Relevant bibliographies by topics / Aircraft engine performance

Academic literature on the topic 'Aircraft engine performance'

Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Aircraft engine performance"

1

A., Armaan, and Srinivas G. "In Tune with Times: Recent Developments in Theoretical, Experimental and Numerical techniques of Aircraft Engines." International Journal of Engineering & Technology 7, no. 2 (May 23, 2018): 805. http://dx.doi.org/10.14419/ijet.v7i2.10910.

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Today the aircraft engine designing and development work is increasing drastically. Especially aircraft engines play a vital role in order to decide the aircrafts speed and its performance. Broadly turbojet, turboprop, turbo shaft and turbofan engines comes under the category of air breathing engines. Every engine has its own purpose and application. But modern aircrafts require much more advancements. Designing a new aircraft engine has been a really challenging task to the researchers. But giving a complete holistic view of aircraft engines and research gap would definitely help a lot to the new designers. Once identified the drawbacks of engine performance can be corrected in the future. For any new design of aircraft engine researchers are suggested to take Theoretical, Experimental and Numerical approaches. Therefore present paper makes an effort to review complete recent Theoretical, Experimental and Numerical approaches which are followed till date. Under all the three approaches all the air breathing engines have been clearly explained and solicited. The effort is to identify the gaps between different approaches which are hampering the process of engine development. The paper also gives the research gaps that need to be incorporated for effective performance enhancement of the aircraft engines for aeromechanical features.
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Chen, Min, Zihao Jia, Hailong Tang, Yi Xiao, Yonghang Yang, and Feijia Yin. "Research on Simulation and Performance Optimization of Mach 4 Civil Aircraft Propulsion Concept." International Journal of Aerospace Engineering 2019 (January 14, 2019): 1–19. http://dx.doi.org/10.1155/2019/2918646.

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Supersonic civil aircraft is of a promising area in the development of future civil transport, and aircraft propulsion system is one of the key issues which determine the success of the aircraft. To get a good conceptual design and performance investigation of the supersonic civil aircraft engine, in this article, a fast, versatile as well as trust-worthy numerical simulation platform was established to analyze the Mach 4 turbine-based combined cycle (TBCC) engine concept so as to be applied to the supersonic civil aircraft. First, a quick and accurate task requirement analysis module was newly established to analyze the mission requirement of the Mach 4 supersonic civil aircraft. Second, the TBCC engine performance simulation model was briefly presented and the number of engines on the supersonic civil aircraft was analyzed, considering single engine inoperative. Third, the Stone model and the DLR method were investigated to estimate the engine jet noise and the NOx emission of the Mach 4 supersonic civil aircraft. Finally, a multiobjective optimization tool made up of a response surface method and a genetic algorithm was developed to optimize the design parameters and the control law of the TBCC engine, in order to make the Mach 4 supersonic civil aircraft engine with better performance, lower noise, and lower emissions. The uniqueness of the developed analysis tool lies in that it affords a numerical simulation platform capable of investigating the task requirement analysis module of the supersonic civil aircraft, engine jet noise prediction model, and the NOx emission prediction model, as well as a multiobjective performance optimization tool, which is beneficial for the conceptual design and performance research of Mach 4 supersonic civil aircraft’s propulsion system.
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Улитенко, Ю. А. "ВІДНОСНИЙ КРИТЕРІЙ ЕФЕКТИВНОСТІ ВИСОКОШВИД-КІСНОГО ЛІТАЛЬНОГО АПАРАТА." Open Information and Computer Integrated Technologies, no. 85 (July 29, 2019): 151–66. http://dx.doi.org/10.32620/oikit.2019.85.09.

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Development of perspective high-speed aircrafts inseparably linked with level of aircraft propulsion engineering as engine performances to determine aircraft capabilities as a whole. The basic requirements to engines of high-speed aircrafts are increase speed and flight height. With each new generation of turbojet bypass engine with afterburner their specific thrust and a specific impulse are increase, also application of high technologies raises leads to substantial growth of the engine cost too. At the same time existing engines design has the big reserves for modernization. For a quantitative assessment of the degree of influence of the new technical solution on the quality of the task performance by the aviation complex, criteria (indicators) of efficiency are used. However, it is not possible to find a direct functional dependence of the overall criterion of the effectiveness of the aviation complex on the technical and operational characteristics, conditions of use of a high-speed aircraft. The purpose of this work is to develop a methodology for determining the economic criterion for assessing the degree of influence of a new technical solution on the quality of the task performance by the aviation complex (the value of the integrated performance criterion). The text of the paper provides an analysis of recent research and publications. The developed relative criterion of the efficiency of a high-speed aircraft makes it possible to accomplish the goal set, as well as to estimate the costs at the cost of which the final result is achieved. It is shown that boosting engines with water injection has some advantage over other options for increasing the thrust of high-speed aircraft engines. The application of the obtained results can be used to substantiate new technical solutions and establish their impact on the quality of the task performance by the aviation complex, as well as reduce the time to create competitive high-speed aircraft.
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Zhou, Hong, Zhan Xue Wang, and Xiao Bo Zhang. "Areo-Engine Cycle Parametric Analysis and Installed Performance Calculation Based on Aircraft Flight Mission." Applied Mechanics and Materials 482 (December 2013): 277–81. http://dx.doi.org/10.4028/www.scientific.net/amm.482.277.

