Patrick Berry

The Sunriser - A Design Study in Solar Powered Flight

The design task for last year students in Aircraft Design at Linkoping University was to design a manned solar-powered aircraft. The mission was to survey the U.S./Mexican borderline in search for ...

Exploring Parametric CAD-models in Aircraft Conceptual Design

The ever fast growing information technology is enabling the re-definition of early stages of aircraft design which have been restricted mostly by statistical and empirical approaches because of lengthy and costly simulation times. This paper will describe a methodology based on parametric and generic CAD modeling methods which will save time when performing repetitive tasks automatically. Furthermore, it enables greater comprehension by giving a holistic view of the aircraft systems because of the proposed multidisciplinary and modular framework. The framework involves a centralized easy to use interface which is coupled to a series of analyses tools. The proposed methods have been applied in student projects of the course “Aircraft Conceptual Design” from Linkoping University where it has shown great promises.

Subscale flight testing used in conceptual design

Purpose - The purpose of this paper is to present the latest subscale demonstrator aircraft developed at Linkoping University. It has been built as part of a study initiated by the Swedish Material ...

Design and Flight Testing of an ECO-Sport Aircraft

The presented work is centered on different concept studies for “greener” sport aircraft. The goal is to show the possibility to manufacture a sport aircraft based on different environmental friendly propulsion systems. A first theoretical part consists of creating a sizing program for studying different concepts. Then the gathered knowledge will result in the realization of two flying down-scaled demonstrators. This study was realized during a student project over a 5 month period.

Analytical weight estimation of landing gear designs

Landing gear weight calculations can be carried out using statistical or analytical methods. Statistical methods were used in the past and offered quick group weights. However, they are not capable of computing accurately the weight of landing gears, which have special geometries and performance. In this work, landing gear weight is computed using analytical methods based on parametric 3D models. The procedure established by Kraus and Wille is applied as a baseline so as to create a procedure capable of dealing with landing gear weight calculations. This method is designed to be as flexible as possible, giving the user the freedom to modify many options and parameters and integrate landing gear design into Robust Aircraft Parametric Interactive Design.

Conceptual Design of a New Generation JAS 39 Gripen Aircraft

This paper describes the conceptual phase of a modification proposal for Saab Gripen, which aims to create the best possible basis for future aircraft development. One of the main tasks in this res ...

Aircraft Design Education at Linköpings University

Abstract Aircraft design is a complex multi-disciplinary task and teaching can easily tend to be too theoretical, not providing the students the tools they need to successfully participate in industrial projects. The approach chosen at Linköping University is intended to create the right balance between theory and practice, and to place the student in the centre of the problem, in order to achieve an overall perspective of the aircraft design process. This article presents in brief layout of the courses, and in more detail, the aircraft design project course given in the last year of the aeronautical masters program, where flying hardware is designed and build, in response to a design challenge.

Knowledge-based Integrated Wing Automation and Optimization for Conceptual Design

Contemporary aircraft design and development incurs high costs and consumes a lot of time for research and implementation. To minimize the development cost, an improvement of the conceptual design phase is desirable. A framework to support the initial design space exploration and conceptual design phase is presently being developed at Linkoping University. In the aircraft design, the geometry carries a critical, discriminating role since it stores a significant part of the information and the data needed for most investigations. Methodology for design automation of a wing with a detailed description such that the geometry is effectively propagated for further analysis is presented in this paper. Initial weight estimation of the wing is performed by combining the weight penalty method with a sophisticated CAD model. This wing model is used for airfoil shape optimization and later for structural optimization. A methodology for automatic meshing of the geometry for CFD and FEM when the surfaces increase or decrease during the design automation is proposed. The framework combining automation capability with shape and structural optimization will enhance the early design phases of aircraft conceptual design.

Design and Flight Testing of a Solar Powered Aircraft, a Student Challenge.

The presented work considers designing, building and flight testing a solar poweraircraft as a student project. The goal is to allow student to participate in an aircraft projectfrom design to flight test in order to acquire aircraft design knowledge from theoretical andpractical means. A first theoretical part consists of creating a sizing program for studyingdifferent concepts. Then the gathered knowledge will result in the realization of a flyingdemonstrator. This was realized during a student project over a 5 month period