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

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.

Environmental assessment of hybrid-electric propulsion in conceptual aircraft design

2020 ◽  
Vol 247 ◽  
pp. 119477 ◽  
Author(s):  
João Ribeiro ◽  
Frederico Afonso ◽  
Inês Ribeiro ◽  
Bruna Ferreira ◽  
Hugo Policarpo ◽  
...  
Keyword(s):  
Environmental Assessment ◽  
Electric Propulsion ◽  
Aircraft Design ◽  
Conceptual Aircraft Design ◽  
Hybrid Electric

scholarly journals Conceptual Advanced Transport Aircraft Design Configuration for Sustained Hypersonic Flight

Aerospace ◽  
2018 ◽  
Vol 5 (3) ◽  
pp. 91 ◽  
Author(s):  
Can Alkaya ◽  
Ashish Alex Sam ◽  
Apostolos Pesyridis
Keyword(s):  
Aircraft Design ◽  
Combined Cycle ◽  
Cfd Analysis ◽  
Conceptual Approach ◽  
Transport Aircraft ◽  
Hypersonic Flight ◽  
Hypersonic Aircraft ◽  
Conceptual Aircraft Design

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.

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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