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Journal articles on the topic 'Aircraft conceptual design'

Author: Grafiati

Published: 4 June 2021

Last updated: 12 February 2022

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1

Kwiek, Agnieszka. "Conceptual design of an aircraft for Mars mission." Aircraft Engineering and Aerospace Technology 91, no. 6 (June 10, 2019): 886–92. http://dx.doi.org/10.1108/aeat-08-2018-0231.

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Purpose The purpose of this paper is to present the results of a conceptual design of Martian aircraft. This study focuses on the aerodynamic and longitudinal dynamic stability analysis. The main research questions are as follows: Does a tailless aircraft configuration can be used for Martian aircraft? How to the short period characteristic can be improved by side plates modification? Design/methodology/approach Because of a conceptual design stage of this Martian aircraft, aerodynamic characterises were computed by the Panukl package by using the potential flow model. The longitudinal dynamic stability was computed by MATLAB code, and the derivatives computed by the SDSA software were used as the input data. Different aircraft configurations have been studied, including different wing’s aerofoils and configurations of the side plate. Findings This paper presents results of aerodynamic characteristics computations and longitudinal dynamic stability analysis. This paper shows that tailless aircraft configuration has potential to be used as Martian aircraft. Moreover, the study of the impact of side plates’ configurations on the longitudinal dynamic stability is presented. This investigation reveals that the most effective method to improve the short period damping ratio is to change the height of the bottom plate. Practical implications The presented result might be useful in case of further design of the aircrafts for the Mars mission and designing the aircrafts in a tailless configuration. Social implications It is considered by the human expedition that Mars is the most probable planet to explore. This paper presents the conceptual study of aircraft which can be used to take the high-resolution pictures of the surface of Mars, which can be crucial to find the right place to establish a potential Martian base. Originality/value Most of aircrafts proposed for the Mars mission are designed in a configuration with a classic tail; this paper shows a preliminary calculation of the tailless Martian aircraft. Moreover, this paper shows the results of a dynamic stability analysis, where similar papers about aircrafts for the Mars mission do not show such outcomes, especially in the case of the tailless configuration. Moreover, this paper presents the results of the dynamic stability analysis of tailless aircraft with different configurations of the side plates.

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2

Fioriti, Marco. "Adaptable conceptual aircraft design model." Advances in aircraft and spacecraft science 1, no. 1 (January 31, 2014): 43–67. http://dx.doi.org/10.12989/aas.2014.1.1.043.

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3

Al-Ahmed, S., and J. P. Fielding. "Vulnerability prediction method for use in aircraft conceptual design." Aeronautical Journal 103, no. 1024 (June 1999): 309–15. http://dx.doi.org/10.1017/s0001924000064903.

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Abstract A methodology has been developed to integrate the vulnerability discipline into the conceptual/preliminary design process of combat aircraft. An interactive and programmable solid modelling Computer Aided Design (CAD) system is used to generate a CAD solid model of the aircraft’s critical components. The aircraft’s components’ sizes and shapes are pre-defined by a conceptual/preliminary design synthesis computer model. A systematic Child-Parent assembly process is used to model the aircraft vulnerability, by defining the criticality degree of each component in the aircraft assembly. Solid Modelling CAD techniques have been modified to develop techniques to perform the two main standard vulnerability assessments, namely the shotline and vulnerable area methods.

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4

Smith, H., D. Sziroczák, GE Abbe, and P. Okonkwo. "The GENUS aircraft conceptual design environment." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 8 (July 16, 2018): 2932–47. http://dx.doi.org/10.1177/0954410018788922.

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The design of aircraft has evolved over time from the classical design approach to the more modern computer-based design method utilizing multivariate design optimization. In recent years, aircraft concepts and configurations have become more diverse and complex thus pushing many synthesis packages beyond their capability. Furthermore, many examples of aircraft design software focus on the analysis of one particular concept thus requiring separate packages for each concept. This can lead to complications in comparing concepts and configurations as differences in performance may originate from different prediction toolsets being used. This paper presents the GENUS Aircraft Design Framework developed by Cranfield University’s Aircraft Design Group to address these issues. The paper reviews available aircraft design methodologies and describes the challenges faced in their development and application. Following this, the GENUS aircraft design environment is introduced, along with the theoretical background and practical reasoning behind the program architecture. Particular attention is given to the programming, choice of methodology, and optimization techniques involved. Subsequently, some applications of the developed methodology, implemented in the framework are presented to illustrate the diversity of the approach. Three special classes of aircraft design concept are presented briefly.

