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Lundström, David
Alternative names
Publications (10 of 25) Show all publications
Nepomuceno, L. M., Annes da Silva, R. G., Sobron, A., Krus, P. & Lundström, D. (2022). Estimation of lift characteristics of a subscale fighter using low-cost experimental methods. AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY, 94(8), 1379-1389
Open this publication in new window or tab >>Estimation of lift characteristics of a subscale fighter using low-cost experimental methods
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2022 (English)In: AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY, ISSN 1748-8842, Vol. 94, no 8, p. 1379-1389Article in journal (Refereed) Published
Abstract [en]

Purpose While computational methods are prevalent in aircraft conceptual design, recent advances in mechatronics and manufacturing are lowering the cost of practical experiments. Focussing on a relatively simple property, the lift curve, this study aims to increase understanding of how basic aerodynamic characteristics of a complex stealth configuration can be estimated experimentally using low-cost equipment, rapid prototyping methods and remotely piloted aircraft. Design/methodology/approach Lift curve estimates are obtained from a wind tunnel test of a three-dimensional-printed, 3.8%-scale model of a generic fighter and from flight testing a 14%-scale demonstrator using both a simple and a more advanced identification technique based on neural networks. These results are compared to a computational fluid dynamics study, a panel method and a straightforward, theoretical approach based on radical geometry simplifications. Findings Besides a good agreement in the linear region, discrepancies at high angles of attack reveal the shortcomings of each method. The remotely piloted model manages to provide consistent results beyond the physical limitations of the wind tunnel although it seems limited by instrumentation capabilities and unmodelled thrust effects. Practical implications Physical models can, even though low-cost experiments, expand the capabilities of other aerodynamic tools and contribute to reducing uncertainty when other estimations diverge. Originality/value This study highlights the limitations of commonly used aerodynamic methods and shows how low-cost prototyping and testing can complement or validate other estimations in the early study of a complex configuration.

Place, publisher, year, edition, pages
EMERALD GROUP PUBLISHING LTD, 2022
Keywords
Lift estimation; Subscale; Flight testing; Rapid prototyping; Unmanned aerial vehicle
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:liu:diva-184398 (URN)10.1108/AEAT-04-2021-0105 (DOI)000777885300001 ()
Note

Funding Agencies|CoordenacAo de Aperfeicoamento de Pessoal de Nivel SuperiorCoordenacao de Aperfeicoamento de Pessoal de Nivel Superior (CAPES) [001]; VINNOVA [MESTA]Vinnova [2017-01502]

Available from: 2022-04-20 Created: 2022-04-20 Last updated: 2023-05-04Bibliographically approved
Sobron, A., Lundström, D. & Krus, P. (2021). A Review of Current Research in Subscale Flight Testing and Analysis of Its Main Practical Challenges. Aerospace, 8(3), Article ID 74.
Open this publication in new window or tab >>A Review of Current Research in Subscale Flight Testing and Analysis of Its Main Practical Challenges
2021 (English)In: Aerospace, ISSN 2226-4310, Vol. 8, no 3, article id 74Article in journal (Refereed) Published
Abstract [en]

Testing of untethered subscale models, often referred to as subscale flight testing, has traditionally had a relatively minor, yet relevant use in aeronautical research and development. As recent advances in electronics, rapid prototyping and unmanned-vehicle technologies expand its capabilities and lower its cost, this experimental method is seeing growing interest across academia and the industry. However, subscale models cannot meet all similarity conditions required for simulating full-scale flight. This leads to a variety of approaches to scaling and to other alternative applications. Through a literature review and analysis of different scaling strategies, this study presents an overall picture of how subscale flight testing has been used in recent years and synthesises its main issues and practical limitations. Results show that, while the estimation of full-scale characteristics is still an interesting application within certain flight conditions, subscale models are progressively taking a broader role as low-cost technology-testing platforms with relaxed similarity constraints. Different approaches to tackle the identified practical challenges, implemented both by the authors and by other organisations, are discussed and evaluated through flight experiments.

