Improved Representation of High Lift Devices for a Multidisciplinary Preliminary Aircraft Design Process

2008 ◽  
Author(s):  
Christian Werner-Westphal ◽  
Wolfgang Heinze ◽  
Peter Horst
Keyword(s):  
Design Process ◽  
Aircraft Design ◽  
High Lift ◽  
Preliminary Aircraft Design

EPISTLE: High lift system design for low-noise applied to a supersonic aircraft

2006 ◽  
Vol 110 (1107) ◽  
pp. 327-331 ◽  
Author(s):  
U. Herrmann
Keyword(s):  
System Design ◽  
Aircraft Design ◽  
Reynolds Numbers ◽  
Low Noise ◽  
High Lift ◽  
New Approach ◽  
Low Speed ◽  
Supersonic Aircraft ◽  
Preliminary Aircraft Design ◽  
High Reynolds

Abstract A new approach for low-drag high-lift system design based on the application of viscous flow solvers was developed in the EC research project EPISTLE. Two high-lift systems for a supersonic commercial transport aircraft (SCT) wing were designed, manufactured and wind-tunnel tested. The predicted large drag reductions were fully confirmed by tests at high Reynolds numbers. These drag reductions significantly reduce the low-speed noise of future SCT configurations. This was estimated by preliminary aircraft design tools. Low-speed noise reduction by aerodynamic means is obtained, as effective high-lift systems enable these aircraft to climb faster.

Improved Representation of High-Lift Devices for a Multidisciplinary Conceptual Aircraft Design Process

2009 ◽  
Vol 46 (6) ◽  
pp. 1984-1994 ◽  
Author(s):  
Christian Werner-Spatz ◽  
Wolfgang Heinze ◽  
Peter Horst
Keyword(s):  
Design Process ◽  
Aircraft Design ◽  
High Lift ◽  
Conceptual Aircraft Design

Integration of Crashworthiness Aspects into Preliminary Aircraft Design

2014 ◽  
Vol 598 ◽  
pp. 146-150 ◽  
Author(s):  
Dominik B. Schwinn
Keyword(s):  
Design Process ◽  
Aircraft Design ◽  
Analysis Tool ◽  
Preliminary Design ◽  
Design Phase ◽  
Crash Analysis ◽  
Early Design ◽  
Preliminary Aircraft Design ◽  
Early Design Stages ◽  
Certification Requirement

Crashworthiness proof is a certification requirement by aviation authorities for new aircraft types. The objective of static design is a sufficiently stiff and strong structure to carry bending and torsion during flight and ground maneuvers. High stiffness, however, is critical for good crashworthiness behavior. Therefore, crashworthiness investigations should be included at early design stages of the overall aircraft design process. This paper introduces the crash analysis tool AC-CRASH and shows an approach of integrating it into the preliminary design phase.

scholarly journals Structural design process and subsequent flight mechanical evaluation in preliminary aircraft design: demonstrated on passenger ride comfort assessment

2021 ◽  
Author(s):  
Vikram Krishnamurthy ◽  
Vega Handojo
Keyword(s):  
Design Process ◽  
Structural Design ◽  
Assessment Tool ◽  
Ride Comfort ◽  
Aircraft Design ◽  
Flight Mechanics ◽  
Design Stage ◽  
Preliminary Aircraft Design ◽  
The Impact ◽  
Tools And Methods

AbstractNew fuel-efficient aircraft designs have high aspect ratio wings. Consequently, those aircraft are more flexible. Additionally, load alleviation functions are implemented to reduce the structural loads, which results in further reductions of the structural stiffness. At the same time, the structural design impacts other disciplines in preliminary aircraft design, especially flight mechanics. For example, it is important to know how at that design stage such flexible aircraft with load alleviation affect passenger ride comfort in turbulent flight. For an efficient design process, it is essential to answer such questions with accurate multi-disciplinary tools and methods as early as possible to minimize development risk and avoid costly and time-consuming redesign loops. Current available tools and methods are not accurate enough for this task. To address this issue, the DLR MONA based design and the TUB flight mechanical assessment tool MITRA are linked to investigate the impact of the structural design on specific flight mechanical assessments such as passenger ride comfort. This is particularly interesting since the implemented load alleviation functions are designed to reduce loads, and not explicitly to improve passenger ride comfort. By conducting this assessment for a particular aircraft configuration, more insight into passenger ride comfort and the key contributors can be gained during preliminary design. This paper describes the combined toolchain and its application on a generic long-range reference aircraft to investigate the effects of load alleviation functions on passenger ride comfort and discusses the results.