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Mieloszyk, Jacek, and Andrzej Tarnowski. "Enhancements in conceptual electric aircraft design." Aircraft Engineering and Aerospace Technology 91, no. 6 (June 10, 2019): 851–56. http://dx.doi.org/10.1108/aeat-07-2018-0192.

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PurposeThis paper aims to describe the enhancement of the numerical method for conceptual phase of electric aircraft design.Design/methodology/approachThe algorithm provides a balance between lift force and weight of the aircraft, together with drag and thrust force equilibrium, while modifying design variables. Wing geometry adjustment, mass correction and performance estimation are performed in an iterative process.FindingsAircraft numerical model, which is most often very simplified, has a number of new improvements. This enables to make more accurate analyses and to show relationships between design parameters and aircraft performance.Practical implicationsThe presented approach can improve design results.Originality/valueThe new methodology, which includes enhanced numerical models for conceptual design, has not been presented before.

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6

YOSHIZAKI, Shinichi, and Junzo SATO. "Computer Analysis of Aircraft Conceptual Design." Journal of the Japan Society for Aeronautical and Space Sciences 46, no. 531 (1998): 224–29. http://dx.doi.org/10.2322/jjsass1969.46.224.

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7

UDROIU, Razvan, and Madalina-Ioana BLAJ. "CONCEPTUAL DESIGN OF A VTOL REMOTELY PILOTED AIRCRAFT FOR EMERGENCY MISSIONS." SCIENTIFIC RESEARCH AND EDUCATION IN THE AIR FORCE 18, no. 1 (June 24, 2016): 207–14. http://dx.doi.org/10.19062/2247-3173.2016.18.1.27.

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8

Henderson, R. P., J. R. R. A. Martins, and R. E. Perez. "Aircraft conceptual design for optimal environmental performance." Aeronautical Journal 116, no. 1175 (January 2012): 1–22. http://dx.doi.org/10.1017/s000192400000659x.

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Abstract Consideration of the environmental impact of aircraft has become critical in commercial aviation. The continued growth of air traffic has caused increasing demands to reduce aircraft emissions, imposing new constraints on the design and development of future airplane concepts. In this paper, an aircraft design optimisation framework is used to design aircraft that minimise specific environmental metrics. Multidisciplinary design optimisation is used to optimise aircraft by simultaneously considering airframe, engine and mission. The environmental metrics considered in this investigation are CO2 emissions — which are proportional to fuel burn — and landing-takeoff NOx emissions. The results are compared to those of an aircraft with minimum direct operating cost. The design variables considered in the optimisation problems include aircraft geometry, engine parameters, and cruise settings. An augmented Lagrangian particle swarm optimiser and a genetic algorithm are used to solve the single objective and multi-objective optimisation problems, respectively.

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9

Romli, Fairuz I. "Conceptual Aircraft Design Exploration through Functional Approach." Applied Mechanics and Materials 446-447 (November 2013): 602–5. http://dx.doi.org/10.4028/www.scientific.net/amm.446-447.602.

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In today’s market, it is no longer sufficient to have better designs than the competition. In order to maximize the product’s market potential, it has to be rapidly produced and made available to the market. To reduce their time-to-market period, manufacturers need to shorten their design and development process. It becomes vital that the design architecture solution is derived faster, which can be handful for complex products like an aircraft with the current geometrical-based approaches due to the plethora of physical alternatives to be considered. On the other hand, the search for design architecture solution from functional requirements is theoretically more effective because functional space is comparatively smaller than physical search space. This allows the design efforts to be more focused and this subsequently saves time, efforts and resources. With this notion, there is a driving motivation to adapt functional approaches into the conceptual product design process in order to exploit some of its advertised benefits. In this paper, an example case study of an aircraft conceptual development is presented to highlight possible advantages of approaching architecture solutions from the functional space.

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10

Pornet, C., and A. T. Isikveren. "Conceptual design of hybrid-electric transport aircraft." Progress in Aerospace Sciences 79 (November 2015): 114–35. http://dx.doi.org/10.1016/j.paerosci.2015.09.002.

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11

Malan, Paul, and Eugene F. Brown. "Inlet drag prediction for aircraft conceptual design." Journal of Aircraft 31, no. 3 (May 1994): 616–22. http://dx.doi.org/10.2514/3.46539.

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Neufeld, Daniel, Joon Chung, and Kamran Behdinian. "Aircraft Conceptual Design Optimization Considering Fidelity Uncertainties." Journal of Aircraft 48, no. 5 (September 2011): 1602–12. http://dx.doi.org/10.2514/1.c031312.