Place, publisher, year, edition, pages
Basel, Switzerland: MDPI, 2021
Keywords
subscale flight testing, similarity, scale model, remotely piloted aircraft, demonstration, rapid prototyping
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:liu:diva-173294 (URN)10.3390/aerospace8030074 (DOI)000633221200001 ()
Note

Funding: Swedish Innovation Agency VINNOVA within project MESTA [NFFP 2017-01502]

Available from: 2021-02-12 Created: 2021-02-12 Last updated: 2021-05-05Bibliographically approved
Sobron, A., Lundström, D., Larsson, R., Krus, P. & Jouannet, C. (2018). Methods for efficient flight testing and modelling of remotely piloted aircraft within visual line-of-sight. In: The International Council of the Aeronautical Sciences (Ed.), Proceedings of the 31st Congress of The International Council of the Aeronautical Sciences (ICAS), September 9-14 2018, Belo Horizonte, Brazil.: . Paper presented at 31st Congress of The International Council of the Aeronautical Sciences (ICAS), September 9-14 2018, Belo Horizonte, Brazil.. Bohn: International Council of the Aeronautical Sciences
Open this publication in new window or tab >>Methods for efficient flight testing and modelling of remotely piloted aircraft within visual line-of-sight
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2018 (English)In: Proceedings of the 31st Congress of The International Council of the Aeronautical Sciences (ICAS), September 9-14 2018, Belo Horizonte, Brazil. / [ed] The International Council of the Aeronautical Sciences, Bohn: International Council of the Aeronautical Sciences , 2018Conference paper, Published paper (Refereed)
Abstract [en]

Remotely piloted scaled models not only serve as convenient low-risk flying test-beds but also can provide useful data and increase confidence in an eventual full-scale design. Nevertheless, performing advanced flight tests in a safe and cost-effective manner is often a challenge for organizations with limited resources. A typical scenario is testing within visual line-of-sight at very low altitude, a type of operation that offers major cost advantages at the expense of a reduced available airspace. This paper describes some of the authors' work towards efficient performance evaluation and system identification of fixed-wing, remotely piloted aircraft under these challenging conditions. Results show that certain techniques, manoeuvre automation, and platform-optimised multisine input signals can improve the flight test efficiency and the modelling process. It is also probable that some of the benefits observed here could be extrapolated to flight testing beyond visual line-of-sight or even to full-scale flight testing.

Place, publisher, year, edition, pages
Bohn: International Council of the Aeronautical Sciences, 2018
Keywords
flight testing, system identification, flight mechanics, modelling and simulation, RPAS
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:liu:diva-155052 (URN)2-s2.0-85060460933 (Scopus ID)978-3-932182-88-4 (ISBN)
Conference
31st Congress of The International Council of the Aeronautical Sciences (ICAS), September 9-14 2018, Belo Horizonte, Brazil.
Projects
MSDEMO
Available from: 2019-03-11 Created: 2019-03-11 Last updated: 2021-08-20Bibliographically approved
Jouannet, C., Lundström, D., Krus, P., Sobron, A., Annes da Silva, R. G., Catalano, F. & Greco, P. (2017). Aerodynamic database of a subscale demonstrator. In: 35th AIAA Applied Aerodynamics Conference: . Paper presented at 35th AIAA Applied Aerodynamics Conference, 5-9 June 2017, Denver, Colorado, USA. Reston, VA, USA, Article ID 2017-4075.
Open this publication in new window or tab >>Aerodynamic database of a subscale demonstrator
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2017 (English)In: 35th AIAA Applied Aerodynamics Conference, Reston, VA, USA, 2017, article id 2017-4075Conference paper, Published paper (Refereed)
Abstract [en]

This paper reports the current status of a joint Swedish-Brazilian research project aiming at exploring sub scale flight testing. A 13% scale fighter aircraft is used as a test bench for developing methods and procedures for data acquisition. This paper will present an aerodynamic database as a partial result of the collaborative project.

Place, publisher, year, edition, pages
Reston, VA, USA: , 2017
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:liu:diva-173295 (URN)10.2514/6.2017-4075 (DOI)
Conference
35th AIAA Applied Aerodynamics Conference, 5-9 June 2017, Denver, Colorado, USA
Available from: 2021-02-12 Created: 2021-02-12 Last updated: 2023-09-22Bibliographically approved
Sobron, A., Lundström, D., Krus, P., Jouannet, C. & Sandoval Goez, L. C. (2017). Flight test design for remotely-piloted aircraft in confined airspace. In: The Council of European Aerospace Societies (Ed.), 6th CEAS Air and Space Conference, Aerospace Europe, 16-20 October, 2017, Bucharest, Romania.: . Paper presented at 6th CEAS Air and Space Conference, Aerospace Europe, 16-20 October, 2017, Bucharest, Romania.. Brussels
Open this publication in new window or tab >>Flight test design for remotely-piloted aircraft in confined airspace
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2017 (English)In: 6th CEAS Air and Space Conference, Aerospace Europe, 16-20 October, 2017, Bucharest, Romania. / [ed] The Council of European Aerospace Societies, Brussels, 2017Conference paper, Published paper (Refereed)
Abstract [en]

