Relevant bibliographies by topics / Aircraft’s life

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Aircraft’s life'

Author: Grafiati
Published: 30 May 2022
Last updated: 31 July 2025

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Journal articles on the topic "Aircraft’s life"

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Fu, Yueshuai, and Huimin Fu. "A Novel Individual Aircraft Life Monitoring Method Based on Reliable Life Consumption Assessment." Machines 11, no. 11 (2023): 1016. http://dx.doi.org/10.3390/machines11111016.

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Individual life monitoring is crucial for ensuring aircraft flight safety. Conventional life-consumption-based monitoring methods ignore reliability, thus disjoining them from the aircraft’s reliable life determination and extension, where high confidence and reliability are required. Therefore, this paper proposes a reliable life consumption and individual life monitoring method for aircraft structure fatigue. In the paper, the P-S-N curve, i.e., the relationship between the aircraft structure’s life (N) and fatigue load (S) under a certain probability (P), is established, by which the lower
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Kuzmich, O., P. Arkushenko, M. Andrushko, and S. Ratushny. "REGARDING THE ORGANIZATION OF THE INFORMATION SECURITY PROCESS OF THE AIRCRAFT’S LIFE CYCLE COMPONENT." Наукові праці Державного науково-дослідного інституту випробувань і сертифікації озброєння та військової техніки 14, no. 4 (2022): 93–98. http://dx.doi.org/10.37701/dndivsovt.14.2022.10.

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In recent years a number of significant changes have taken place in the field of control, regulation and management in the development processes, manufacture and aircraft’s operation, new international requirements and standards in the field of ensuring flight safety have been put into effect. Large-scale implementation of information technologies in the supporting the technical operation processes of aircraft and monitoring safety of aviation activity is being carried out.
 The analysis of modern views on the provision in the information component of the aircraft life cycle indicates the
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Hasan, Yusra, Ishak Hasan, Amir A. Aliabadi, and Bahram Gharabaghi. "Comparative Life Cycle Assessment (LCA) in the Aerospace Industry Regarding Aviation Seat Frame Options." Sustainability 17, no. 7 (2025): 3188. https://doi.org/10.3390/su17073188.

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The aerospace industry is actively seeking sustainable solutions within the aviation sector to mitigate greenhouse gas (GHG) emissions driven by increasing population demands. This study presents the first environmental life cycle assessment (LCA) of economy-class seating frames, comparing conventional alloy steel with lightweight alternative materials, including magnesium alloy, aluminum alloy, and titanium. Seat frames account for an aircraft’s total weight, making them a critical component for innovation toward more sustainable solutions. Using SolidWorks V3.1, economy-class seat frames wer
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Gerhardinger, David, Anita Domitrović, and Ernest Bazijanac. "Fatigue Life Prognosis of a Light Aircraft Landing Gear Leg." Annual Conference of the PHM Society 12, no. 1 (2020): 9. http://dx.doi.org/10.36001/phmconf.2020.v12i1.1245.

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Aircraft components are subject to fatigue damage. The prediction of fatigue life has significant influence on maintenance and flight operations. Light aircraft, designed for recreational purposes, have vital components that are subject to a hard time maintenance approach. The focus of this article is on a simple method for predicting fatigue life. The method is applied to a light aircraft’s fixed landing gear leg. The landing gear leg is modelled in a computer aided design environment. The load spectrum is determined, based on a characteristic flight profile. Principal strains are determined
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Naeem, M. "Impacts of low-pressure (LP) compressor’s deterioration of a turbofan engine upon fuel-usage of a military aircraft." Aeronautical Journal 112, no. 1127 (2008): 33–45. http://dx.doi.org/10.1017/s0001924000001974.