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The aircraft/engine integration design numerical simulation model was established. The engine design performance specifications were obtained by calculating aircraft lift-drag characteristics, mission analysis, constraint analysis. Combining engine cycle parametric analysis with installation loss computing, the engine performance parameters can be found, which meet the aircraft flight envelope performance requirements. Taking double bypass variable cycle engine as an example to check the model, the results show that the variable cycle engine can meet aircrafts thrust and fuel consumption demands under different operating conditions, and achieve cruise thrust adjustment at the same inlet mass flow to reduce installation losses.
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Sabaruddin, Ainul Aniyah, Surjatin Wiriadidjaja, Dayang Laila Abang Abdul Majid, Harijono Djojodihardjo, and Mohamed Tarmizi Ahmad. "An Investigation on the Effect of Variable Valve Timing on Piston Engine for Lightweight Aircraft." Applied Mechanics and Materials 225 (November 2012): 245–49. http://dx.doi.org/10.4028/www.scientific.net/amm.225.245.

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As the Lycoming engine had failed its attempt on using variable valve timing for aircraft piston engine back in 1940s, the idea of the technology was abandoned as the turbines were then introduced in the aviation for better performance and greater power. Since piston engines produce smaller power efficiently in the low speed than turbine engines, they are presently still practically used in most of lightweight aircraft. With the use of a variable valve timing mechanism, it may help to increase the amount of air inlet and to provide more power output with lesser fuel consumption. With the use of this new valve system, improvements in the performance of automobile engines have been recorded. The indicated improvements, however, are limited to automobile engines running with high revolutions only. Engine simulation program was run in this investigation as an attempt to predict engine performances that are appropriate for lightweight aircraft.
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Tovkach, Serhii. "CUDA-інтеграція контурів керування авіаційного газотурбінного двигуна." Aerospace Technic and Technology, no. 6 (November 27, 2023): 31–39. http://dx.doi.org/10.32620/aktt.2022.6.04.

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The problem of accelerating the process of designing aircraft gas turbine engines and their control systems, the system "AIRCRAFT-AVIATION ENGINE-FUEL", and forming the technical type of an aircraft engine, adapting to new operating conditions within the framework of experimental design bureaus (EDB) and the industry is using automated systems with low computing performance and incomplete description. Information technologies for developing engines allow duplication and mismatch of data, loss of information and time during transmission and processing for making parametric and structural decisions. To better adaptation of the characteristics of an aviation engine (AE) to the tasks solved by an aircraft in flight, it is necessary to integrate control systems. Integrated control systems are especially effective for managing today's multi-mode aircraft. On the basis of their control, optimal control programs for the power plant (PP) are formed using the criteria for evaluating the effectiveness of the aircraft. This article proposes a paradigm for building integrated control loops for an aircraft gas turbine engine, which can be formed by automating control processes, an automatic control system, and combined control programs. The objective of this research is the processes of constructing adaptive control loops for aircraft gas turbine engines. The subject of this study is the adaptive control of aircraft gas turbine engines using embedded control loops and CUDA architecture. The goal is to improve the dynamic characteristics of an aircraft gas turbine engine through adaptive control using control loops, considering various aircraft flight modes and engine operating modes. Objectives: to determine the main controllable elements of an aircraft engine, adjustable parameters and factors for constructing control loops according to the principle of adaptation; describe the mechanism of joint management of gas turbine engines; to study the processes of building an integration circuit "aircraft - power plant" and develop the concept of an integrated ACS; define the CUDA paradigm for parallel computing of control loops. Conclusions. The scientific novelty lies in the formation of a paradigm for developing adaptive control models for gas turbine engines, considering different aircraft flight modes and engine operation modes.
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Улитенко, Юрий Александрович. "АНАЛИЗ ХАРАКТЕРИСТИК ТУРБОРЕАКТИВНОГО ДВУХКОНТУРНОГО ДВИГАТЕЛЯ С ФОРСАЖНОЙ КАМЕРОЙ СГОРАНИЯ С ВПРЫСКОМ ВОДЫ ЗА ВХОДНЫМ УСТРОЙСТВОМ." Aerospace technic and technology, no. 1 (March 7, 2019): 29–38. http://dx.doi.org/10.32620/aktt.2019.1.03.

