scholarly journals Wing Structural Model for Overall Aircraft Design of Distributed Electric Propulsion General Aviation and Regional Aircraft

Aerospace ◽  
2021 ◽  
Vol 9 (1) ◽  
pp. 5
Author(s):  
Raquel Alonso Castilla ◽  
Florent Lutz ◽  
Joël Jézégou ◽  
Emmanuel Bénard
Keyword(s):  
Conceptual Design ◽  
Electric Propulsion ◽  
Structural Model ◽  
Aircraft Design ◽  
General Aviation ◽  
The European Union ◽  
Analytical Methodology ◽  
Conceptual Design Phase ◽  
Aerodynamic Properties ◽  
Structural Mass

In the context of reducing the environmental footprint of tomorrow’s aviation, Distributed Electric Propulsion (DEP) has become an increasingly interesting concept. With the strong coupling between disciplines that this technology brings forth, multiple benefits are expected for the overall aircraft design. These interests have been observed not only in the aerodynamic properties of the aircraft but also in the structural design. However, current statistical models used in conceptual design have shown limitations regarding the benefits and challenges coming from these new design trends. As for other methods, they are either not adapted for use in a conceptual design phase or do not cover CS-23 category aircraft. This paper details a semi-analytical methodology compliant with the performance-based certification criteria presented by the European Union Aviation Safety Agency (EASA) to predict the structural mass breakdown of a wing. This makes the method applicable to any aircraft regulated by EASA CS-23. Results have been validated with the conventional twin-engine aircraft Beechcraft 76, the innovative NASA X-57 Maxwell concept using DEP, and the commuter aircraft Beechcraft 1900.

Aerodynamic Loads Prediction in an Integrated Computer-Based Conceptual Design Environment

2003 ◽  
Author(s):  
M. W. Goldstraw ◽  
C. Bil ◽  
C. Nicholson
Keyword(s):  
Conceptual Design ◽  
Aircraft Design ◽  
Automated System ◽  
Aerodynamic Load ◽  
Design Environment ◽  
Design Data ◽  
Conceptual Design Phase ◽  
Design Changes ◽  
Computer Based ◽  
Step Over

An important aspect of successful aircraft design is the concept of ‘right first time’, as any design changes downstream can be costly and may cause project delays. This is most applicable to the conceptual design phase. However, in the early stages of aircraft design, data is limited and prone to inaccuracies. Consequently, a design will typically traverse through a number of iterations, improving and refining with each step. Over the past 15 years, computer-based tools have become commonplace in aircraft design [1]. In general, most computer-based tools have been developed for the more advanced stages of the design process. For these tools to be useful in conceptual design, they must be user-friendly, interactive, and provide quick return times. A classic example is the aerodynamic load data required for structural design. Both are dependent on geometric parameters, which may still be subject to change. To complete the analysis within practical time constraints, a highly integrated and automated system is required [2, 3]. This paper presents such a system, developed using industry accepted software components including AutoCAD, VSAERO and MSC Nastran. This system allows an automatic, structured topology mesh to be generated from a basic three-view aircraft drawing, which inputs directly into VSAERO for loads calculations. The loads are subsequently transferred to MSC Patran as a pre-processor for structural analysis using MSC Nastran. If the result is unsatisfactory, the geometry or placement of structural components can easily be changed and the process repeated. The design environment was developed using FORTRAN90. The results of an application of this system to a simple wing, as well as a regional transport aircraft, are also presented.

Conceptual Design for the Performance Optimization of Compound Coaxial Helicopter

2016 ◽  
Vol 826 ◽  
pp. 40-44 ◽  
Author(s):  
Fei Cao ◽  
Ming Chen ◽  
Mei Li Wen Wu
Keyword(s):  
Conceptual Design ◽  
Performance Optimization ◽  
Design Method ◽  
Aircraft Design ◽  
Design Parameters ◽  
Design Work ◽  
Design And Optimization ◽  
Conceptual Design Phase ◽  
And Performance ◽  
Coaxial Helicopter