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AbstractSome in-service deterioration in any mechanical device, such as an aircraft’s gas-turbine engine, is inevitable. However, its extent and rate depend upon the qualities of design and manufacture, as well as on the maintenance/repair practices followed by the users. Deterioration of an engine normally results in the engine seeking a different steady operating-point relative to that for an engine without any deterioration. The variation in engine’s steady operating point leads to changes in the specific fuel consumption (SFC) and/or fuel flow (FF). Any rise in SFC and/or FF and thereby th
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Natarajan, Balakrishnan, Amarnadha Reddy, and Nitin Sharma. "A Secure, Configurable, Wireless System for Transfer of Sensor Data from Aircraft to Ground." Defence Science Journal 72, no. 6 (2022): 771–82. http://dx.doi.org/10.14429/dsj.72.17713.

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Modern aircraft are complex systems, equipped with hundreds of embedded sensors that record a wide repertoire of data during flight, such as crucial engine and airframe parameters, status of flight control system, air conditioning system, landing gear, life-saving and emergency systems. The data from the sensors is stored in the Flight Data Recorder. Maintenance personnel routinely transfer this sensor data to a ground terminal device to analyze it for aircraft health and performance monitoring purposes. Manual methods of extracting sensor data can be tedious and error-prone when large fleets
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Ge, Zengwen. "Testing method for electrical properties on moving cables of civil aircraft." Journal of Physics: Conference Series 3026, no. 1 (2025): 012059. https://doi.org/10.1088/1742-6596/3026/1/012059.

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Abstract Moving cables of civil aircraft should meet the requirements of the aircraft’s whole life cycle, and the electrical property test is an important means to determine whether the cables are qualified. This paper introduces a test method for electrical properties, including building a test platform based on cable motion characteristics, establishing a test principle based on the relationship between voltage and resistance, clarifying the test idea, etc., and taking the development project of a domestic aircraft Moving cables as an example. This method has been proven to have important pr
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White, Paul, David Mongru, and Lorrie Molent. "A crack growth–based individual aircraft monitoring method utilising a damage metric." Structural Health Monitoring 17, no. 5 (2017): 1178–91. http://dx.doi.org/10.1177/1475921717738389.

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The need and benefits of individual aircraft fatigue monitoring are now well established. There are broadly two fatigue damage methods employed for this purpose, namely, crack growth and stress (or strain)-life. The crack growth methods tend to provide a relative comparison between an aircraft’s usage and a baseline usage, while the strain-life methods provide a measure of the amount of fatigue life consumed against that (generally) demonstrated through a fatigue test. In this article, a new crack growth–based tracking method is described that also includes a measure of the certified fatigue l
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Chen, Chui Xin, and Yang Hong Mao. "Design of Remote Control Aircraft Model Based on ARM." Applied Mechanics and Materials 568-570 (June 2014): 954–57. http://dx.doi.org/10.4028/www.scientific.net/amm.568-570.954.

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The system designs wireless remote control airplane model, operatie the keys of the remote controller, after the model aircraft receiving the instruction, and handle through the ARM, control the aircraft forward or backward. While the aircraft are working turn left and turn right and straight line, the system makes a judgment on the ultrasonic feedback information, and then control the aircraft’s direction of movement, and display the corresponding information on LCD. after several debugging and operating, System can work stable and reliable. This model can be widely used in the industry and a
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Venugopal, Arvinthan, Roslina Mohammad, Md Fuad Shah Koslan, Syed Roslee Sayd Bakar, and Alizarin Ali. "The Effect of Tropical Environment on Fatigue Failure in Royal Malaysian Airforce (RMAF) Aircraft Structure and Operational Readiness." Materials 14, no. 9 (2021): 2414. http://dx.doi.org/10.3390/ma14092414.

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The environmental condition in which the Royal Malaysian Airforce is currently operating its aircraft is prone to corrosion. This is due to the high relative humidity and temperature. With most of its aircraft being in the legacy aircraft era, the aircraft’s main construction consists of the aluminium 2024 material. However, this material is prone to corrosion, thus reducing fatigue life and leading to fatigue failure. Using the concept of either Safe Life or Damage Tolerance as its fatigue design philosophy, the RMAF adopts the Aircraft Structure Integrity Program (ASIP) to monitor its struct
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Dissertations / Theses on the topic "Aircraft’s life"

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Ramesh, Aashish, and Gaurav Kalkur. "Fatigue life validation of aircraft materials." Thesis, Linköpings universitet, Mekanik och hållfasthetslära, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-170893.