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Development of perspective high-speed aircraft inseparably depends on the level of aircraft propulsion engineering as engine performances to determine aircraft capabilities as a whole. The basic requirements to engines of high-speed aircraft are increase speed and flight height. The new generation of turbojet bypass engine with afterburner each their specific thrust and a specific impulse increases, also the application of high technologies raises leads to substantial growth of the engine cost too. At the same time, existing engines design has big reserves for modernization. The system of water injection to the input at the turbojet bypass engine with afterburner is one of the accessible ways for design improvement. Those advanced engines theoretically will allow to satisfy requirements from designers of high-speed aircraft concerning to thrust and other key parameters, at the same time to secure continuity of already existing types of power-plants. The possibility of range extension of turbojet bypass engine with classical scheme afterburner operation till Mach number 3 is considered in this article. The analysis of existing developments is carried out. Impact of water injection to the input at turbojet bypass engine with afterburner on its performance is investigated. Results of calculations for the influence of water injection to reaction mass parameters on the engine duct and its thrust characteristics are proved. Received results will allow to increase thermodynamic efficiency and to expand range extension of turbojet bypass engine with afterburner provided to use materials that applied in aviation manufacture, as well as to reduce terms of development competitive engines for high-speed aircraft at the expense of purposeful search of their rational thermodynamic and is constructive-geometrical architecture.
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Wang, Hao Xiang, and Hong Sen Yan. "An Adaptive Assembly Scheduling Approach in Knowledgeable Manufacturing." Applied Mechanics and Materials 433-435 (October 2013): 2347–50. http://dx.doi.org/10.4028/www.scientific.net/amm.433-435.2347.

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To address the uncertainty of production environment in aircraft engine assembly, an adaptive optimization scheduling algorithm is designed for an aircraft engine assembly line in knowledgeable manufacturing. A Q-learning adaptive scheduling model of aircraft engine assembly is built on the objective function of minimizing earliness penalty. Simulation experiments indicate that the proposed algorithm outperforms other scheduling rules much. Especially, better results are generally achieved with the increase in number of engines to show good adaptive performance.
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Grabowski, Łukasz, Konrad Pietrykowski, and Paweł Karpiński. "Energetic Analysis of the Aircraft Diesel Engine." MATEC Web of Conferences 252 (2019): 05012. http://dx.doi.org/10.1051/matecconf/201925205012.

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The analysis of the distribution of thermal energy generated during the combustion process in internal combustion engines and the estimation of individual losses are important regarding performance and efficiency. The article analyses the energy balance of the designed two-stroke opposed piston diesel engines with offset, i.e. the angle by which the crankshaft at the side of exhaust ports is ahead of the crankshaft at the side of intake ports. Based on the developed zero-dimensional engine model, a series of simulations were performed in steady-state conditions using the AVL BOOST software. The values of individual energy losses, including cooling losses, exhaust gas losses, friction losses were obtained. The influence of decreasing and increasing the offset on the performance of the tested engine was analysed.
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Azami, Muhammad Hanafi, and Mark Savill. "Comparative study of alternative biofuels on aircraft engine performance." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 8 (June 22, 2016): 1509–21. http://dx.doi.org/10.1177/0954410016654506.

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Aviation industries are vulnerable to the energy crisis and simultaneously posed environmental concerns. Proposed engine technology advancements could reduce the environmental impact and energy consumption. Substituting the source of jet fuel from fossil-based fuel to biomass-based fuel will help reduce emissions and minimize the energy crisis. The present paper addresses the analysis of aircraft engine performance in terms of thrust, fuel flow and specific fuel consumption at different mixing ratio percentages (20%, 40%, 50%, 60% and 80%) of alternative biofuel blends already used in flight test (Algae biofuel, Camelina biofuel and Jatropha biofuel) at different flight conditions. In-house computer software codes, PYTHIA and TURBOMATCH, were used for the analysis and modeling of a three-shaft high-bypass-ratio engine which is similar to RB211-524. The engine model was verified and validated with open literature found in the test program of bio-synthetic paraffinic kerosene in commercial aircraft. The results indicated that lower heating value had a significant influence on thrust, fuel flow and specific fuel consumption at every flight condition and at all mixing ratio percentages. Wide lower heating value differences between two fuels give a large variation on the engine performances. Blended Kerosene–Jatropha biofuel and Kerosene–Camelina biofuel showed an improvement on gross thrust, net thrust, reduction of fuel flow and specific fuel consumption at every mixing ratio percentage and at different flight conditions. Moreover, the pure alternative of Jatropha biofuel and Camelina biofuel gave much better engine performances. This was not the case for the Kerosene–Algae blended biofuel. This study is a crucial step in understanding the influence of different blended alternative biofuels on the performance of aircraft engines.
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Dissertations / Theses on the topic "Aircraft engine performance"

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Miao, Zhisong. "Aircraft engine performance and integration in a flying wing aircraft conceptual design." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7249.