Thispaper presents various techniques and procedures that aim to simplify flighttesting of fixed-wing, remotely-piloted aircraft with the purposes ofperformance evaluation and system identification. These methods have beenspecifically developed for flight within visual line-of-sight, a type ofoperation that limits the available airspace severely but offers major costadvantages considering the current regulations for unmanned flight in mostWestern countries.

Place, publisher, year, edition, pages
Brussels: , 2017
Keywords
flight testing, visual line-of-sight, UAS, data acquisition, flight dynamics
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:liu:diva-155054 (URN)
Conference
6th CEAS Air and Space Conference, Aerospace Europe, 16-20 October, 2017, Bucharest, Romania.
Projects
MSDEMO
Available from: 2019-03-11 Created: 2019-03-11 Last updated: 2019-03-22Bibliographically approved
Jouannet, C., Lundström, D., Melin, T. & Berry, P. (2013). Design and Flight Testing of a Solar Powered Aircraft, a Student Challenge. In: : . Paper presented at 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013; Grapevine, TX; United States. American Institute of Aeronautics and Astronautics
Open this publication in new window or tab >>Design and Flight Testing of a Solar Powered Aircraft, a Student Challenge
2013 (English)Conference paper, Published paper (Other academic)
Abstract [en]

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

Place, publisher, year, edition, pages
American Institute of Aeronautics and Astronautics, 2013
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:liu:diva-88324 (URN)10.2514/6.2013-942 (DOI)978-1-62410-181-6 (ISBN)
Conference
51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013; Grapevine, TX; United States
Available from: 2013-01-31 Created: 2013-01-31 Last updated: 2014-12-05
Lundström, D. (2012). Aircraft Design Automation and Subscale Testing: With Special Reference to Micro Air Vehicles. (Doctoral dissertation). Linköping: Linköping University Electronic Press
Open this publication in new window or tab >>Aircraft Design Automation and Subscale Testing: With Special Reference to Micro Air Vehicles
2012 (English)Doctoral thesis, comprehensive summary (Other academic)
Abstract [en]

This dissertation concerns how design automation as well as rapid prototyping and testing of subscale prototypes can support aircraft design. A framework for design automation has been developed and is applied specifically to Micro Air Vehicles (MAV). MAVs are an interesting area for design automation as they are an application where the entire design, from requirements to manufacturing, can indeed be automated. From a complexity point of view it can be considered to be similar to conceptual design of manned aircraft.

The created design optimization framework interfaces several software systems to generate MAVs to optimally fulfil specific mission requirements. The goal has been to find a method for MAV design and optimization from a holistic viewpoint, i.e. not a method for optimizing single subsystems, such as motor or propeller, but a method that embraces all disciplines of MAV design. Key drivers have been the use of off-the-shelf components wherever possible and to optimize the geometric shape not just from an aerodynamic perspective, but also to consider internal component placement and stability criteria. The optimization technique chosen is a multi-objective genetic algorithm. Finally, a novel method for direct digital manufacturing of MAVs is proposed.

The utility of the framework has been demonstrated with several case studies on MAV design. The propulsion system is identified as most influential on MAV performance and thus is where it is most important to have accurate models. For this reason the models used in the framework are experimentally validated. The influence of atmospheric winds and turbulence on MAV performance is also experimentally investigated

The subscale testing efforts are aimed at reducing cost and increasing the usability of flight testing with subscale vehicles. Data acquisition system design is described and low-cost testing methods are presented, such as car top testing or in-flight flow visualization. Two subscale flight projects are also presented.

Abstract [sv]

Den här avhandlingen handlar om hur konstruktionsprocessen av flygplan kan stödjas dels genom förbättrade analysverktyg, s.k.  konstruktionsautomation, och dels genom metoder för att snabbt och billigt kunna tillverka och testa nedskalade prototyper.

