Relevant bibliographies by topics / Aircraft engineering

Contents

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

Academic literature on the topic 'Aircraft engineering'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Aircraft engineering"

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Liang, Di, and Sheng Jing Tang. "The Design and Development of the Aerodynamic Engineering Prediction Software for Aircrafts." Applied Mechanics and Materials 543-547 (March 2014): 3136–40. http://dx.doi.org/10.4028/www.scientific.net/amm.543-547.3136.

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Aerodynamic analysis and calculation are very important parts in the aircraft design, and aerodynamic engineering prediction is widely used in the aircraft preliminary design stage. However, traditional aerodynamic engineering prediction causes heavy computation and is time-consuming. The developed software such as DATCOM has the disadvantages of complicated operation and black box structure. To overcome the disadvantages above, we develop the software for aerodynamic engineering prediction based on the aerodynamic characteristics and prediction for aircrafts. There are three parts in this software which are database, calculation module and user interface. The software is verified by a numerical example of one aircraft, and compares with the data of Computational Fluid Dynamics (CFD) and the wind tunnel test. The results show that the calculated results of the aerodynamic engineering prediction and CFD are basically consistent, and the software is able to meet the accuracy demand in the preliminary design phase of the aircraft.
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Olugbeji, Jemitola P., Okafor E. Gabriel, and Godwin Abbe. "Wing Thickness Optimization for Box Wing Aircraft." Recent Patents on Engineering 14, no. 2 (October 29, 2020): 242–49. http://dx.doi.org/10.2174/1872212113666190206123755.

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Background: In the interest of improving aircraft performance, studies have highlighted the benefits of Box wing configurations over conventional cantilever aircraft configuration. Generally, the greater an aircraft's average thickness to chord ratio (τ), the lower the structural weight as well as volumetric capacity for fuel. On the other hand, the lower the ., the greater the drag reduction. A review of patents related to the Box-wing aircraft was carried out. While methodologies for optimizing wing thickness of conventional aircrafts have been studied extensively, limited research work exist on the methodology for optimizing the wing thickness to chord ratio of the Box wing aircraft configurations. Methods: To address this gap, in this work, a two stage optimization methodology based on gradient search algorithm and regression analysis was implemented for the optimization of Box wing aircrafts wing thickness to chord ratio. The first stage involved optimizing the All Up Mass (AUM), Direct Operating Cost (DOC) and Zero Lift Drag Coefficients (CDO), with respect to the aft and fore sweep angle for some selected τ values. At the second stage, a suitability function (γ) was optimized with respect to the aft and fore sweep angle for some selected τ values. A comparative study was further carried out using the proposed methodology on similar size cantilever wing aircraft. Results: From the result, an optimal τ value was reached. Also the τ value for the cantilever aircraft found based on the proposed methodology was similar to the true τ value of the adopted aircraft, thereby validating the methodology. Conclusion: Based on the optimal τ value reached from this work, the Box wing aircraft are suitable for thin airfoils.
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Rogalski, Tomasz, and Boguslaw Dołęga. "THE METHOD OF EVALUATION OF THE AIRCRAFT CONTROL SYSTEM." Aviation 9, no. 2 (June 30, 2005): 29–34. http://dx.doi.org/10.3846/16487788.2005.9635901.

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The dynamical development of general aviation demands compilation of new aircraft control methods. Those methods allow people without special airborne qualifications to pilot these aircrafts. The main goals of such a control system are to reduce a pilot's load, to improve control precision, and to protect an aircraft against dangerous situations. There are many criterions applied to grading and describing an aircraft's flying characteristics and the handling qualities of general aviation airplanes equipped with classical mechanical control systems. But a modern, small, transport aircraft should be equipped with fly‐by‐wire control systems, and there are no clear, straight, rules rate and describe the handling qualities of small airplanes with fly‐by‐wire control systems. This paper presents a methodology created by the authors that classifies and compares the handling qualities of general aviation aircraft equipped with fly‐by‐wire control systems. It takes into consideration two parameters: pilot's effort during realization of ordered tasks and precision of his control.
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Sun, Ji Ku, Zong Jie Cao, De Jian Sun, and Yi Chen. "Characteristic of Corrosive Damages about Aircraft Structures in Service." Applied Mechanics and Materials 543-547 (March 2014): 316–19. http://dx.doi.org/10.4028/www.scientific.net/amm.543-547.316.