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The increasing demand of more economical and environmentally friendly aero engines leads to the proposal of a new concept – geared turbofan. In this thesis, the characteristics of this kind of engine and relevant considerations of integration on a flying wing aircraft were studied. The studies can be divided into four levels: GTF-11 engine modelling and performance simulation; aircraft performance calculation; nacelle design and aerodynamic performance evaluation; preliminary engine installation. Firstly, a geared concept engine model was constructed using TURBOMATCH software. Based on parametric analysis and SFC target, the main cycle parameters were selected. Then, the maximum take-off thrust was verified and corrected from 195.56kN to 212kN to meet the requirements of take-off field length and second segment climb. Besides, the engine performance at offdesign points was simulated for aircraft performance calculation. Secondly, an aircraft performance model was developed and the performance of FW-11 was calculated on the basis of GTF-11 simulation results. Then, the effect of GTF-11 characteristics performance on aircraft performance was evaluated. A comparison between GTF-11 and conventional turbofan, RB211- 524B4, indicated that the aircraft can achieve a 13.1% improvement in fuel efficiency by using the new concept engine. Thirdly, a nacelle was designed for GTF-11 based on NACA 1-series and empirical methods while the nacelle dimensions of conventional turbofan RB211-525B4 were obtained by measure approach. Then, the installation thrust losses caused by nacelle drags of the two engines were evaluated using ESDU 81024a. The results showed that the nacelle drags account for about 4.08% and 3.09% of net thrust for GTF-11 and RB211-525B4, respectively. Finally, the considerations of engine installation on a flying wing aircraft were discussed and a preliminary disposition of GTF-11 on FW-11 was presented.
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Navaratne, Rukshan. "Investigation of impact of engine degradation on optimum aircraft trajectories." Thesis, Cranfield University, 2016. http://dspace.lib.cranfield.ac.uk/handle/1826/12296.

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The continuous growth in flight operations has led to public concern regarding the impact of aviation on the environment with its anthropogenic contribution to global warming. Several solutions have been proposed in order to reduce the environmental impact of aviation. However most of them are long term solutions such as new environmental friendly aircraft and engine designs. In this respect, management of aircraft trajectory and mission is a potential short term solution that can readily be implemented. Therefore, in order to truly understand the optimised environment friendly trajectories that can be actually deployed by airlines, it is important to investigate the impact of degraded engine performance on real aircraft trajectories at multi-disciplinary level. Several trajectory optimisation studies have been conducted in this direction in the recent past, but engines considered for the studies were clean and trajectories were ideal and simple. This research aims to provide a methodology to enhance the conventional approach of the aircraft trajectory optimisation problem by including engine degradation and real aircraft flight paths within the optimisation loop (framework); thereby the impact of engine degradation on optimum aircraft trajectories were assessed by quantifying the difference in fuel burn and emissions, when flying a trajectory which has been specifically optimised for an aircraft with degraded engines and flying a trajectory which has been optimised for clean engines. For the purpose of this study models of a clean and two levels of degraded engines have been developed that are similar to engines used in short range and long range aircraft currently in service. Degradation levels have been assumed based on the deterioration levels of Exhaust Gas Temperature (EGT) margin. Aircraft performance models have been developed for short range and long range aircraft with the capability of simulating (generating) vertical and horizontal flight profiles provides by the airlines. An emission prediction model was developed to assess NOx emissions of the mission. The contrail prediction model was adopted from previous studies to predict contrail formation. In addition, a multidisciplinary aircraft trajectory optimisation framework was developed and employed to analyse short range flight trajectories between London and Amsterdam and long range flight trajectories between London and Colombo under three cases. Case_1: Aircraft with clean engines, Case_2 and Case_3 were Aircraft with two different levels of degraded engines having a 5% and 10% Exhaust Gas Temperature (EGT) increase respectively. Three different multi objective optimisation studies were performed; (1) Fuel burn vs Flight time, (2) Fuel burn vs NOx emission, and (3) Fuel burn vs Contrails. Finally optimised trajectories generated with degraded engines were compared with the optimised trajectories generated with clean engines ... [cont].
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Yarlagadda, Santosh. "Performance Analysis of J85 Turbojet Engine Matching Thrust with Reduced Inlet Pressure to the Compressor." University of Toledo / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1271367584.

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Tow, Kevin Robert. "Aircraft engine performance improvements using multistage compressors with actively controlled stall lines." Thesis, Massachusetts Institute of Technology, 1994. http://hdl.handle.net/1721.1/36437.

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Toufexis, Dimitrios. "Aircraft maintenance and development of a performance-based creep life estimation for aero engine." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7750.

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For any machine designed to generate power, or to fulfill its functions in general, maintenance actions will have an impact on many aspects of its overall capabilities, especially its performance and the length of its useful life. Since these are vital in order to generate maximum profit, the maintenance actions that affect them must be given serious consideration. For this reason, this research aims to propose a method that will enhance the cost saving potential with more accurately determined maintenance intervals and greater exploitation of the remaining life of the components by utilizing the capabilities of condition based monitoring. Initially, the research focuses on the description and the understanding of maintenance methods as they are performed within the aviation industry, but it also aims to investigate the state of the art Condition Based Monitoring Maintenance (CBMM) and its associated advantaged relating to the older methods. The thesis begins by describing the fundamental aviation maintenance management domains, paying particular attention to CBMM, and continues with the diagnostic and prognostic methods that are in use in order to support the condition monitoring concept. Next, a description is given of the actual implementations of the CBMM process, with the presentation of the maintenance enhancement systems, namely the Central Maintenance System and the Aircraft Condition Monitoring System. Lastly, a case study is presented of the estimation of the remaining useful life of a turbine blade, as it relates to the primary failure mode of creep. The case study endorses the use of the condition monitoring diagnostic methods discussed previously and also aims to demonstrate the predictive capabilities of the Engine Usage Diagnostics at both the design and the into-service stage. The created/simulated engine performance models concern several operating conditions of the engine while the impact of each of those on the remaining useful life of the blade is investigated. The benefit of this research is that it proposes a practical, effective, and relatively easy way to perform maintenance by predicting the need according to the usage. Additionally, the data required have already been measured, which paves the way for the creation of more intelligent engine control units. The contribution and innovation of the research is demonstrated by the fact that no similar approaches to creep life prediction have been published for the same type of engine, namely the CFM56 5B2. Last but not least, the results are presented in the most beneficial form of remaining hours before the failure.
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Gu, Weiqun. "Evaluation of optimised flight trajectories for conventional and novel aircraft and engine integrated systems." Thesis, Cranfield University, 2013. http://dspace.lib.cranfield.ac.uk/handle/1826/10254.