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Fatigue is one of the critical design aspects with immense significance where thefatigue life of a material can be stated as the number of cycles that a componentcan withstand under a particular type of loading without failure. The design processhas to include fatigue analysis in order to predict failure due to fatigue. This helpsin maintenance and servicing of a component reducing the chance of failure duringoperation of the component. Increased efficiency of predictive maintenance improvesthe life of the component.This thesis aims to study the relationship between the experimental, analytica
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Öhrn, Philip, and Markus Åstrand. "Direct Lift Control of Fighter Aircraft." Thesis, Linköpings universitet, Reglerteknik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-157464.

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Direct lift control for aircraft has been around in the aeronautical industry for decades but is mainly used in commercial aircraft with dedicated direct lift control surfaces. The focus of this thesis is to investigate if direct lift control is feasible for a fighter aircraft, similar to Saab JAS 39 Gripen, without dedicated control surfaces. The modelled system is an aircraft that is inherently unstable and contains nonlinearities both in its aerodynamics and in the form of limited control surface deflection and deflection rates. The dynamics of the aircraft are linearised around a flight ca
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Erasmus, Daniel Jacobus. "The fatigue life cycle prediction of a light aircraft undercarriage." Thesis, Nelson Mandela Metropolitan University, 2010. http://hdl.handle.net/10948/1527.

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The reliability of systems relies heavily on accurate fatigue life prediction of related components. Fatigue life prediction is a complicated process requiring the correct methodology to determine accurate and reliable predictions. The Palmgren – Miner damage accumulation hypothesis is widely used in determining the fatigue life of components exposed to variable loading conditions. Modifications have been made to this hypothesis trying to achieve a greater degree of accuracy, of these the Liu – Zenner modification has been the most successful. In this report the systematic process of fatigue l
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Henzler, Eric, and Mark Williams. "Is electronic life-cycle tracking of aircraft parts degrading readiness?" Thesis, Monterey, California: Naval Postgraduate School, 2013. http://hdl.handle.net/10945/38944.

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Approved for public release; distribution is unlimited.<br>The Naval Aviation Logistics Command Managed Information System (NALCOMIS), the current Navy and Marine Corps electronic tracking system for aircraft components, provides complete, up-to-date life-cycle information about aircraft and associated components to all maintenance agencies across the Naval Aviation Enterprise (NAE). By design, the system is meant to facilitate efficient receipt, repair, documentation, and transfer of all aircraft and components inducted into the maintenance cycle. However, many end users within the NAE still
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Crowley, Christopher Keith Aerospace Civil &amp Mechanical Engineering Australian Defence Force Academy UNSW. "Meeting the ageing aircraft challenge." Awarded by:University of New South Wales - Australian Defence Force Academy. School of Aerospace, Civil and Mechanical Engineering, 2004. http://handle.unsw.edu.au/1959.4/38679.

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&quotMeeting the ageing aircraft challenge&quot is not just about safety, not just about effectiveness, and not just about economy of support. It is about proactive and reactive optimization of all three service goals throughout long life cycles that span 20 or 30 years, or more, and typically, beyond the originally intended design life. It is therefore about organizational attitudes towards ongoing trend analysis and condition monitoring, and pervading cost benefit assessments of all forms of human innovation across what the author describes as 'the eight sustaining disciplines for long aero
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Goebel, James E. "Design of a lift fan engine for a heavy lift aircraft." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Dec%5FGoebel.pdf.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, December 2003.<br>Thesis advisor(s): Raymond Shreeve, E.R. Wood. Includes bibliographical references (p. 41). Also available online.
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Iskender, Hani. "Aircraft Simulator." Thesis, Linköping University, Department of Electrical Engineering, 2005. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-2936.