Method for Estimation of Electrical Wiring Interconnection Systems in Preliminary Aircraft Design

2019 ◽  
Vol 56 (3) ◽  
pp. 1259-1263 ◽  
Author(s):  
Francesca Tomasella ◽  
Marco Fioriti ◽  
Luca Boggero ◽  
Sabrina Corpino
Keyword(s):  
Aircraft Design ◽  
Preliminary Aircraft Design ◽  
Electrical Wiring

Advanced aircraft performance analysis

2018 ◽  
Vol 90 (4) ◽  
pp. 627-638 ◽  
Author(s):  
Marc Immer ◽  
Philipp Georg Juretzko
Keyword(s):  
Performance Analysis ◽  
Design Process ◽  
Performance Optimization ◽  
Electric Propulsion ◽  
Vertical Plane ◽  
Aircraft Design ◽  
Efficient Design ◽  
Content Type ◽  
Aircraft Performance ◽  
Hybrid Electric

Purpose The preliminary aircraft design process comprises multiple disciplines. During performance analysis, parameters of the design mission have to be optimized. Mission performance optimization is often challenging, especially for complex mission profiles (e.g. for unmanned aerial vehicles [UAVs]) or hybrid-electric propulsion. Therefore, the purpose of this study is to find a methodology that supports aircraft performance analysis and that is applicable to complex profiles and to novel designs. Design/methodology/approach As its core element, the developed method uses a computationally efficient C++ software “Aircraft Performance Program” (APP), which performs a segment-based mission computation. APP performs a time integration of the equations of motion of a point mass in the vertical plane. APP is called via a command line interface from a flexible scripting language (Python). On top of APP’s internal radius of action optimization, state-of-the-art optimization packages (SciPy) are used. Findings The application of the method to a conventional climb schedule shows that the definition of the top of climb has a significant influence on the resulting optimum. Application of the method to a complex UAV mission optimization, which included maximizing the radius of action, was successful. Low computation time enables to perform large parametric studies. This greatly improves the interpretation of the results. Research limitations/implications The scope of the paper is limited to the methodology that allows for advanced performance analysis at the conceptual and preliminary design stages with an emphasis on novel propulsion concepts. The methodology is developed using existing, validated methods, and therefore, this paper does not contain comprehensive validation. Other disciplines, such as cost analysis, life-cycle assessment or market analysis, are not considered. Practical implications With the proposed method, it is possible to obtain not only the desired optimum mission performance but also off-design performance of the investigated design. A thorough analysis of the mission performance provides insight into the design’s capabilities and shortcomings, ultimately aiding in obtaining a more efficient design. Originality/value Recent developments in the area of hybrid or hybrid-electric propulsion systems have shown the need for performance computation tools aiding the related design process. The presented method is especially valuable when novel design concepts with complex mission profiles are investigated.

Advancements in a Web-Based Framework in Product Family Optimization and Visualization

2004 ◽  
Author(s):  
Jessica L. Mulberger ◽  
Timothy W. Simpson
Keyword(s):  
Design Process ◽  
Product Family ◽  
Aircraft Design ◽  
Product Variety ◽  
General Aviation ◽  
Design Parameters ◽  
Web Based ◽  
Ongoing Research ◽  
Product Platforms ◽  
Number Of Customers

Today’s market is becoming increasingly more competitive as companies strive to achieve success by reaching a large number of customers in a mass market while simultaneously treating them as individuals in a customized market. Many companies have begun to appreciate the benefits of using product platforms as they increase the customizability of their offered products, while reducing development costs and time to market. However, product variety is not customization; it is simply an attempt on the part of a company to meet the individual needs of their customers by flooding the market with many variations of the same product. With recent innovations in the field of information technology, web-based product development methodologies provide the capability for advanced customer involvement during the design process, which is a crucial aspect of differentiating customization from variety. Current approaches have provided web-based frameworks where users are offered a limited amount of control in the design process by assembling different configurations of given modules or by choosing a product already available in the company database. The focus in this paper is on advancements to a web-based framework where design parameters are collected from the user by means of a web-based browser interface, optimization is completed using the specified parameters, and a 3D visual representation is dynamically provided based on the results from the optimization. This proposed framework is illustrated using an example from ongoing research involving General Aviation Aircraft design.

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