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13

Park, Hyeong-Uk, Jae-Woo Lee, Joon Chung, and Kamran Behdinan. "Uncertainty-based MDO for aircraft conceptual design." Aircraft Engineering and Aerospace Technology 87, no. 4 (July 6, 2015): 345–56. http://dx.doi.org/10.1108/aeat-07-2013-0128.

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14

Curran, R., M. Price, S. Raghunathan, E. Benard, S. Crosby, S. Castagne, and P. Mawhinney. "Integrating Aircraft Cost Modeling into Conceptual Design." Concurrent Engineering 13, no. 4 (December 2005): 321–30. http://dx.doi.org/10.1177/1063293x05060698.

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15

Frediani, A., Vittorio Cipolla, K. Abu Salem, V. Binante, and M. Picchi Scardaoni. "Conceptual design of PrandtlPlane civil transport aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 10 (February 1, 2019): 1675–87. http://dx.doi.org/10.1177/0954410019826435.

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According to aircraft manufacturers and several air transportation players, the main challenge the civil aviation will have to deal with in the future is to provide a sustainable growth strategy, in order to face the growing demand of air traffic all over the world. The sustainability requirements are related to air pollution, noise impact, airport congestion, competitiveness of the air transportation systems in terms of travel time and passengers' comfort. Among the possible ways to allow a sustainable growth of the air transportation systems, disruptive aircraft configurations have been object of study for several years, in order to demonstrate that the improvement of aircraft performance can enable the envisaged growth. This paper presents the study of a possible novel configuration called “PrandtlPlane,” having a box-wing layout derived from Prandtl's “Best Wing System” concept. The paper deals with the definition of top level requirements and faces the conceptual study of the overall configuration, focusing on fuselage sizing as well as on the aerodynamic design of the box-wing system. This latter is designed through an optimization-driven strategy, carried out by means of a low-fidelity aerodynamic tool, which simulates the flow condition in the subsonic range and introduces corrections to take the transonic effects into account. Design procedures and tools are presented, showing preliminary results related to a PrandtlPlane compliant with ICAO Aerodrome Reference Code “C” standard, such as Airbus A320 and Boeing 737, whose wingspan is limited to 36 m. Activities and results here shown are part of the first phase of the research project “PARSIFAL” (Prandtlplane ARchitecture for the Sustainable Improvement of Future AirpLanes), funded by the European Commission under the Horizon 2020 Program, which aims to demonstrate that the PrandtlPlane configuration can improve aircraft payload capability, keeping their dimensions compatible with present airport infrastructures.

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OMIYA, Ryohei, and Kenichi RINOIE. "Classification of Aircraft Design Variables using Principal Component Analysis in Aircraft Conceptual Design." AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 16 (2017): 65–71. http://dx.doi.org/10.2322/astj.16.65.

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17

Djojodihardjo, Harijono. "Overview of green quad bubble business jet aerodynamic configuration design." Aircraft Engineering and Aerospace Technology 90, no. 3 (April 9, 2018): 566–82. http://dx.doi.org/10.1108/aeat-12-2016-0241.

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Purpose The purpose of this paper is to explore the possibilities of introducing a number of visionary and pioneering ideas and upcoming enabling technologies for a conceptual and aerodynamic design of green business jet aircraft to meet various requirements within Green and N + 2 Aircraft framework, and at the same time, to meet the requirements of air transportation demand, economic growth and environmental conservation. Design/methodology/approach A synthesis of various aircraft design methodologies has been carried out through iterative optimization to arrive at the conceptually designed aircraft with novel concept with optimum performance within the subsonic flight regimes. Major ideas derived from D8 and other novel concepts are appropriately applied in the work, which starts with fuel efficient motivation, and followed by wing aerodynamics and other critical factors related to the design requirements and objectives. Findings Through a meticulous effort following the synthesized design methodologies in the conceptual design phase, a conceptual design of a quad-bubble business jets with a set of specifications that meet the green and N + 2 aircraft technology requirements and exhibit promising performances is proposed and assessed within recent aircraft technology development. Research limitations/implications The research work is limited to conceptual design and analytical work which should be followed by further iterative steps incorporating experiments and detailed structural and aerodynamic computations. Practical implications The conceptual design proposed can be utilized as a baseline for further practical step in an aircraft development project. Social implications The conceptual design proposed could be utilized for business and economic study for future air transportation system. Originality/value The work is original, incorporating review of state-of-the-art technology, environmental requirements and a synthesis of a novel product.

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Sanchez-Carmona, Alejandro, and Cristina Cuerno-Rejado. "Composite stiffened panel sizing for conceptual tail design." Aircraft Engineering and Aerospace Technology 90, no. 8 (November 5, 2018): 1272–81. http://dx.doi.org/10.1108/aeat-05-2017-0129.