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In engineering practices, aircraft structures have been damaged due to the structural corrosion, the corrosive problem of aircrafts needs to call high attentions for researchers because aircraft structures are composed of metals and compound metals. In this paper, corrosion problems and structural reliability of aircraft structures are discussed. Corrosion morphology and mechanism of aircraft structures are analyzed based on metal corrosion theory. The characteristics of the various types of corrosions of aircraft structures have been enumerated. The effect of environments in corrosion process of aircraft structures is studied. The law of corrosion developed at aircraft structural parts or materials is summarized. This research contributes to improving professionals capacity of corrosion prevention and control. It also provides technical support for aircraft maintainers.
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Bendall, Keith C. "Metallic materials for aircraft engineering." Aircraft Engineering and Aerospace Technology 67, no. 5 (May 1995): 5–7. http://dx.doi.org/10.1108/eb037595.

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Jackson, Scott. "SYSTEMS ENGINEERING FOR COMMERCIAL AIRCRAFT." INCOSE International Symposium 7, no. 1 (August 1997): 36–43. http://dx.doi.org/10.1002/j.2334-5837.1997.tb02151.x.

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Wang, X., H. Yu, and D. Feng. "Pose estimation in runway end safety area using geometry structure features." Aeronautical Journal 120, no. 1226 (April 2016): 675–91. http://dx.doi.org/10.1017/aer.2016.16.

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ABSTRACTA novel image-based method is presented in this paper to estimate the poses of commercial aircrafts in a runway end safety area. Based on the fact that similar poses of an aircraft will have similar geometry structures, this method first extracts features to describe the structure of an aircraft's fuselage and aerofoil by RANdom Sample Consensus algorithm (RANSAC), and then uses the central moments to obtain the aircrafts’ pose information. Based on the proposed pose information, a two-step feature matching strategy is further designed to identify an aircraft's particular pose. In order to validate the accuracy of the pose estimation and the effectiveness of the proposed algorithm, we construct a pose database of two common aircrafts in Asia. The experiments show that the designed low-dimension features can accurately capture the aircraft's pose information and the proposed algorithm can achieve satisfied matching accuracy.
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Sobolev, L. B. "Economic aspects of military aircraft engineering." Economic Analysis: Theory and Practice 17, no. 4 (April 27, 2018): 600–613. http://dx.doi.org/10.24891/ea.17.4.600.

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Danil’chenko, V. P., and M. V. Skiba. "Minimization of aircraft engineering enterprise losses." Russian Aeronautics (Iz VUZ) 50, no. 2 (June 2007): 199–203. http://dx.doi.org/10.3103/s1068799807020146.

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Padfield, G. D. "Flight handling qualities." Aeronautical Journal 110, no. 1104 (February 2006): 73–84. http://dx.doi.org/10.1017/s0001924000001020.

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Abstract This paper describes the methodology and key results from the first three years of delivery of ‘Flight Handling Qualities’ (FHQ), a problem-based-learning core module for fourth year Master of Engineering (MEng) undergraduates in Aerospace Engineering and optional module for the Systems Engineering MSc Programme, at the University of Liverpool. The module aim is to equip students with the skills and knowledge required to tackle aircraft handling qualities (HQs) and related ‘whole aircraft’ problems. Students are presented with the theory of handling qualities engineering in a series of interactive lectures. The students work in teams of four or five and undertake a number of team-building exercises throughout the first semester. Teams are presented with the idea that the aircraft with its handling qualities is the focus for knowledge acquisition and skills development. Each team is given the task of assessing and quantifying the HQs of a particular aircraft in a particular role, and then developing fixes to any handling deficiencies they identify; the current aircraft include the Wright Flyer, Grob 115, Black Hawk, Bo-105 and XV-15. Teams write an interim report at the end of the first term and a final report at the end of the second term, showing how they have assessed the aircraft, developed solutions to the problems and made recommendations concerning the aircraft’s suitability in the defined role. The reports also address the technical feasibility and economic viability of the proposed upgrades. The teams present their work to mock ‘customers’ (group of staff, another student team, visiting Industrialists) with the objective of demonstrating that the aircraft is now fit for the role. Each individual student maintains a ‘personal learning journal’, in which they document the development of their understanding of handling qualities and, more general, transferable skills. The module is designed to enable students to engage in all elements of the conceive-design-implement-operate (CDIO) cycle.
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Dissertations / Theses on the topic "Aircraft engineering"

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Serrano, Ignacio. "Unmanned Aircraft System (UAS) vs. Manned Aircraft System (MAS): A Military Aircraft Study." Digital Commons at Loyola Marymount University and Loyola Law School, 2015. https://digitalcommons.lmu.edu/etd/430.