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Today, the air transport industry has become an essential element of global society by its great contributions to the wide exchanges of cultures/people and to the rapid growth in the world economy. However, on the other hand, the adverse impacts on the environment caused by air transport, such as air pollution, noise and climate change, are drawing, increasingly, growing public concern. In order to address the steady growth in air-travel demand in the next decades through an environmentally-friendly way and realise the ACARE 2020 environmental goals, The Clean Sky programme has been launched by European Union over the period 2008 – 2013. The project research, described in this thesis and sponsored by the Clean Sky programme, aims at evaluating the feasibility of reducing the environmental impact of commercial aviation through the introduction of changes in the aircraft operational rules and procedures, as well as the application of the new-generation propfan (open rotor) engine, based on flight trajectory multidisciplinary optimisation and analysis of commercial aircraft. In order to accomplish the above research objectives, a complete methodology to achieve and realise optimum flight trajectories has been initially proposed. Then, 12 component-level models which function as simulating different disciplines, such as aircraft performance, engine performance, engine gaseous emission, and flight noise, have been developed or selected/adopted. Further, nine system-level integration and optimisation models were built. These system-level models simulate flights from Amsterdam Schiphol airport in the Netherlands to Munich airport in Germany flown by different types of aircraft through different flight phases with different optimisation objectives. Finally, detailed investigations into the flight trajectory optimisations were performed, extensive optimisation results were achieved and corresponding description, analysis and comparisons were provided. The main contributions of this work to knowledge broadly comprise the following: 1) the further development regarding the methodology of flight trajectory multidisciplinary optimisation; 2) previous work on aircraft trajectory optimisation has often considered fixed objectives over the complete flight trajectory. This research focused on representative flight phases of a flight mission with different optimisation objectives, namely, noise impact and fuel burn during the departure phase; fuel burn and flight time during en route phase; and noise impact and NOx emission during the arrival phase; 3) this research has extended the current flight trajectory optimisations to turboprop and propfan equipped aircraft. As a result, a relative complete 2D flight trajectory multidisciplinary optimisation spectrum, spanned by primary commercial aircraft types, primary flight phases and primary optimisation objectives of interest, has been built. Although encouraging progress have been achieved, this project research, as with any other research activity, is also only ‘on the way’ rather than coming to the ‘end’ point. There are still many aspects which can be improved further and there is still much new research and exploration which can be investigated further. All these have also been suggested in this thesis.
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Materano, Blanco Gilberto Ignacio. "Numerical modelling of pressure rise combustion for reducing emissions of future civil aircraft." Thesis, Cranfield University, 2014. http://dspace.lib.cranfield.ac.uk/handle/1826/9259.

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This work assesses the feasibility of designing and implementing the wave rotor (WR), the pulse detonation engine (PDE) and the internal combustion wave rotor (ICWR) as part of novel Brayton cycles able to reduce emissions of future aircraft. The design and evaluation processes are performed using the simplified analytical solution of the devices as well as 1D-CFD models. A code based on the finite volume method is built to predict the position and dimensions of the slots for the WR and ICWR. The mass and momentum equations are coupled through a modified SIMPLE algorithm to model compressible flow. The code includes a novel tracking technique to ensure the global mass balance. A code based on the method of characteristics is built to predict the profiles of temperature, pressure and velocity at the discharge of the PDE and the effect of the PDEs array when it operates as combustion chamber of gas turbines. The detonation is modelled by using the NASA-CEA code as a subroutine whilst the method of characteristics incorporates a model to capture the throttling and non-throttling conditions obtained at the PDE's open end during the transient process. A medium-sized engine for business jets is selected to perform the evaluation that includes parameters such as specific thrust, specific fuel consumption and efficiency of energy conversion. The ICWR offers the best performance followed by the PDE; both options operate with a low specific fuel consumption and higher specific thrust. The detonation in an ICWR does not require an external source of energy, but the PDE array designed is simple. The WR produced an increase in the turbine performance, but not as high as the other two devices. These results enable the statement that a pressure rise combustion process behaves better than pressure exchangers for this size of gas turbine. Further attention must be given to the NOx emission, since the detonation process is able to cause temperatures above 2000 K while dilution air could be an important source of oxygen.
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Woods, Nathan Michael. "Taking Off in Africa: Critical Elements of Aircraft Engine Manufacturer Engagement That Can Affect Airline Safety Performance." Antioch University / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=antioch1578644754400526.