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Purpose A conceptual design method for composite material stiffened panels used in aircraft tail structures and unmanned aircraft has been developed to bear compression and shear loads. Design/methodology/approach The method is based on classical laminated theory to fulfil the requirement of building a fast design tool, necessary for this preliminary stage. The design criterion is local and global buckling happen at the same time. In addition, it is considered that the panel does not fail due to crippling, stiffeners column buckling or other manufacturing restrictions. The final geometry is determined by minimising the area and, consequently, the weight of the panel. Findings The results obtained are compared with a classical method for sizing stiffened panels in aluminium. The weight prediction is validated by weight reductions in aircraft structures when comparing composite and aluminium alloys. Research limitations/implications The work is framed in conceptual design field, so hypotheses like material or stiffeners geometry shall be taken a priori. These hypotheses can be modified if it is necessary, but even so, the methodology continues being applicable. Practical implications The procedure presented in this paper allows designers to know composite structure weight of aircraft tails in commercial aviation or any lifting surface in unmanned aircraft field, even for unconventional configurations, in early stages of the design, which is an aid for them. Originality/value The contribution of this paper is the development of a new rapid methodology for conceptual design of composite panels and the feasible application to aircraft tails and also to unmanned aircraft.

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TSUSHIMA, Hiroki, and Kenichi RINOIE. "Study on Civil Aircraft Weight Estimation Method for Aircraft Conceptual Design." AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 10 (2011): 101–5. http://dx.doi.org/10.2322/astj.10.101.

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20

Chiesa, Sergio, Sabrina Corpino, Marco Fioriti, Alessandro Rougier, and Nicole Viola. "Zonal safety analysis in aircraft conceptual design: application to SAvE aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 227, no. 4 (March 22, 2012): 714–33. http://dx.doi.org/10.1177/0954410012441430.

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21

Morris, Robert, and Anjan Chakrabarty. "Addressing Autonomy in Conceptual Design." AI Magazine 40, no. 2 (June 24, 2019): 3–16. http://dx.doi.org/10.1609/aimag.v40i2.2856.

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Aircraft design is an iterative process of creating a design concept from a set of requirements. Conceptual design is an early phase in the process, during which preliminary decisions and trade studies are made from a set of requirements related to mission objective and costs. Although much attention has been paid to applying autonomy technologies to robotic systems, including air vehicles, there has been little attention paid to incorporating autonomy as part of the conceptual design process. Consequently, designing for autonomy tends to be retrofitted to a vehicle that has already gone through a complete design process rather than as part of the initial process. This derivative approach to designing autonomous systems is suboptimal, and there is evidence that this has hindered the acceptance of autonomy technologies. This article proposes an approach to conceptual design for aircraft that incorporates autonomy into the conceptual design process. To illustrate the principles introduced, we consider the example of configuring an autonomous small unmanned aerial vehicle for searching and tracking a target of interest.

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Dowling, A. P., and T. Hynes. "Towards a silent aircraft." Aeronautical Journal 110, no. 1110 (August 2006): 487–94. http://dx.doi.org/10.1017/s000192400000138x.

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Abstract We set a target for a ‘Silent’ aircraft to be imperceptible outside the airfield perimeter in an urban environment, and then address conceptual designs to meet this requirement. Avoiding some traditional aircraft noise sources requires a radical rethink about the configuration. An all-lifting design has many benefits, enabling a closer integration of airframe and engine than the traditional ‘tube and wing’. Low-noise design includes taking advantage of shielding of engine noise by the airframe; low-noise engines with large, low speed jets; an order of magnitude increase in absorption by liners; and operations for low-noise informing the design. Progress to date on the Silent Aircraft Initiative is presented, along with some conceptual aircraft and engine designs. The further work needed to develop these into viable future aircraft is discussed.

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23

Abu-Hamdeh, Nidal H., Khaled A. Alnefaie, and Majed K. Al-Hajjaj. "Conceptual Design of Solar Powered Unmanned Arial Vehicle." Applied Mechanics and Materials 225 (November 2012): 299–304. http://dx.doi.org/10.4028/www.scientific.net/amm.225.299.

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The solar-powered aircraft represents a major step forward in environmentally friendly vehicle technology. An unmanned aircraft vehicle (UAV) was designed to fly for 24 hours continuously to achieve surveillance at low altitude. It is a lightweight, solar-powered, remotely piloted flying wing aircraft that is demonstrating the technology of applying solar power for long-duration and low-altitude flight. Several programs and codes were used in the designing process of the UAV and generating its layout. A MATLAB computer programming code was written to optimize on various values of aspect ratio (AR) and wingspan (b) after setting the mission requirements and estimating the technological parameters. A program called Java Foil was used to calculate the lift. Another program called RDS was used to obtain the final layout of the aircraft. The great benefit is that the design is general enough to be applied to different values of aspect ratio and wingspan. Moreover, the analytical form of the method allows identifying clear some general principles like the optimization on various values of aspect ratio and wingspan, and the calculation of the lift.