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Unmanned Aerial Vehicles (UAVs) are common place in the 21st century, whether they are small to medium sized remotely piloted vehicles (aka drones) or large advanced Unmanned Aerial Systems with a preprogrammed flight path. There is anticipation that these Unmanned Systems will, in the future assume the roles of their traditional manned aircraft counterparts. There is also the perception that these Unmanned Systems should be developed partly because they would be less expensive when compared to their manned aircraft. This integrative paper asserts that this perception is not reality with regards to developing a newly designed UAV to replace its manned counterpart, for the same mission. Through the examination of systems engineering principles between the unmanned RQ-4 Global Hawk and the manned U-2 Dragon Lady one will understand why this perception is not correct. Both aircraft perform the same mission of providing High Altitude Intelligence, Surveillance, and Reconnaissance (ISR). Through evaluation of requirements analysis both aircraft flowed down the requirements to all the various subsystems in a similar manner, creating similar subsystems for Imagery Intelligence (!MINT) and Signals Intelligence (SIGINT). However, the additional requirement for long endurance required that the Global Hawk systems engineers had additional requirements to flow down to the software, communications, data processing, and ground support subsystems in order to control an unmanned aircraft for greater than 24 hours. This one additional requirement had various derived requirements that needed to be verified, and validated during analysis, manufacturing, subsystem build and test, and final system integration. By using both System Integration Laboratories (SIL) and Flight Tests both systems requirements were verified and validated by the systems engineers. The Global Hawk since it was unmanned was required to perform more verification of subsystems and software as it was the first UAV to achieve flight airworthiness. The future of ISR missions requires that the aircraft become more adaptable to future technologies and situations. The U-2 has a modular configuration to change out to and from different subsystems depending on the mission. However, these subsystems were designed 20 to 30 years ago, and were not designed for lower level modularity or interoperability. The Global Hawk systems engineering team understood the future needs and the high level demand and data to be gathered and processed. The SE's developed modularity and interoperability requirements and flowed them down to the various subsystems. The Global Hawk system is more useful in highly contested areas of interest as there is no pilot; however resilient communications of the data and data link must be robust with anti-jamming capabilities to ensure the data is secure from cyber-attack. However,the U-2 is more survivable since it has a defense system, and can provide greater situational awareness. Taking all the general ISR requirements into consideration a trade study using a matrix was performed indicating that the Global Hawk is the most optimal solution to meeting both the current and future requirements for ISR missions. Even though the overall acquisition cost of the Global Hawk is equivalent to the U-2, systems engineering for Global Hawk had the responsibility to flow down requirements to all subsystems with consideration of the entire systems lifecycle. This is exemplified in that the Global Hawk is cost effective to fly in terms of cost per flight hour. Therefore, the Global Hawk can fulfill all the requirements of the given stakeholders with the lowest operational cost.
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Farhat, M. A. "Engineering a miniature remotely piloted helicopter." Thesis, University of Sussex, 1986. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.372718.

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Smith, Harry Redgrave. "Engineering models of aircraft propellers at incidence." Thesis, University of Glasgow, 2015. http://theses.gla.ac.uk/6799/.