Konstruktion av flygplan är ett komplext område som innefattar många tätt sammanlänkade underdiscipliner. Ett lyckat flygplan är således en väl avvägd kompromiss mellan alla dessa discipliner. Dagens hårda konkurrens, krav på miljö, samt tekniska komplexitet ökar kraven på att framtidens flygplan måste vara bättre optimerade än idag. Traditionell flygplanskonstruktion kan ses som en sekventiell process där man stegvis förfinar konstruktionen en disciplin i taget. Med modern datorkraft och beräkningsprogram kan denna process delvis automatiseras varpå man på ett tidigare stadium kan ta hänsyn till fler discipliner. Många av de steg som tidigare genomförts sekventiellt kan nu göras parallellt. Det ökar möjligheten att nå en optimal konstruktion, samt minskar riskerna för att man tidigt bygger in fel i konstruktionen som är kostsamma att rätta till i ett senare skede. I den här avhandlingen beskrivs hur sådan konstruktionsautomation kan genomföras med hjälp av multidisciplinär optimering och en sammankoppling av ett flertal programvaror. Detta har speciellt applicerats på så kallade ”micro air vehicles” (MAV).

En MAV kan beskrivas som en luftfarkost av en sådan storlek att den enkelt kan bäras och skötas av en person. I princip ett flygplan i samma storleksklass som fåglar. I Sverige benämns dessa ofta som ”micro UAV”. Nyttan med MAVs är många sett både från ett militärt och civilt perspektiv. Typiska användningsområden är spaning/övervakning inom polis, militär och räddningsverksamhet, samt kartering, meterologi, gränsbevakning, jordbruksinventering etc. Den konstruktionsautomation som har utvecklats möjliggör att generera MAVs optimerade för givna prestandakrav och önskad nyttolast. I optimeringen så genereras den optimala skrovformen, val av framdrivningssystem, samt placering av interna komponenter. Slutligen så tillverkas den genererade farkosten genom en 3D skrivare. Avhandlingen lägger även vikt vid att experimentellt validera de beräkningar som ligger till grund för optimeringen.

Det andra spåret i avhandlingen behandlar ämnet konceptutvärdering genom nedskalade modeller. Att bygga och testa fysiska modeller är egentligen inget nytt inom flygkonstruktion. Avhandlingen visar dock hur man med modern teknik kan göra detta billigare än tidigare och samtidigt öka nyttan. Miniatyriseringen av elektronik gör att det idag går att utrusta radiostyrda demonstratorer med avancerade mätsystem varpå värdefull data kan insamlas. Vikten av att kunna testa fysiska prototyper ökar alltjämt som flygindustrin blir allt mer teoretisk. Tiden mellan olika flygplanskonstruktioner blir också längre, samt att behovet för nya radikala konstruktioner ökar för att möta de strama miljökraven. Att snabbt och billigt kunna utvärdera prototyper blir därför en allt viktigare del för att hålla kompetensen på en hög nivå. Avhandlingen behandlar skalning, konstruktionsmetoder, instrumentering och testning.

Place, publisher, year, edition, pages
Linköping: Linköping University Electronic Press, 2012. p. 100
Series
Linköping Studies in Science and Technology. Dissertations, ISSN 0345-7524 ; 1480
National Category
Engineering and Technology
Identifiers
urn:nbn:se:liu:diva-84673 (URN)978-91-7519-788-3 (ISBN)
Public defence
2012-11-23, ACAS, A huset, Campus Valla, Linköpings universitet, Linköping, 10:15 (English)
Opponent
Supervisors
Available from: 2012-10-17 Created: 2012-10-17 Last updated: 2019-12-10Bibliographically approved
Staack, I., Chaitanya Manjula, R., Berry, P., Melin, T., Amadori, K., Jouannet, C., . . . Krus, P. (2012). Parametric Aircraft Conceptual Design Space. In: Prceedings of the 28th International Congress of the Aeronautical Sciences. Paper presented at 28th Congress of the International Council of the Aeronautical Sciences (ICAS 2012), 23-28 September 2012, Brisbane, Australia.
Open this publication in new window or tab >>Parametric Aircraft Conceptual Design Space
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2012 (English)In: Prceedings of the 28th International Congress of the Aeronautical Sciences, 2012Conference paper, Oral presentation only (Other academic)
Abstract [en]

This paper presents the development of a design framework for the initial conceptual design phase. The focus in this project is on a flexible database in XML format, together with close integration of automated CAD, and other tools, which allows the developed geometry to be used directly in the subsequent preliminary design phase. The database and the geometry are also described and an overview is given of included tools like aerodynamic analysis and weight estimation.