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Singh, Vedant, Somesh K. Sharma, and S. Vaibhav. "Transport Aircraft Conceptual Design Optimization Using Real Coded Genetic Algorithm." International Journal of Aerospace Engineering 2016 (2016): 1–11. http://dx.doi.org/10.1155/2016/2813541.

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Due to soaring oil prices, increased air traffic and competition among air transport companies, and environmental concerns, aircraft maximum takeoff weight (MTOW) is becoming a critical aspect, of air transport industry. It is very important to estimate the MTOW of the aircraft in order to determine its performance. However, estimating the weight of an aircraft is not a simple task. The purpose of this paper is to present a simplified method to optimize the aircraft MTOW using a genetic algorithm approach. For the optimization of MTOW of transport aircraft, a MATLAB program consisting of genetic algorithm techniques with appropriate genetic algorithm parameters setting was developed. The objective function for the optimization was a minimization of MTOW. The use of genetic real coded algorithm (GA) as an optimization tool for an aircraft can help to reduce the number of qualitative decisions. Also, using GA approach, the time and the cost of conceptual design can considerably be reduced. The model is applicable to the air transport industry. The proposed model has been validated against the known configuration of an aircraft.

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Rinoie, Kenichi, and Yu Tsumuraya. "Aircraft Conceptual Design Sizing Method for Undergraduate Education." JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 51, no. 597 (2003): 585–88. http://dx.doi.org/10.2322/jjsass.51.585.

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Bos, A. H. W. "Aircraft conceptual design by genetic/gradient-guided optimization." Engineering Applications of Artificial Intelligence 11, no. 3 (June 1998): 377–82. http://dx.doi.org/10.1016/s0952-1976(98)00009-8.

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Sutradhar, Trinayan, and E. Vijayaragavan. "Conceptual design of “S-39” aircraft carried submarine." IOP Conference Series: Materials Science and Engineering 402 (October 1, 2018): 012192. http://dx.doi.org/10.1088/1757-899x/402/1/012192.

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Risse, Kristof, and Eike Stumpf. "Conceptual aircraft design with hybrid laminar flow control." CEAS Aeronautical Journal 5, no. 3 (May 15, 2014): 333–43. http://dx.doi.org/10.1007/s13272-014-0111-6.

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Munjulury, Raghu Chaitanya, Ingo Staack, Patrick Berry, and Petter Krus. "A knowledge-based integrated aircraft conceptual design framework." CEAS Aeronautical Journal 7, no. 1 (November 19, 2015): 95–105. http://dx.doi.org/10.1007/s13272-015-0174-z.

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Gavel, Hampus, Johan Olvander, and Petter Krus. "Optimal Conceptual Design of Aircraft Fuel Transfer Systems." Journal of Aircraft 43, no. 5 (September 2006): 1334–40. http://dx.doi.org/10.2514/1.19548.

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Wang, Yu, Shuai Zhang, and Xiong Qing Yu. "Estimation of Emissions for Civil Jet Conceptual Design." Applied Mechanics and Materials 448-453 (October 2013): 596–99. http://dx.doi.org/10.4028/www.scientific.net/amm.448-453.596.

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Parts of emission from the aircraft engine are doing harm to the environment. The greenhouse gas emission (CO2 equivalent) per passenger per thousand kilometers is used to measure the emissions in this work. And a new estimation method of emissions for aircraft conceptual design was proposed, based on the ICAO aircraft engine emissions databank and the response surface fitting methods. Because the amounts of greenhouse effects of various pollutant gases rely on altitudes, the estimation accuracy of emission was improved by refining the flight dynamics models in various stages of mission profile. The impacts of the wing configuration on greenhouse effect were discussed, after verifying the accuracy of this proposed method. The results indicate that the greenhouse gas emissions could be reduced by appropriately increasing wing sweep and aspect ratio.

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Nöding, Michel, and Lothar Bertsch. "Application of Noise Certification Regulations within Conceptual Aircraft Design." Aerospace 8, no. 8 (August 3, 2021): 210. http://dx.doi.org/10.3390/aerospace8080210.