The purpose of this paper is to study the conceptual design and optimization of a compound coaxial helicopter. At the conceptual design phase, the compound coaxial helicopter design work was based on the conventional helicopter and fix-wing aircraft design method. The intersection of these aspects makes the design work more complex, thus, a program for the sizing and performance optimization was developed for the aircraft. The program included the total weight design, aerodynamic analysis, flight dynamics analysis, performance calculation and particle swarm optimization analysis. Under the restricted condition of the flight performance requirements, optimize the design parameters which make the weight efficiency factor decrease. Therefore, the study of optimum design process was warranted.

scholarly journals Application of Noise Certification Regulations within Conceptual Aircraft Design

Aerospace ◽  
2021 ◽  
Vol 8 (8) ◽  
pp. 210
Author(s):  
Michel Nöding ◽  
Lothar Bertsch
Keyword(s):  
Conceptual Design ◽  
Aircraft Design ◽  
Low Noise ◽  
Operating Conditions ◽  
Published Data ◽  
Design Phase ◽  
Simulation Process ◽  
Research Activities ◽  
Conceptual Design Phase ◽  
Conceptual Aircraft Design

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.

Future aircraft concepts and design methods

2021 ◽  
pp. 1-33
Author(s):  
Robert A. McDonald ◽  
Brian J. German ◽  
T. Takahashi ◽  
C. Bil ◽  
W. Anemaat ◽  
...  
Keyword(s):  
Collaborative Design ◽  
Electric Propulsion ◽  
Travel Demand ◽  
Ghg Emissions ◽  
Aircraft Design ◽  
General Aviation ◽  
Civil Aviation ◽  
Joint Decision ◽  
Trade Offs ◽  
Multidisciplinary Design Optimisation

Abstract With an annual growth in travel demand of about 5% globally, managing the environmental impact is a challenge. In 2019, the International Civil Aviation Organisation (ICAO) issued emission reduction targets, including well-to-wake greenhouse gas (GHG) emissions reduced at least 50% from 2005 levels by 2050. This discusses several technologies from an aircraft design perspective that can contribute to achieving these targets. One thing is certain: aircraft will look different in the future. The Transonic Truss-Braced Wing and Flying V configurations are promising significant efficiency improvements over conventional configurations. Electric propulsion, in various architectures, is becoming a feasible option for general aviation and commuter aircraft. It will be a growing field of aviation with zero-emissions flight and opportunities for special missions. Lastly, this paper discusses methods and design processes that include all relevant disciplines to ensure that the aircraft is optimised as a complete system. While empirical methods are essential for initial design, Multidisciplinary Design Optimisation (MDO) incorporates models and simulations integrated in an optimisation environment to capture critical trade-offs. Concurrent design places domain experts in one site to facilitate collaboration, interaction, and joint decision-making, and to ensure all disciplines are equally considered. It is supported by a Collaborative Design Facility (CDF), an information technology facility with connected hardware and software tools for design analysis.

Applying Function-Based Failure Propagation in Conceptual Design

2007 ◽  
Author(s):  
Daniel Krus ◽  
Katie Grantham Lough
Keyword(s):  
Risk Analysis ◽  
Product Design ◽  
Conceptual Design ◽  
Functional Model ◽  
Thermal Control ◽  
Design Phase ◽  
Historical Knowledge ◽  
Conceptual Design Phase ◽  
Failure Propagation ◽  
Potential Risks

When designing a product, the earlier the potential risks can be identified, the more costs can be saved, as it is easier to modify a design in its early stages. Several methods exist to analyze the risk in a system, but all require a mature design. However, by applying the concept of “common interfaces” to a functional model and utilizing a historical knowledge base, it is possible to analyze chains of failures during the conceptual phase of product design. This paper presents a method based on these “common interfaces” to be used in conjunction with other methods such as Risk in Early Design in order to allow a more complete risk analysis during the conceptual design phase. Finally, application of this method is demonstrated in a design setting by applying it to a thermal control subsystem.

Conceptual design of electric propulsion systems for ultralight manned airplane

2020 ◽  
pp. 5-14
Author(s):  
A.V. Varyukhin ◽  
V.S. Zakharchenko ◽  
A.V. Geliev ◽  
M.V. Gordin ◽  
I.O. Kiselev ◽  
...  
Keyword(s):  
Conceptual Design ◽  
Electric Propulsion ◽  
Propulsion Systems
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