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<p>At Saab Bofors Dynamics there are projects running which purpose are to develop simulators for various weapon systems like RBS 70. In order to manage creating real working simulators Saab Bofors Dynamics has to do more research and this final thesis is a part of this process.</p><p>This final thesis has been performed at Saab Bofors Dynamics in the department of modelling and simulation, RTRKM, in Karlskoga. The purpose was to develop a control algorithm which makes it possible for an aircraft to behave real when controlling through a joystick.</p><p>The conclusions show that further improv
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Alqetami, Isa Mohamed. "Life Cycle Management of Bahraini Amiri Air Force F-16 Aircraft." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2001. http://handle.dtic.mil/100.2/ADA397511.

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Holmberg, Gunnar. "On aircraft development : managing flexible complex systems with long life cycles /." Linköping : Univ, 2003. http://www.bibl.liu.se/liupubl/disp/disp2003/tek853s.pdf.

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Liu, Ziqian. "Life cycle assessment of composites and aluminium use in aircraft systems." Thesis, Cranfield University, 2013. http://dspace.lib.cranfield.ac.uk/handle/1826/8573.

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As a consequence of the gradually expanding aviation network, civil aircrafts are occupying an increasingly high proportion of the transport industry. Air transport now dominates the intercity rapid transit, long-distance passenger transport, international passenger and freight transport, and specific regional transport, advantaged as it is by fast, convenient, comfortable and safe options. Nevertheless, the potential adverse impact on the environment of air transport, specifically, in the case of this research, the pollutants generated during aircraft production remain a concern. Using the A3
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Books on the topic "Aircraft’s life"

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Niver, Heather Moore. Life on an aircraft carrier. Gareth Stevens Pub., 2013.

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Niver, Heather Moore. Life on an aircraft carrier. Gareth Stevens Pub., 2013.

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Engineers, Society of Automotive, ed. Aircraft engine life cycle cost. Society of Automotive Engineers, 1987.

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Deckert, W. H. Powered-lift aircraft technology. Scientific and Technical Information Division, National Aeronautics and Space Administration, 1989.

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Deckert, W. H. Powered-lift aircraft technology. Scientific and Technical Information Branch, National Aeronautics and Space Administration, 1989.

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Deckert, W. H. Powered-lift aircraft technology. NASA, 1989.

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United States. National Aeronautics and Space Administration., ed. A life saving device for ships. National Aeronautics and Space Administration, 1985.

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Savage, M. Life and dynamic capacity modeling for aircraft transmissions. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

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1935-, Smart D. F., Worgul B. V, and COSPAR, eds. Space life sciences: Aircraft and space radiation environment. Published for the Committee on Space Research [by] Elsevier, 2005.

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Michael, Savage. Life and dynamic capacity modeling for aircraft transmissions. Lewis Research Center, 1991.

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Book chapters on the topic "Aircraft’s life"

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Rozhkova, Liubov, and Timur Tyncherov. "Remaining Useful Life for Tires on Aircraft’s Main Wheels: Prediction Based on Quick Access Recorder Data." In Lecture Notes in Networks and Systems. Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-68476-1_13.

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Molent, Lorrie. "Fleet Management, Repair and Life-Enhancement Considerations." In Aircraft Fatigue Management. Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-99-7468-9_8.

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Howe, Denis. "Basic Lift, Drag and Mass Representations." In Aircraft Conceptual Design Synthesis. John Wiley & Sons, Ltd, 2014. http://dx.doi.org/10.1002/9781118903094.ch6.

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Franz, Katharina, Ralf Hörnschemeyer, Arthur Ewert, et al. "Life Cycle Engineering in Preliminary Aircraft Design." In Leveraging Technology for a Sustainable World. Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-29069-5_80.

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Decher, Reiner. "The Vortex and Wing Lift." In The Vortex and The Jet. Springer Singapore, 2022. http://dx.doi.org/10.1007/978-981-16-8028-1_2.

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AbstractThe vortex is a necessary element of fluid motion for the generation of aerodynamic forces. For flight, lift balances the weight of an aircraft and the means for providing lift is the wing constructed to move oncoming air downward in a controlled fashion. Nature allows this to happen by establishing a flow about the wing that, from a distance, is like a vortex, the kind we see in nature. Unlike a compact natural vortex like a tornado, a surface, like an airfoil, distributes the vortex into smaller elements along the surfaces. In the chapter, we look at how and why.
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Wild, Jochen. "Aircraft Performance at Take-Off and Landing." In High-Lift Aerodynamics. CRC Press, 2021. http://dx.doi.org/10.1201/9781003220459-4.