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Kline, Sara E. "An Investigation of the Performance of Compliant Finger Seals for use in Gas Turbine Engines using Navier-Stokes and Reynolds Equation Based Numerical Models and Experimental Evaluation." University of Akron / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=akron1478984223281402.

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Hrabovský, Matúš. "Posouzení letových vlastností a zatížení malého sportovního letounu po modifikaci pohonné jednotky." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2020. http://www.nusl.cz/ntk/nusl-417471.

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The thesis deals with the issue of replacement of the Rotax 912 ULS engine with the Rotax 915 iSc3 B engine and its impact on flight performance, characteristics and airframe loads of the WT 9 Dynamic. For accomplish better maneuverability tail surfaces are enlarged. Both versions of airplane with different engines and tails surfaces are quantified with respect to airframe loads and flight characteristics. The output of the diploma thesis can be used for strength design of airplane structure and stress tests of the new modification of the WT 9 Dynamic aircraft.
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Books on the topic "Aircraft engine performance"

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Comparative engine performance measurements (Mesures comparatives des performances des moteurs). Neuilly-sur-Seine, France: AGARD, 1990.

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Franciscus, Leo C. Supersonic through-flow fan engine and aircraft mission performance. [Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1989.

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Simon, Donald L. Adaptive optimization of aircraft engine performance using neural networks. [Washington, D.C.]: National Aeronautics and Space Administration, 1995.

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Kobayashi, Takahisa. A hybrid neural network-genetic algorithm technique for aircraft engine performance diagnostics. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2001.

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Kobayashi, Takahisa. A hybrid neural network-genetic algorithm technique for aircraft engine performance diagnostics. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2001.

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Kobayashi, Takahisa. A hybrid neural network-genetic algorithm technique for aircraft engine performance diagnostics. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2001.

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Kobayashi, Takahisa. A hybrid neural network-genetic algorithm technique for aircraft engine performance diagnostics. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2001.

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Neal, Bradford. The implementation and operation of a variable-response electronic throttle control system for a TF-104G aircraft. Edwards, Calif: National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, 1989.

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Burkardt, Leo A. General aviation light aircraft propulsion: From the 1940's to the next century. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1998.

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Maine, Trindel A. A preliminary evaluation of an F100 engine parameter estimation process using flight data. Moffett Field, Calif: Ames Research Center, 1990.

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Book chapters on the topic "Aircraft engine performance"

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Sadraey, Mohammad H. "Engine performance." In Aircraft Performance, 109–76. Boca Raton : CRC Press, [2016]: CRC Press, 2017. http://dx.doi.org/10.1201/9781315366913-4.

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Zhang, Hang, Ying Wang, Liping Pang, and Zhe Xu. "Research on the Fin Performance of Air-Oil Heat Exchanger for Aircraft Engine." In Lecture Notes in Electrical Engineering, 419–26. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-5963-8_59.

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Wang, Lifeng, and Datian Zhong. "Regularization Method Combined with Parameter Competitive Criterion for Model-Plant Performance Matching of Aircraft Engine." In Communications in Computer and Information Science, 657–64. Berlin, Heidelberg: Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-27503-6_90.

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El-Sayed, Ahmed F. "Performance Parameters of Jet Engines." In Fundamentals of Aircraft and Rocket Propulsion, 161–218. London: Springer London, 2016. http://dx.doi.org/10.1007/978-1-4471-6796-9_3.

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Montomoli, Francesco, Mauro Carnevale, Antonio D’Ammaro, Michela Massini, and Simone Salvadori. "Manufacturing and in Service Uncertainty and Impact on Life and Performance." In Uncertainty Quantification in Computational Fluid Dynamics and Aircraft Engines, 1–19. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-14681-2_1.

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Massini, M., and Francesco Montomoli. "Manufacturing/In-Service Uncertainty and Impact on Life and Performance of Gas Turbines/Aircraft Engines." In Uncertainty Quantification in Computational Fluid Dynamics and Aircraft Engines, 1–32. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-92943-9_1.

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"Engine Selection: Engine Performance Analysis." In Aircraft Engine Design, Third Edition, 163–220. Reston, VA: American Institute of Aeronautics and Astronautics, Inc., 2018. http://dx.doi.org/10.2514/5.9781624105173.0163.0220.

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"Engine/Airframe Performance Matching." In Aircraft Propulsion Systems Technology and Design, 167–237. Washington DC: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/5.9781600861499.0167.0237.

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"Engine Selection: Performance Cycle Analysis." In Aircraft Engine Design, Second Edition, 139–88. Reston ,VA: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/5.9781600861444.0139.0188.

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"Sizing the Engine: Installed Performance." In Aircraft Engine Design, Second Edition, 189–230. Reston ,VA: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/5.9781600861444.0189.0230.

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Conference papers on the topic "Aircraft engine performance"

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Zein-Sabatto, Saleh, Alireza Behbahani, Richard Hans Mgaya, and Mohammad Bodruzzaman. "Turbine Engine Reconfigurable Control Systems for Aircraft Propulsion Performance Improvement." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-94910.