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Aircraft propellers in any flight condition other than pure axial flight are subject to an incident flowfield that gives rise to time-varying forces. Means of modelling these time-dependent forces have been presented in the literature, to varying degrees of success but a review of the different models is missing, and there is a need for an instructive means of simulation using physically realistic but computationally light methodologies. This dissertation provides a comprehensive overview of the relevant work to date, in addition to providing a logical framework in which the problem of propeller blade cyclic load variation may be assessed. Through this framework, the importance of different aerodynamic features pertinent to this problem are compared, and a new solution methodology based on adaptations of existing models is presented. This research project was commissioned by Dowty Propellers (DP), who chose Glasgow University and the supervisors for their rotorcraft simulation experience. Prediction of the propeller induced flowfield is shown to be of importance for the calculation of blade cyclic loads. Momentum models are fit for purpose owing to relative computational simplicity - this dissertation suggests a new radially-weighted implementation of momentum theory that provides better correlation with wind tunnel data than existing models. Swept propeller blades are discussed and the inherent problems faced by a designer or performance engineer are highlighted. An Euler transform to resolve velocities and forces between disc and blade element axes is presented, along with the assertion that ‘simple’ sweep correction methods can be deleterious to propeller aerodynamic simulation if used naïvely. Fundamentally, representation of a swept propeller blade by a blade element model is described as wholly more problematic than a straight propeller blade owing to the displacement of blade elements with respect to the blade pitch change axis - and that flow information will always be lost with such a representation. Installation effects are simulated and installed load fluctuations are predicted to a reasonable degree of accuracy compared to what little data is available. Different means of resolving installation velocities to disc and, subsequently, blade element axes are compared, and it is shown that representing installation effects by an effective incidence angle as is ‘standard practice’ will most likely underpredict installed load fluctuation. In addition to a varying blade root bending load caused directly by load fluctuation on a propeller at an angle of incidence, the reacted net loads at a propeller hub may include a constant yawing moment and in-plane force. This in-plane force has been well documented in the literature, but the equations for its calculation may miss a component of force due to a tilting of the blade tangential force. New equations for this additional force term are presented that validate well to legacy experimental data.
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Andersson, Henric. "Aircraft Systems Modeling : Model Based Systems Engineering in Avionics Design and Aircraft Simulation." Licentiate thesis, Linköping University, Linköping University, Machine Design, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-17573.

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Aircraft developers like other development and manufacturing companies, are experiencing increasing complexity in their products and growing competition in the global market. One way to confront the challenges is to make the development process more efficient and to shorten time to market for new products/variants by using design and development methods based on models. Model Based Systems Engineering (MBSE) is introduced to, in a structured way, support engineers with aids and rules in order to engineer systems in a new way.

In this thesis, model based strategies for aircraft and avionics development are studied. A background to avionics architectures and in particular Integrated Modular Avionics is described. The integrating discipline Systems Engineering, MBSE and applicable standards are also described. A survey on available and emerging modeling techniques and tools, such as Hosted Simulation, is presented and Modeling Domains are defined in order to analyze the engineering environment with all its vital parts to support an MBSE approach.

Time and money may be saved by using modeling techniques that enable understanding of the engineering problem, state-of-the-art analysis and team communication, with preserved or increased quality and sense of control. Dynamic simulation is an activity increasingly used in aerospace, for several reasons; to prove the product concept, to validate stated requirements, and to verify the final implementation. Simulation is also used for end-user training, with specialized training simulators, but with the same underlying models. As models grow in complexity, and the set of simulation platforms is expanded, new needs for specification, model building and configuration support arise, which requires a modeling framework to be efficient.

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Pineda, Elvine Philip B. II. "Nature's engineering : a blueprint for efficient aircraft design." Thesis, Massachusetts Institute of Technology, 2011. http://hdl.handle.net/1721.1/68916.

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Thesis (S.B.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 2011.
Cataloged from PDF version of thesis.
Includes bibliographical references (p. 34).
The flight of birds inspired engineers like Leonard da Vinci and Wilbur and Orville Wright to design aircraft that mimic the behavior they observed. The success of the Wright brothers' first controllable aircraft ushered in an era of rapid advances in aviation technology leading to the airplanes of today. Despite these advances, airplanes possess many restrictions that prevent them from being as efficient as their nature-engineered counterparts. Researchers have thus returned to the methods of the earlier engineers in aviation and begun observing birds to look for ways to improve aircraft design. Two methods currently being researched to improve aircraft efficiency are morphing wings and perching. Morphing wings allow airplanes to change the shape of their wings to suit the needs of their mission. Perching is a landing maneuver that uses the nonlinear dynamics of stall to create the drag forces necessary to decelerate the aircraft. Experiments on these methods prove them viable for implementation in small scale aircraft such as remote-controlled planes and unmanned aerial vehicles. However, because of the complexities involved in both morphing wings and perching, further developments are necessary to achieve full implementation.
by Elvine Philip B. Pineda.
S.B.
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Thomas, Rohan J. "Prediction of aircraft fuselage vibration." Thesis, The University of North Dakota, 2015. http://pqdtopen.proquest.com/#viewpdf?dispub=1594387.