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Chan, K. W., G. J. Trmal, A. P. H. May, and G. Southcombe. "Reliability of Aircraft High Lift Devices." In COMADEM 89 International. Springer US, 1989. http://dx.doi.org/10.1007/978-1-4684-8905-7_16.

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Kirov, Dmitrii, and Simone Fulvio Rollini. "Benchmark: Remaining Useful Life Predictor for Aircraft Equipment." In Bridging the Gap Between AI and Reality. Springer Nature Switzerland, 2023. http://dx.doi.org/10.1007/978-3-031-46002-9_18.

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Baluch, Haroon Awais, and Michel van Tooren. "Multidisciplinary Design of Flexible Aircraft." In Collaborative Product and Service Life Cycle Management for a Sustainable World. Springer London, 2008. http://dx.doi.org/10.1007/978-1-84800-972-1_36.

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De Gennaro, Michele, James Page, Isik Ozcer, Guillaume Moula, Salvatore Corcione, and Vincenzo Cusati. "Advances on the Next Generation Short-Medium Range Aircraft Rear End: The CleanSky 2 Project IMPACT." In Lecture Notes in Mobility. Springer Nature Switzerland, 2025. https://doi.org/10.1007/978-3-031-89444-2_15.

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Abstract This paper aims at presenting the results of the CleanSky 2 European project IMPACT (GA no. 885052), granted under the Large Passenger Aircraft Integrated Technology Demonstrator (LPA-ITD), aiming at optimizing the rear-end design for the next generation Short and Medium Range (SMR) A320-like aircraft. Specifically, the project has investigated a Forward Swept Horizontal Tail Plane (FSHTP) enhanced with a Leading-Edge eXtension (LeX) device. The activities have focused on the optimisation of the horizontal stabilizer, accounting for the coupled aerodynamic, aeroelastic and, for the fi
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Conference papers on the topic "Aircraft’s life"

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Kelly, Stacey, and John Lloyd. "V-22 Osprey Maintenance Cost Savings using SAFE for Fatigue Life Calculations." In Vertical Flight Society 71st Annual Forum & Technology Display. The Vertical Flight Society, 2015. http://dx.doi.org/10.4050/f-0071-2015-10233.

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The V-22 SAFE (Structural Appraisal of Fatigue Effects) is a software program for the V-22 Osprey tiltrotor aircraft that calculates fatigue damage for serialized components based on the aircraft's actual usage instead of a pre-defined design spectrum. SAFE allows life limited aircraft components to remain on the aircraft beyond the initially defined fatigue life if the aircraft was flown less aggressively than the design spectrum. Although fatigue lives for the various components are determined with the same design usage spectrum for the aircraft, different maneuvers within that design spectr
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şerpar, Ariana-Andra. "Prepared for Lift-Off: Hybrid CNN-LSTM Architecture for Aircraft Engine Remaining Useful Life Estimation." In 2024 26th International Symposium on Symbolic and Numeric Algorithms for Scientific Computing (SYNASC). IEEE, 2024. https://doi.org/10.1109/synasc65383.2024.00066.

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Singletary, Harold J. "Aircraft Service Life Extension through Corrosion Control." In CORROSION 1987. NACE International, 1987. https://doi.org/10.5006/c1987-87217.

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Abstract Escalating costs of new inventory and long lead time for many replacement parts have created greater emphasis among aircraft operators to establish a corrosion control program that will increase service life of their equipment. The paper stresses practical methods for protecting and extending the life of aircraft structure and systems. It describes how a corrosion engineer goes about developing a tailored corrosion control program for the aircraft operator.
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Duffy, Michael, and Tony Samaritano. "The LIFT! Project - Modular, Electric Vertical Lift System." In Vertical Flight Society 71st Annual Forum & Technology Display. The Vertical Flight Society, 2015. http://dx.doi.org/10.4050/f-0071-2015-10502.