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ICAO Annex 16 regulations are used to certify the acoustic performance of subsonic transport aircraft. Each aircraft is classified according to the measured EPNL levels at specific certification locations along the approach and departure. By simulating this certification process, it becomes possible to identify all relevant parameters and assess promising measures to reduce the noise certification levels in compliance with the underlying ICAO regulations, i.e., allowable operating conditions of the aircraft. Furthermore, simulation is the only way to enable an assessment of novel technology and non-existing vehicle concepts, which is the main motivation behind the presented research activities. Consequently, the ICAO Annex 16 regulations are integrated into an existing noise simulation framework at DLR, and the virtual noise certification of novel aircraft concepts is realized at the conceptual design phase. The predicted certification levels can be directly selected as design objectives in order to realize an advantageous ICAO noise category for a new aircraft design, i.e., simultaneously accounting for the design and the resulting flight performance. A detailed assessment and identification of operational limits and allowable flight procedures for each conceptual aircraft design under consideration is enabled. Sensitivity studies can be performed for the relevant input parameters that influence the predicted noise certification levels. Specific noise sources with a dominating impact on the certification noise levels can be identified, and promising additional low-noise measures can be applied within the conceptual design phase. The overall simulation process is applied to existing vehicles in order to assess the validity of the simulation resultsfcompared to published data. Thereafter, the process is applied to some DLR low-noise aircraft concepts to evaluate their noise certification levels. These results can then be compared to other standard noise metrics that are typically applied in order to describe aircraft noise, e.g., SEL isocontour areas. It can be demonstrated that certain technologies can significantly reduce the noise impact along most of an approach or departure flight track but have only a limited influence on the noise certification levels and vice versa. Finally, an outlook of the ongoing developments is provided, in order to apply the new simulation process to supersonic aircraft. Newly proposed regulations for such concepts are implemented into the process in order to evaluate these new regulations and enable direct comparison with existing regulations.

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SHIBATA, Kazuki, and Kenichi RINOIE. "Aircraft Conceptual Design Method Considering Secondary Power Systems Effect on Aircraft Performance." AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 14 (2015): 23–32. http://dx.doi.org/10.2322/astj.14.23.

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Alkaya, Can, Ashish Alex Sam, and Apostolos Pesyridis. "Conceptual Advanced Transport Aircraft Design Configuration for Sustained Hypersonic Flight." Aerospace 5, no. 3 (September 1, 2018): 91. http://dx.doi.org/10.3390/aerospace5030091.

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The conceptual aircraft design and its integration with a combined cycle engine for hypersonic cruise at Mach 8 is documented in this paper. The paper describes the process taken to develop a hypersonic aircraft from a conceptual approach. The discussion also includes the design and CFD analysis of the integrated combined cycle engine. A final conceptual hypersonic transport aircraft with an integrated combined cycle engine was achieved through this study. According to the analysis carried out, the aircraft is able to take-off and land at the airports it is intended to be used and will be able to generate enough thrust to sustain hypersonic cruise at an altitude of 30 km.

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Davies, W. J., R. A. Baumbick, and R. W. Vizzini. "Conceptual Design of an Optic-Based Engine Control System." Journal of Engineering for Gas Turbines and Power 110, no. 1 (January 1, 1988): 28–32. http://dx.doi.org/10.1115/1.3240082.

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Advanced integrated flight and propulsion control systems may require the use of optic technology to provide enhanced electromagnetic immunity and reduced weight. Immunity to electromagnetic interference and pulses is required for integrated systems where flight and propulsion control systems communicate with each other and diverse systems located throughout a composite aircraft. Weight reduction is crucial to the complex engine control systems required for advanced engines incorporating diagnostics, variable geometry and vectoring/reversing exhaust nozzles. A team of Pratt & Whitney, McDonnell Aircraft, Hamilton Standard, and United Technologies Research Center have developed the conceptual design of an optic engine control system, under a contract from NASA Lewis, entitled Fiber Optic Control System Integration (FOCSI). FOCSI is a triservice/NASA joint program designed to provide the optic technology requirements for advanced fighter/attack aircraft.

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Liu, Dianzi, Chuanwei Zhang, Z. Wan, and Z. Du. "Topology optimization of a novel fuselage structure in the conceptual design phase." Aircraft Engineering and Aerospace Technology 90, no. 9 (November 14, 2018): 1385–93. http://dx.doi.org/10.1108/aeat-04-2017-0100.