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Modern unmanned aerial vehicles (UAV) are made of lightweight structures, owing to the demand for longer ranges and heavier payloads. These lightweight aircraft are more susceptible to vibrations caused by atmospheric turbulence transmitted to the fuselage from the wings. These vibrations, which can cause damage to the payload or on board avionics present a serious problem, since air turbulence is expected to increase over the next few decades, due to climate change.

The objective of this thesis is to predict the vibration of an aircraft fuselage by establishing a relationship between wing and fuselage vibration. A combination of ANSYS® and MATLAB® modeling are used to simulate aircraft vibrations. First, the displacement of a lumped mass aircraft model to step and sinusoidal forces acting on the wings are compared to displacements calculated using modal superposition equations. Next, a state space representation of this system is found using system identification techniques, which uses wing displacement as input, and provides fuselage displacement as output. This state space model is compared to a derived state space model for validation. Finally, a three dimensional aircraft with distributed displacement sensors on its wings is modeled. A state space representation is established using the wing displacement output from the sensors as its input and the motion and rotation of the fuselage along the X, Y and Z axes as the output.

It is seen that the displacement results of the lumped mass system match with those calculated using modal superposition equations. The state space model can also accurately predict the fuselage vibration of the lumped mass system, when provided with wing displacement as input. More importantly, results have shown that the distributed vibration sensors on the three dimensional plane model are able to measure the wing displacements. Using the output from these distributed sensors, the motion and rotation of the fuselage about all three axes can be effectively predicted.

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GongZhang, Hanlin, and Eric Axtelius. "Aircraft Winglet Design." Thesis, KTH, Skolan för teknikvetenskap (SCI), 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-276586.

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Aerodynamic drag can be decreased with respect to a wing’s geometry, and wingtip devices, so called winglets, play a vital role in wing design. The focus has been laid on studying the lift and drag forces generated by merging various winglet designs with a constrained aircraft wing. By using computational fluid dynamic (CFD) simulations alongside wind tunnel testing of scaled down 3D-printed models, one can evaluate such forces and determine each respective winglet’s contribution to the total lift and drag forces of the wing. At last, the efficiency of the wing was furtherly determined by evaluating its lift-to-drag ratios with the obtained lift and drag forces. The result from this study showed that the overall efficiency of the wing varied depending on the winglet design, with some designs noticeable more efficient than others according to the CFD-simulations. The shark fin-alike winglet was overall the most efficient design, followed shortly by the famous blended design found in many mid-sized airliners. The worst performing designs were surprisingly the fenced and spiroid designs, which had efficiencies on par with the wing without winglet.
Det aerodynamiska luftmotståndet kan minskas genom justeringar i vingens geometri, och vingtipsenheter så kallade virveldämpare spelar en vital roll inom vingdesign och utveckling. Projektet hade fokuset på att undersöka de lyft -och motståndskrafterna som genererades av en förutbestämd vinge vid användandet av olika varianter av virveldämpare. Genom beräkningsströmningsdynamiska simuleringar (CFD) och vindtunneltester av nerskalade 3D-utskrivna modeller kan dessa krafter beräknas. Med hjälp av dessa kan respektive virveldämparens bidrag till de sammanlagda lyft -och motståndskrafterna på vingen vidare bestämmas. Genom att beräkna förhållandet mellan de erhållna lyft -och motståndskrafterna kan vingens glidtal sist bestämmas, som är ett dimensionslöst mått på vingens effektivitet. Resultatet från denna studie visade att vingens prestanda varierade efter på valet av virveldämpare, där vissa designer gav avsevärda förbättringar över andra enligt CFD-simuleringar. Den hajfensliknande varianten (så kallad sharklet på engelska) var den mest effektiva designen, tätt följt av den ordinära uppåtriktade typen (blended på engelska) som återfinns på många av dagens medelstora flygplan. De sämst presterande designerna var förvånande nog den triangel -och spiralformade (fenced och spiroid på engelska), vilka presterade på samma nivå som den virveldämparfria vingen.
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Jackson, David Wayne. "Robust aircraft subsystem conceptual architecting." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/50202.