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The LIFT! Project explored scaling of all-electric multi-rotor propulsion and methods of cooperation between multiple VTOL aircraft. Multi-rotor aircraft have become pervasive throughout the hobby industry, toy industry and research institutions due - in part - to very powerful, inexpensive inertial measurement devices and increased energy density of Li-Ion batteries driven by the mobile phone industry. This research demonstrates the viability of large multi-rotor systems up to two magnitudes of gross weight larger than a typical COTS hobby multi-rotor vehicle. Furthermore, this research demon
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Schrage, Daniel, and Alex Van. "A DAVBA Approach for Complex VTOL Aircraft Development." In Vertical Flight Society 71st Annual Forum & Technology Display. The Vertical Flight Society, 2015. http://dx.doi.org/10.4050/f-0071-2015-10269.

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As aircraft systems become more complex the need to integrate software and hardware at different levels of abstraction becomes more important. For complex civil aircraft USA and Europe have reached a consensus in "Guidelines for Development of Civil Aircraft and Systems Development" in SAE ARP 4754A/ED-79. This document discusses the development of aircraft systems taking into account the overall aircraft operating environment and functions. This includes validation of requirements and verification of the design implementation for certification and product assurance. It provides practices for
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Miller, Robert N., and R. L. Schuessler. "Predicting Service Life of Aircraft Coatings in Various Environments." In CORROSION 1989. NACE International, 1989. https://doi.org/10.5006/c1989-89600.

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Abstract There is a great need for a method of evaluating aircraft coating systems and predicting their performance under a variety of service conditions. This paper describes an accelerated simulated service test and a procedure for using the test results to predict the time to initial breakdown of the coating and the optimium time for complete repaint of aircraft operating in various environments. The predictive coating degradation procedure involves a statistical analysis which is based on reliability theory. Multiple coated panels are subjected to an environmental spectrum which includes t
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Bavarian, Behzad, Lisa Reiner, Hamed Youssefpour, and Ivan Juraga. "Vapor Phase Inhibitors to Extend the Life of Aging Aircraft." In CORROSION 2005. NACE International, 2005. https://doi.org/10.5006/c2005-05329.

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Abstract Localized corrosion of Al-alloys in the aircraft industry can cause expensive catastrophic failures, especially in aging aircraft. To further aggravate conditions, aircraft maintenance with conventional cleaning solutions can gradually destroy the protective Al oxide film and accelerate corrosion in crevices and lap joints. VCI 415, a solution with corrosion inhibition properties used for washing/rinsing aircraft was investigated to determine the corrosion susceptibility for several Al alloys. The VCI 415 chemical composition, as determined from XPS analysis, is a mixture of sodium co
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Martinel, François, and Jean-loup Gatti. "System Geometrical Management." In Vertical Flight Society 70th Annual Forum & Technology Display. The Vertical Flight Society, 2014. http://dx.doi.org/10.4050/f-0070-2014-9648.

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This process, based on end to end philosophy defines the way of managing geometrical specifications concerning the aircraft during its complete lifecycle. Final geometry of an aircraft is the result of many manufacturing operations performed by many stakeholders. As a result, geometrical management is centered on Frontier and Interface management, following the sharing of responsibilities of vehicle systems and integrators. System geometrical Management is based on functional analysis of the Helicopter vehicle. This is a top-down approach leading to systems specification at each level of the A
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Hall, G. Warren. "Risk Management: A Test Pilot’s Perspective." In ASME 2000 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/imece2000-1018.

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Abstract To achieve advances in technology and aeronautics, experimental aircraft with untested characteristics and unknown risks must be flown. The test pilot puts his life on the line and assumes the ultimate risk during the first flight. To minimize the effects of unknown risks, the pilot’s primary risk mitigation rests in rigorous preparation for the first flight. This preparation requires input to the designers about the aircraft’s flightworthiness, extensive study, in addition to many hours in aircraft simulation where catastrophic events must be anticipated and emergency procedures acti
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Ames, Eric C., and Raja V. Pulikollu. "Virtual Life and Performance Modeling of Aerospace Spiral Bevel Gears." In ASME 2013 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/detc2013-12351.