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Purpose In recent years, innovative aircraft designs have been investigated by researchers to address the environmental and economic issues for the purpose of green aviation. To keep air transport competitive and safe, it is necessary to maximize design efficiencies of the aircrafts in terms of weight and cost. The purpose of this paper is to focus on the research which has led to the development of a novel lattice fuselage design of a forward-swept wing aircraft in the conceptual phase by topology optimization technique. Design/methodology/approach In this paper, the fuselage structure is modelled with two different types of elements – 1D beam and 2D shell – for the validation purpose. Then, the finite element analysis coupled with topology optimization is performed to determine the structural layouts indicating the efficient distributed reinforcements. Following that, the optimal fuselage designs are obtained by comparison of the results of 1D and 2D models. Findings The topological results reveal the need for horizontal stiffeners to be concentrated near the upper and lower extremities of the fuselage cross section and a lattice pattern of criss-cross stiffeners should be well-placed along the sides of the fuselage and near the regions of window locations. The slight influence of windows on the optimal reinforcement layout is observed. To form clear criss-cross stiffeners, modelling the fuselage with 1D beam elements is suggested, whereas the less computational time is required for the optimization of the fuselage modelled using 2D shell elements. Originality/value The authors propose a novel lattice fuselage design in use of topology optimization technique as a powerful design tool. Two types of structural elements are examined to obtain the clear reinforcement detailing, which is also in agreement with the design of the DLR (German Aerospace Center) demonstrator. The optimal lattice layout of the stiffeners is distinctive to the conventional semi-monocoque fuselage design and this definitely provides valuable insights into the more efficient utilization of composite materials for novel aircraft designs.

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Formentini, Giovanni, Claudio Favi, Claude Cuiller, Pierre-Eric Dereux, Francois Bouissiere, and Cédric Jurbert. "CONCEPTUAL DESIGN FOR ASSEMBLY IN AEROSPACE INDUSTRY: SENSITIVITY ANALYSIS OF MATHEMATICAL FRAMEWORK AND DESIGN PARAMETERS." Proceedings of the Design Society 1 (July 27, 2021): 731–40. http://dx.doi.org/10.1017/pds.2021.73.

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AbstractOne of the most challenging activity in the engineering design process is the definition of a framework (model and parameters) for the characterization of specific processes such as installation and assembly. Aircraft system architectures are complex structures used to understand relation among elements (modules) inside an aircraft and its evaluation is one of the first activity since the conceptual design. The assessment of aircraft architectures, from the assembly perspective, requires parameter identification as well as the definition of the overall analysis framework (i.e., mathematical models, equations).The paper aims at the analysis of a mathematical framework (structure, equations and parameters) developed to assess the fit for assembly performances of aircraft system architectures by the mean of sensitivity analysis (One-Factor-At-Time method). The sensitivity analysis was performed on a complex engineering framework, i.e. the Conceptual Design for Assembly (CDfA) methodology, which is characterized by level, domains and attributes (parameters). A commercial aircraft cabin system was used as a case study to understand the use of different mathematical operators as well as the way to cluster attributes.

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Joiner, Keith F., Jordan Zahra, and Obaid Rehman. "Conceptual sizing of next supersonic passenger aircraft from regression of the limited existing designs." MATEC Web of Conferences 198 (2018): 05001. http://dx.doi.org/10.1051/matecconf/201819805001.

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Despite previous versions, there are no current supersonic passenger transport aircraft. Much aircraft research is focused on hypersonic flight and the new technologies therein and is therefore unlikely to add to commercial versions anytime soon. This study re-examines conceptual sizing of a supersonic transport aircraft based on extant supersonic designs in order to ignite research into whether a commercially-viable design might exist. Key metrics are developed using distances between likely airport network nodes, an assumed number of passengers, and a reduction in transport time to one-third of current journeys. The study uses multiple response regression of known designs to develop key performance formulae, which are then optimized to set performance values so as to estimate an initial aircraft size, including an expected value analysis to guide the next conceptual design iteration. Twenty years ago a NASA Langley Research optimization system was used to examine non-linear regression of supersonic aircraft designs and to optimize such a design around similar performance criteria. In contrast, this work is the first supersonic transport aircraft sizing to use commercially-available Excel add-on software and standard design-for-sixsigma analysis techniques; notably for the sensitivity analyses to guide the next design iteration.

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Nam, Taewoo, and Dimitri N. Mavris. "Multistage Reliability-Based Design Optimization and Application to Aircraft Conceptual Design." Journal of Aircraft 55, no. 5 (September 2018): 2022–36. http://dx.doi.org/10.2514/1.c032099.

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van Dommelen, Jorrit, and Roelof Vos. "Conceptual design and analysis of blended-wing-body aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 228, no. 13 (January 29, 2014): 2452–74. http://dx.doi.org/10.1177/0954410013518696.