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Aircraft subsystems are key components in modern aircraft, the impact and significance of which have been constantly increasing. Furthermore, the architecture selection of these subsystems has overall system-level effects. Despite the significant effects of architecture selections, existing methods for determining the architecture, especially early in design, are similar to the use of traditional point solutions. Currently, aircraft subsystems are rarely examined during the conceptual design phase, despite the fact that this phase has a significant influence on aircraft cost and performance. For this reason, there is a critical need to examine subsystem architecture trades and investigate the design space during the conceptual design of an aircraft. Traditionally, after the aircraft conceptual design phase, subsystems are developed in a process that begins with the point selection of the architecture, then continues with its development and analysis, and concludes in the detailed development of the subsystems. The choice of the point design of the architecture to be developed can be made using simplified models to explore the design space. This method known as conceptual architecting is explored in this dissertation. This dissertation also focuses on bringing actuation subsystem architecture trades into conceptual design because of the significant cost impact of this design phase and the interdependence of vehicle sizing with the subsystems impact on the aircraft. The extent of these interdependencies is examined and found to be significant. As a result, this coupling must be captured to enable better informed decision making. A methodology to examine the design space of aircraft subsystem architectures during the conceptual design of aircraft, while incorporating this coupling, is presented herein and applied specifically to actuation architectures.
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Copley-Woods, Djuna S. (Djuna Sunlight) 1977. "Aircraft interior acoustic noise control." Thesis, Massachusetts Institute of Technology, 1999. http://hdl.handle.net/1721.1/9330.

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Thesis (S.B.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 1999.
Includes bibliographical references (p. 45).
An experimental study was perfonned to determine which materials are best suited for internal aircraft noise reduction. An impedance tube with dimensions of a scaled aircraft was constructed and evaluated, and eleven materials were tested and compared based on their noise reduction properties, weight, and thickness. Polyvinylidene Fluoride was tested for use in active noise control for a large space.
by Djuna S. Copley-Woods.
S.B.
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Filarsky, Brian Michael. "Quaternion-Based Aircraft Attitude Estimation." Thesis, University of California, San Diego, 2016. http://pqdtopen.proquest.com/#viewpdf?dispub=10133153.

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Aircraft attitude estimation requires fusing several sensors in order to recover both high and low frequency information in an observable manner. This thesis explores the fusion of gyroscope integration, gravity vector estimation, and magnetic field vector estimation using a complementary filter and an extended Kalman filter (EKF), both of which use a unit quaternion to represent the attitude portion of the state.

First, a set of models, which contain bias, scale factor errors, alignment errors, and Gaussian white noise, is introduced to govern the available sensors. The gyroscope bias is modeled as a random walk. A calibration routine is then established to minimize scale factor and bias errors. After some definitions and derivations for quaternion algebra are established, the attitude solution is then estimated using the complementary filter. Then the EKF is introduced and used to estimate both the quaternion state and gyroscope bias.

The thesis is concluded with a Monte Carlo run to compare the complementary filter with the EKF. Due in large part to the estimation of gyroscope bias in the EKF, this filter is shown to give a significantly more accurate state estimate. The robustness is also evaluated, with both filters initialized with the incorrect initial quaternion and gyroscope bias estimate. The EKF is shown to converge relatively quickly, while the complementary filter does not reliably converge due to the lack of gyroscope bias estimation.

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Books on the topic "Aircraft engineering"

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Megson, T. H. G. Aircraft structures for engineering students. 2nd ed. London: Edward Arnold, 1990.

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Megson, T. H. G. Aircraft structures for engineering students. 2nd ed. New York: Halsted Press, 1990.

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Biancolini, Marco Evangelos, and Ubaldo Cella, eds. Flexible Engineering Toward Green Aircraft. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-36514-1.

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Jackson, Scott. Systems engineering for commercial aircraft. Aldershot, England: Ashgate, 1997.

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Aircraft structures for engineering students. 4th ed. Oxford: Butterworth-Heinemann, 2007.

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Aircraft structures for engineering students. 2nd ed. London: Arnold, 1990.

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Wagenmakers, Joop. Aircraft performance engineering: Guidelines from an aircraft performance engineer. New York: Prentice-Hall, 1991.

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Aircraft performance engineering: Guidelines from an aircraft performance engineer. New York: Prentice Hall, 1991.

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Aircraft systems. 2nd ed. New York: McGraw-Hill, 1999.