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Artificial intelligent technologies are being investigated for development of advanced adaptation and reconfiguration algorithms for turbine engine distributed control systems. Adding adaptation and reconfiguration feature to the control systems is expected to improve engine performance and provide more efficient aircraft operations. The benefits of transitioning from the existing centralized supervisory control, the Full Authority Digital Electronic Control (FADEC), of turbine engines to distributed control architecture have been well articulated in the literature. The major benefits are summarized as; weight reduction, cost saving, and damage tolerant turbine engines. However, consideration of advanced intelligent technologies in the design and operation of distributed control systems has been a challenging task and requires further investigation. This paper describes research activities to address the above stated challenge leading to fully reconfigurable distributed control systems for turbine engines of the future aircrafts. The goal of the research work is to accelerate the development and implementation of disturbed control systems in aircrafts propulsion controls and its integration with distributed diagnostics and prognostics algorithms. This will be achieved by means of using artificial intelligent technologies to design adaptation and reconfiguration algorithms and integrate it with a set of engine decentralized controllers. Fuzzy inference concept will be used to develop and implement the proposed adaptation and reconfiguration algorithms. Finally, the integrated reconfiguration algorithms with the control system will be tested and verified on publicly available turbine engine simulation software.
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Zhao, Bin, Shaobin Li, Qiushi Li, and Sheng Zhou. "Impact of Air System Bleeding on Aircraft Engine Performance." In ASME-JSME-KSME 2011 Joint Fluids Engineering Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/ajk2011-22004.

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Air system bleeding is indispensable to aircraft engines despite its negative impact on the engine thrust and the fuel consumption. However, the compressor performance can be improved if the bleeding design is optimized. The model in this paper is a one-dimensional engine model based on air system bleeding. The relation between the compressor performance and the engine thermodynamic cycle caused by bleeding is analyzed to explore the potential of air system bleeding in improving compressor and engine performance. The results show that if bleeding brings an increase the pressure ratio of compressor, the negative impact on engine specific fuel consumption can be inhibited. If the efficiency of compressor is increased after bleeding, the negative impact on engine thrust can be alleviated. With proper bleeding flow rates, if both the pressure ratio and the efficiency increase at the same time, the negative impact on the engine performance can be eliminated.
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Menon, P., Gregory Sweriduk, S. Vaddi, and Khary Parker. "Nonlinear Control of a High-Performance Aircraft Engine." In AIAA Guidance, Navigation, and Control Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-6087.

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FRANZ, JOSEPH. "Performance estimation of an aircraft internal combustion engine." In 23rd Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2173.

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Tong, Michael T. "A Machine-Learning Approach to Assess Aircraft Engine System Performance." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-14661.

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Abstract Machine learning and big data have become the most disruptive technologies for organizations to improve workplace efficiency and productivity. This work explored the application of machine learning-based predictive analytics that would enable aircraft engine designers to estimate engine system performance quickly during the conceptual design stage. Supervised machine-learning algorithm was employed to study patterns in an open-source database of one-hundred-eighty-three production and research turbofan engines, and built predictive analytics for use in predicting system performance of new turbofan designs. Specifically, the author developed deep-learning analytics to predict turbofan system weight, using turbofan design parameters as the input. The predictive analytics were trained and deployed in Keras, an open-source neural networks API (application program interface) written in Python, with TensorFlow (an open-source Google machine learning library) serving as the backend engine. The current engine-weight prediction results, together with those for the TSFC (thrust specific fuel consumption) and core-size predictions that were studied previously by the author, show that machine learning-based predictive analytics can be an effective, time-saving tool for assessing aircraft engine system performance (TSFC, weight, and core size) during the conceptual design stage. It would enable expeditious identification of the best engine design amongst several candidates.
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Cosner, Andrew A., and Glyn S. Rutledge. "Successful Performance Development Program for the T800-LHT-800 Turboshaft Engine." In General Aviation Aircraft Meeting and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1989. http://dx.doi.org/10.4271/891048.

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Herzog, James P., Jason Hanlin, Stephan W. Wegerich, and Alan D. Wilks. "High Performance Condition Monitoring of Aircraft Engines." In ASME Turbo Expo 2005: Power for Land, Sea, and Air. ASMEDC, 2005. http://dx.doi.org/10.1115/gt2005-68485.

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A similarity-based modeling (SBM) technique is demonstrated that provides very early annunciation of the onset of gas path faults in aircraft engines. This powerful approach is shown to provide high fidelity estimates for real-time condition monitoring of aircraft engine signals. These estimates are used to detect the onset of changes in the inter-relationship between the various signals using a sophisticated set of built-in algorithms and tools. The ability of the SBM software to reliably detect subtle changes in signal behavior that are characteristic of a developing anomaly is coupled with a diagnostic rules engine to enable a rapid and robust fault recognition capability. The SBM software operates using a set of algorithms that construct a multivariate nonparametric model of the traditional monitoring sensors (pressure transducers, thermocouples, flow meters, etc.) present in the system. This model is used to generate real-time estimates of sensor values that represent normal system operation. A series of sophisticated tools compares these very high fidelity estimates to the actual sensor readings to detect discrepancies. Finally, a series of logic rules derived from a combination of engineering analysis and experience is applied to the output from the modeling engine in real-time to alert the user of developing serious conditions that need either immediate or planned maintenance attention. The software system provides a complete approach to asset monitoring that minimizes down time, maximizes availability, encodes (preserves) operator knowledge and lowers the overall costs associated with maintaining the assets. In this paper, we demonstrate the use of the similarity-based modeling approach for detecting faults in the gas path of aircraft engines. Some results from the monitoring of over 1,100 engines at a major commercial airline over a two-year period are described. Operationally, the early detection of developing engine faults has prevented delays and cancellations, and has contributed to a reduction in the airline’s in-flight shutdown rate. Financially, this approach has led to significant cost savings by the prevention of major secondary damage.
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Cue, R. W., and D. E. Muir. "Engine Performance Monitoring and Troubleshooting Techniques for the CF-18 Aircraft." In ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1990. http://dx.doi.org/10.1115/90-gt-357.