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Due to the unconventional nature of the blended wing body (BWB) no off-the-shelf software package exists for its conceptual design. This study details a first step towards the implementation of traditional and BWB-specific design and analysis methods into a software tool to enable preliminary sizing of a BWB. The tool is able to generate and analyze different BWB configurations on a conceptual level. This paper investigates three different BWB configurations. The first configuration is an aft-swept BWB with aft-mounted engines, the second configuration is an aft-swept BWB with wing-mounted engines and the third configuration is a forward-swept BWB with wing-mounted engines. These aircraft comply with the same set of top-level requirements and airworthiness requirements. Each of the designs has been optimized for maximum harmonic range, while keeping its maximum take-off weight constant and identical. Results show that the forward-swept configuration with wing-mounted engines has the highest harmonic range. These findings warrant further investigation in this configuration and other alternative BWB configurations.

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41

Dag, Fatih Mehmet, and Ozgur Tamer. "Conceptual Design of Low Altitude Unmanned Small Hybrid Airship." International Research Journal of Electronics and Computer Engineering 4, no. 1 (March 30, 2018): 11. http://dx.doi.org/10.24178/irjece.2018.4.1.11.

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In the last two decades, popularity of Unmanned Air Systems (UAS) are at their peaks. Their capacities and abilities are advancing day by day in parallel with development of science and technology. They are doing almost everything what conventional aircrafts are doing except passenger transfer, for now. Despite an UAS can be controlled from thousands of miles away, they are still limited in range and endurance because of their energy storage capacities. Most of the energy sources of an aircraft is used against to gravitational force. However, Lighter Than Air(LTA) gases like helium, hydrogen etc. provides an option to aircrafts using lifting capacity of these gases and combination of lifting capacity of LTA gases and mechanical forces produced by engines allows engineers to create hybrid airships. Hybrid Airships gains flight altitude by using static lifting force of lighter than air gases in addition of the mechanical force which is produced by the propulsion system of the vehicle. Engines makes necessary maneuver with direction units to control the airship in all directions. Static lift from the LTA gases provide additional payload capacity to vehicle without consuming energy. Therefore, unlike the conventional aircrafts, hybrid airship has more flight duration than the others and more payload capacity. Aim of this work is, developing a low-cost small hybrid airship by using static lift force of the lighter than air gases and present to advantages of hybrid aircrafts.

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42

Mulyanto, Taufiq, and M. Luthfi Nurhakim. "CONCEPTUAL DESIGN OF BLENDED WING BODY BUSINESS JET AIRCRAFT." Journal of KONES. Powertrain and Transport 20, no. 4 (January 1, 2015): 299–306. http://dx.doi.org/10.5604/12314005.1137630.

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Blasi, Luciano, Luigi Iuspa, and Giuseppe Del Core. "Conceptual Aircraft Design Based on a Multiconstraint Genetic Optimizer." Journal of Aircraft 37, no. 2 (March 2000): 351–54. http://dx.doi.org/10.2514/2.2604.

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SHINKAKU, Akane, and Kenichi RINOIE. "Study on Aircraft Conceptual Design Method Applying Genetic Programming." AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 13 (2014): 33–40. http://dx.doi.org/10.2322/astj.13.33.

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Machida, Yasuaki, and Kenichi Rinoie. "Optimum Conceptual Design of Single Engine Turbo-Prop Aircraft." JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 52, no. 606 (2004): 295–301. http://dx.doi.org/10.2322/jjsass.52.295.

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Mallik, Wrik, Joseph A. Schetz, and Rakesh K. Kapania. "Rapid Transonic Flutter Analysis for Aircraft Conceptual Design Applications." AIAA Journal 56, no. 6 (June 2018): 2389–402. http://dx.doi.org/10.2514/1.j056218.

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Antoine, Nicolas E., and Ilan M. Kroo. "Framework for Aircraft Conceptual Design and Environmental Performance Studies." AIAA Journal 43, no. 10 (October 2005): 2100–2109. http://dx.doi.org/10.2514/1.13017.

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Liu, Hu, Zhe Wu, and Daniel P. Raymer. "Automated Scheme Adjustment for Conceptual Aircraft Design and Optimization." Journal of Aircraft 43, no. 3 (May 2006): 825–31. http://dx.doi.org/10.2514/1.14138.

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Newberry, Conrad F. "The conceptual design of deck-launched waverider-configured aircraft." Aircraft Design 1, no. 3 (September 1998): 159–91. http://dx.doi.org/10.1016/s1369-8869(98)00015-9.

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FENG, Haocheng, Mingqiang LUO, Hu LIU, and Zhe WU. "A Knowledge-based and Extensible Aircraft Conceptual Design Environment." Chinese Journal of Aeronautics 24, no. 6 (December 2011): 709–19. http://dx.doi.org/10.1016/s1000-9361(11)60083-6.

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