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1950-, Stojić R., ed. Modern aircraft flight control. Berlin: Springer-Verlag, 1988.

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Book chapters on the topic "Aircraft engineering"

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Michel, Ulf, Werner Dobrzynski, Wolf Splettstoesser, Jan Delfs, Ullrich Isermann, and Frank Obermeier. "Aircraft Noise." In Handbook of Engineering Acoustics, 489–537. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-540-69460-1_17.

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Kelly, Don W., Murray L. Scott, and Rodney S. Thomson. "Composite Aircraft Structures." In Modeling Complex Engineering Structures, 247–74. Reston, VA: American Society of Civil Engineers, 2007. http://dx.doi.org/10.1061/9780784408506.ch09.

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Davey, Samuel, Neil Gordon, Ian Holland, Mark Rutten, and Jason Williams. "Aircraft Cruise Dynamics." In SpringerBriefs in Electrical and Computer Engineering, 35–46. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-0379-0_6.

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Davey, Samuel, Neil Gordon, Ian Holland, Mark Rutten, and Jason Williams. "Aircraft Manoeuvre Dynamics." In SpringerBriefs in Electrical and Computer Engineering, 47–54. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-0379-0_7.

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Ginevsky, A. S., and A. I. Zhelannikov. "Aerodynamic Loads on Aircraft Encountering Vortex Wakes of Other Aircraft." In Foundations of Engineering Mechanics, 129–48. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-01760-5_8.

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Kanistras, Konstantinos, Kimon P. Valavanis, and Matthew J. Rutherford. "Aircraft Takeoff Performance." In Intelligent Systems, Control and Automation: Science and Engineering, 99–105. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-67852-8_10.

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Ganesh, T. S., M. C. Keerthi, Sabari Girish, S. Sreeja Kumar, and B. Mrunalini. "Control of Tailless Aircraft." In Lecture Notes in Mechanical Engineering, 523–32. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-15-9601-8_40.

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Curran, Richard, Xiaojia Zhao, and Wim J. C. Verhagen. "Concurrent Engineering and Integrated Aircraft Design." In Concurrent Engineering in the 21st Century, 571–605. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-13776-6_20.

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Winter, Carl-Jochen. "Hydrogen Technologies for Future Aircraft." In Lecture Notes in Engineering, 23–42. Berlin, Heidelberg: Springer Berlin Heidelberg, 1990. http://dx.doi.org/10.1007/978-3-642-51686-3_3.

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Schroijen, Marcel, Michel van Tooren, Mark Voskuijl, and Richard Curran. "Addressing Complexity in Sustainable Aircraft Design." In Advanced Concurrent Engineering, 311–18. London: Springer London, 2011. http://dx.doi.org/10.1007/978-0-85729-799-0_36.

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Conference papers on the topic "Aircraft engineering"

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Mehler, Leo. "Military Aircraft System Engineering." In SAE Aerospace Technology Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1986. http://dx.doi.org/10.4271/861690.

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RICCI, PETER, and JEFFREY HALE. "Cost-conscious concurrent engineering." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3152.

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FULTON, R. "Managing engineering design information." In Aircraft Design, Systems and Operations Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-4452.

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KNODLE, M. "Transitioning to a concurrent engineering environment." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3151.

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MOSARD, G. "Measuring implementation progress in concurrent engineering." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3154.

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ALRED, JOHN, and CAROL HOPF. "NASA/USRA advanced engineering design program." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2063.

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OREILLY, P. "Marinized Apache/An engineering challenge." In Aircraft Systems, Design and Technology Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-2676.

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TOMARCHIO, A. "Concurrent engineering - Electronic packaging methodology yields quality improvements." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3153.

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PALMER, D. "Influence of computer aids on engineering productivity." In Aircraft Design Systems and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-3099.

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CARPENTER, JOYCE, and DAVID SCOTT. "Supportability - A key element of systems engineering." In Aircraft Design, Systems and Operations Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-4472.

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Reports on the topic "Aircraft engineering"

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Frazey, John S., and Stephen Reynolds. Decontamination of Bioaerosols within Engineering Tolerances of Aircraft Materials. Fort Belvoir, VA: Defense Technical Information Center, September 2012. http://dx.doi.org/10.21236/ada568160.