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Spiral bevel gears are widely used in the tail rotor drive trains of most rotorcraft. The loads associated with the tail rotor drive train are generally much more variable than those in the main rotor drive train primarily resulting from maneuvers. Over the life of any particular military rotorcraft it is not uncommon for the aircraft’s operating gross weight to steadily increase, causing the aircraft to fly at higher mean power levels and thus increasing the operating load spectrum associated with the tail rotor drive train. Special missions and equipment such as pulling a mine sweeping sled
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Reports on the topic "Aircraft’s life"

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Heymsfield, Ernie, and Jeb Tingle. State of the practice in pavement structural design/analysis codes relevant to airfield pavement design. Engineer Research and Development Center (U.S.), 2021. http://dx.doi.org/10.21079/11681/40542.

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An airfield pavement structure is designed to support aircraft live loads for a specified pavement design life. Computer codes are available to assist the engineer in designing an airfield pavement structure. Pavement structural design is generally a function of five criteria: the pavement structural configuration, materials, the applied loading, ambient conditions, and how pavement failure is defined. The two typical types of pavement structures, rigid and flexible, provide load support in fundamentally different ways and develop different stress distributions at the pavement – base interface
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APR CONSULTANTS INC MEDWAY OH. A Practical Method for Aircraft Life Enhancement. Defense Technical Information Center, 1998. http://dx.doi.org/10.21236/ada362642.

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Elsner, J. H., K. L. Boyd, and J. A. Harter. Verification of Life Prediction Methods for Aging Aircraft Structures. Defense Technical Information Center, 1997. http://dx.doi.org/10.21236/ada339094.

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Muller, R. P. Feasibility Study for Life Enhancement of Military Aircraft Through Re-Squeezing Joints with Geriatric Aircraft. Defense Technical Information Center, 2001. http://dx.doi.org/10.21236/ada399037.

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Henzler, Eric, and Mark Williams. Is Electronic Life-Cycle Tracking of Aircraft Parts Degrading Readiness? Defense Technical Information Center, 2013. http://dx.doi.org/10.21236/ada612967.

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Thomas, R., and W. E. Franklin. Life Cycle Assessment for PC Blend 2 Aircraft Radome Depainter. Defense Technical Information Center, 1996. http://dx.doi.org/10.21236/ada349115.

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Reason, William. Helicopter Aircrew Integrated Life Support System (HAILSS) Aircraft Integration Tests. Defense Technical Information Center, 1999. http://dx.doi.org/10.21236/ada377892.

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Fernandez, Ruben, Hernando Lugo, and Georfe Dulikravich. Aerodynamic Shape Multi-Objective Optimization for SAE Aero Design Competition Aircraft. Florida International University, 2021. http://dx.doi.org/10.25148/mmeurs.009778.

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The SAE Regular Class Aero Design Competition requires students to design a radio-controlled aircraft with limits to the aircraft power consumption, take-off distance, and wingspan, while maximizing the amount of payload it can carry. As a result, the aircraft should be designed subject to these simultaneous and contradicting objectives: 1) minimize the aerodynamic drag force, 2) minimize the aerodynamic pitching moment, and 3) maximize the aerodynamic lift force. In this study, we optimized the geometric design variables of a biplane configuration using 3D aerodynamic analysis using the ANSYS
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Kristof, Nicholas A. Hybrid Aircraft for Heavy Lift / High Speed Strategic Mobility. Defense Technical Information Center, 2011. http://dx.doi.org/10.21236/ad1019070.

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Wezeman, Siemon T. International Transfers of Combat Aircraft, 2005–2009. Stockholm International Peace Research Institute, 2010. http://dx.doi.org/10.55163/urrc9996.

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Stories like the United State's planned sale of combat aircraft to Saudi Arabia, Israel's and Canada's selection of the US Joint Strike Fighter, and ongoing competition for large orders from India and Brazil are making headlines in the media. This SIPRI Fact Sheet shows that combat aircraft together with related weapons and components accounted for one-third of worldwide arms transfers in the past five years and highlights concerns about the economic and security consequences of these transfers.
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