Keywords
aircraft conceptual design, parametric modeling, sizing, XML database
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:liu:diva-86541 (URN)
Conference
28th Congress of the International Council of the Aeronautical Sciences (ICAS 2012), 23-28 September 2012, Brisbane, Australia
Available from: 2013-01-15 Created: 2012-12-18 Last updated: 2015-06-02Bibliographically approved
Jouannet, C., Berry, P., Melin, T., Amadori, K., Lundström, D. & Staack, I. (2012). Subscale flight testing used in conceptual design. AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY, 84(3), 192-199
Open this publication in new window or tab >>Subscale flight testing used in conceptual design
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2012 (English)In: AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY, ISSN 1748-8842, Vol. 84, no 3, p. 192-199Article in journal (Refereed) Published
Abstract [en]

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 Board (FMV) on a Generic Future Fighter aircraft. The paper will cover different aspects of the performed work: from paper study realised by SAAB to the first flight of the scaled demonstrator. The intention of the paper is to describe what has been realised and explain how the work is may be used to fit within aircraft conceptual design. Design/methodology/approach - The approach has been to address the challenges proposed by the customer of the demonstrator, how to design, manufacture and operate a scaled demonstrator of an aircraft study in conceptual design within five months. Similar research projects have been reviewed in order to perform the current work. Findings - The results obtained so far have led to new questions. In particular, the project indicated that more research is needed within the area of subscale flight testing for usage in aircraft conceptual design, since a scaled demonstrator is likely to answer some questions but will probably open up new ones. Research limitations/implications - The current research is just in its infancy and does not bring any final conclusion but does, however, offer several guidelines for future works. Since the aircraft study was an early phase concept study, not much data are available for validation or comparison. Therefore, the paper is not presenting new methods or general conclusions. Practical implications - Results from a conceptual aircraft study and a realisation of a scaled prototype are presented, which show that scaled flight testing may be used with some restriction in conceptual design. Originality/value - The value of this paper is to show that universities can be involved in prototype development and can work in close collaboration with industries to address issues and solutions within aircraft conceptual design.

Place, publisher, year, edition, pages
EMERALD GROUP PUBLISHING LIMITED, 2012
Keywords
Aircraft; Design; Aerodynamics; Subscale flight testing; Conceptual design; Prototype; Demonstrator
National Category
Engineering and Technology
Identifiers
urn:nbn:se:liu:diva-79714 (URN)10.1108/00022661211222058 (DOI)000305871700008 ()
Available from: 2012-08-13 Created: 2012-08-13 Last updated: 2012-10-17Bibliographically approved
Lundström, D. & Krus, P. (2012). Testing of Atmospheric Turbulence Effects on the Performance of Micro Air Vehicles. INTERNATIONAL JOURNAL OF MICRO AIR VEHICLES, 4(2), 133-149
Open this publication in new window or tab >>Testing of Atmospheric Turbulence Effects on the Performance of Micro Air Vehicles
2012 (English)In: INTERNATIONAL JOURNAL OF MICRO AIR VEHICLES, ISSN 1756-8293, Vol. 4, no 2, p. 133-149Article in journal (Refereed) Published
Abstract [en]

Micro Air Vehicles (MAV) are generally operated at low altitudes and within the earth boundary layer. This is a very dynamic environment with varying wind intensity and turbulence levels far greater than those experienced by traditional manned aircraft cruising at higher altitudes. Yet aerodynamic research on MAVs is often based on the assumption of steady aerodynamics. Little effort has been made to experimentally determine the validity of this assumption. In this paper, the effect of turbulence on the performance of a MAV is studied using flight testing in different wind conditions. Flight testing technique, data logging equipment and data reduction are explained. Additionally, a low cost technique for propeller performance measurement is presented. Results show that the flow around a MAV flying in windy conditions qualifies as highly unsteady, although the impact on its performance is surprisingly small for the kind of turbulence levels at which MAVs can be expected to operate. Accelerometer data from the flights reveals that if steady aerodynamic theory is assumed, increasing turbulence should have resulted in a measurable drag increase, thus indicating that the tested MAV to some extent passively manages to benefit from the turbulence.

Place, publisher, year, edition, pages
Multi-Science Publishing, 2012
National Category
Engineering and Technology
Identifiers
urn:nbn:se:liu:diva-81837 (URN)10.1260/1756-8293.4.2.133 (DOI)000307637400003 ()
Available from: 2012-09-25 Created: 2012-09-24 Last updated: 2012-10-17
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