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Fu, Xiangyang, Guangdao Gao, and Peng Yang. Aircraft Drawing-Die Design CAD Expert System Based on Engineering Graph,. Fort Belvoir, VA: Defense Technical Information Center, August 1995. http://dx.doi.org/10.21236/ada300179.

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Author, Not Given. Engineering drawing transfer test with Douglas Aircraft Company: MIL-D-28000 Class II (IGES). Office of Scientific and Technical Information (OSTI), May 1989. http://dx.doi.org/10.2172/6032847.

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Drown, Daron J., and Seth W. Graham. Core Logistics Capability Policy Applied to USAF Combat Aircraft Avionics Software: A Systems Engineering Analysis. Fort Belvoir, VA: Defense Technical Information Center, June 2010. http://dx.doi.org/10.21236/ada521260.

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Meeker, Brent. Engineering Investigation of Failures of Cable Used to Tow the TDU-32A Banner Target from T2C Aircraft. Fort Belvoir, VA: Defense Technical Information Center, December 2000. http://dx.doi.org/10.21236/ada389724.

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Arsenlis, Athanasios, and John Allison. Integrated Computational Materials Engineering (ICME) Tools for Optimizing Strength of Forged Al-Li Turbine Blades for Aircraft Engines Final Report CRADA No. TC02238.0. Office of Scientific and Technical Information (OSTI), September 2017. http://dx.doi.org/10.2172/1425447.

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Arsenlis, A., and J. Allison. Integrated Computational Materials Engineering (ICME) Tools for Optimizing Strength of Forged Al-Li Turbine Blades for Aircraft Engines Final Report CRADA No. TC02238.0. Office of Scientific and Technical Information (OSTI), March 2021. http://dx.doi.org/10.2172/1774219.

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Carruth, William D. Evaluation of In-Place Asphalt Recycling for Airfield Applications. Engineer Research and Development Center (U.S.), July 2021. http://dx.doi.org/10.21079/11681/41142.

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Abstract:
Over the last few decades, in-place recycling of asphalt pavements has seen increased use by the highway industry, primarily to take a dvantage of potential cost and logistical savings compared to conventional reconstruction. More recently, the U.S. Navy and Federal Aviation Administration have allowed recycling to be used on airfields with lighter traffic. This report contains a discussion of in-place recycling design considerations obtained from a literature review of its use in the highway industry. Observations developed from a review of airfield pavement projects that have utilized recycling is also included. A structural analysis was performed using the Pavement-Transportation Computer Assisted Structural Engineering (PCASE) tool to determine typical stiffness values that recycled layers must achieve to support various types of military aircraft traffic for different pavement structures. Overall, in-place recycling is recommended for consideration as a rehabilitati on technique for military airfield pavements, and further investigation is recommended before it is implemented it into design guidance.
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Brodie, Katherine, Brittany Bruder, Richard Slocum, and Nicholas Spore. Simultaneous mapping of coastal topography and bathymetry from a lightweight multicamera UAS. Engineer Research and Development Center (U.S.), August 2021. http://dx.doi.org/10.21079/11681/41440.

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A low-cost multicamera Unmanned Aircraft System (UAS) is used to simultaneously estimate open-coast topography and bathymetry from a single longitudinal coastal flight. The UAS combines nadir and oblique imagery to create a wide field of view (FOV), which enables collection of mobile, long dwell timeseries of the littoral zone suitable for structure-from motion (SfM), and wave speed inversion algorithms. Resultant digital surface models (DSMs) compare well with terrestrial topographic lidar and bathymetric survey data at Duck, NC, USA, with root-mean-square error (RMSE)/bias of 0.26/–0.05 and 0.34/–0.05 m, respectively. Bathymetric data from another flight at Virginia Beach, VA, USA, demonstrates successful comparison (RMSE/bias of 0.17/0.06 m) in a secondary environment. UAS-derived engineering data products, total volume profiles and shoreline position, were congruent with those calculated from traditional topo-bathymetric surveys at Duck. Capturing both topography and bathymetry within a single flight, the presented multicamera system is more efficient than data acquisition with a single camera UAS; this advantage grows for longer stretches of coastline (10 km). Efficiency increases further with an on-board Global Navigation Satellite System–Inertial Navigation System (GNSS-INS) to eliminate ground control point (GCP) placement. The Appendix reprocesses the Virginia Beach flight with the GNSS–INS input and no GCPs.
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