't Helicopters Operating Jointly: A Case for a Joint Helicopter Doctrine. Fort Belvoir, VA: Defense Technical Information Center, October 2010. http://dx.doi.org/10.21236/ada535470.

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Lux, C. Helicopter Crash Frequency for DWPF. Office of Scientific and Technical Information (OSTI), April 2002. http://dx.doi.org/10.2172/1482194.

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Shanahan, Dennis F. Basic Principles of Helicopter Crashworthiness. Fort Belvoir, VA: Defense Technical Information Center, February 1993. http://dx.doi.org/10.21236/ada267099.

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Houtsma, Adrianus J. Nonspeech Audio in Helicopter Aviation. Fort Belvoir, VA: Defense Technical Information Center, December 2003. http://dx.doi.org/10.21236/ada419911.

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Amador, Manuel, and Javier Bianchi. Helicopter Drops and Liquidity Traps. Cambridge, MA: National Bureau of Economic Research, March 2023. http://dx.doi.org/10.3386/w31046.

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Miller, Billy J. Requirement for a Light Combat Helicopter. Fort Belvoir, VA: Defense Technical Information Center, March 1986. http://dx.doi.org/10.21236/ada177631.

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McEntire, B. J., and Dennis F. Shanahan. Mass Requirements for Helicopter Aircrew Helmets,. Fort Belvoir, VA: Defense Technical Information Center, August 1997. http://dx.doi.org/10.21236/ada328597.

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