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The F404-GE-400 engines of the CF-18 aircraft are the first engines of the Canadian Forces to be maintained under a formal on-condition maintenance program. In support of this program, the Canadian Forces are developing advanced troubleshooting and performance monitoring procedures based on information recorded by the aircraft In-flight Engine Condition Monitoring System (IECMS). A suite of computer programs has been developed which enables maintenance personnel to access, display and analyze in-flight event data recorded by the IECMS and to track the performance of individual engines based on “health indices” derived from the IECMS takeoff ground roll recordings. The new techniques have been under evaluation at each of the CF-18 main operating bases for a period of approximately 14 months. Results to-date indicate that the IECMS recordings provide a considerable amount of information of benefit to engine technicians and maintenance planners.
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Kestner, Brian, Taewoo Nam, Andrew Flett, J. Wilson, and Dimitri Mavris. "Integrated Engine and Aircraft Mission Performance Analysis Using NPSS." In 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-841.

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Schmidt, Marvin F., Christopher M. Norden, and Jeffrey M. Stricker. "Ideal Power Output — An Alternative Aircraft Engine Performance Comparator." In ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-gt-228.

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The gas turbine is applied in four basic configurations; the turbojet, the turbofan, the turboprop and the turboshaft. Comparisons of the performance of these various configurations is difficult since they convert the energy to different forms, i.e. thrust or shaft power. Cycle variables which do not necessarily constitute advancements in the state-of-the-art such as bypass ratio and fan pressure ratio can have a profound effect on thrust and shaft power. Differences in flight speed and altitude capability further confound the comparisons. What is required is a comparison methodology that removes all of these variables and yet puts all the various types of engines on an equitable basis. This paper will provide such a comparison tool. All turbomachinery, regardless of configuration, can be compared with this method.
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Reports on the topic "Aircraft engine performance"

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Gann, Richard G., and Richard G. Gann. Fire suppression system performance of alternative agents in aircraft engine and dry bay laboratory simulations. Gaithersburg, MD: National Institute of Standards and Technology, 1995. http://dx.doi.org/10.6028/nist.sp.890v1.

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Gann, Richard G., and Richard G. Gann. Fire suppression system performance of alternative agents in aircraft engine and dry bay laboratory simulations. Gaithersburg, MD: National Institute of Standards and Technology, 1995. http://dx.doi.org/10.6028/nist.sp.890v2.

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Robinson, W. Evaluation of thin flexible pavements under simulated aircraft traffic. Engineer Research and Development Center (U.S.), December 2020. http://dx.doi.org/10.21079/11681/39161.

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A full-scale airfield pavement test section was constructed and trafficked by the U.S. Army Engineer Research and Development Center (ERDC) to evaluate the performance of relatively thin airfield pavement structures. The test section consisted of 16 test items that included three asphalt pavement thicknesses and two different aggregate base courses. The test items were subjected to simulated aircraft traffic to evaluate their response and performance to realistic aircraft loads and to evaluate the effect of reductions in tire pressure on thin asphalt pavement. Rutting behavior, pavement cracking, instrumentation response, and falling weight deflectometer response were monitored at selected traffic intervals. The results of this study were used to extend existing Department of Defense pavement design and evaluation techniques to include the evaluation of airfield pavement sections that do not meet the current criteria for aggregate base quality and minimum asphalt concrete surface thickness. These performance data were used to develop new aggregate base failure design curves using existing stress-based design methodology.
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Edwards, Lulu, Haley Bell, and Marcus Opperman. Alternatives for large crater repairs using Rapid Set Concrete Mix®. Engineer Research and Development Center (U.S.), June 2021. http://dx.doi.org/10.21079/11681/40969.

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Research was conducted at the U.S. Army Engineer Research and Development Center (ERDC) in Vicksburg, MS, to identify alternative repair methods and materials for large crater repairs using Rapid Set Concrete Mix®. This report presents the technical evaluation of the field performance of full-depth slab replacement methods conducted using Rapid Set Concrete Mix® over varying strength foundations. The performance of each large crater repair was determined by using a load cart representing one-half of the full gear of a C-17 aircraft. Results indicate that using rapid-setting concrete is a viable material for large crater repairs, and the performance is dependent on surface thickness and base strength.
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