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Staack, Ingo
Publications (10 of 12) Show all publications
Munjulury, R. C., Staack, I., Berry, P. & Krus, P. (2016). A knowledge-based integrated aircraft conceptual design framework. CEAS Aeronautical Journal, 7(1), 95-105
Open this publication in new window or tab >>A knowledge-based integrated aircraft conceptual design framework
2016 (English)In: CEAS Aeronautical Journal, ISSN 1869-5582, 1869-5590, Vol. 7, no 1, p. 95-105Article in journal (Refereed) Published
Abstract [en]

"The conceptual design is the early stage of aircraft design process where results are needed fast, both analytically and visually so that the design can be analyzed and eventually improved in the initial phases. Although there is no necessity for a CAD model from the very beginning of the design process, it can be an added advantage to have the model to get the impression and appearance. Furthermore, this means that a seamless transition into preliminary design is achieved since the CAD model can guardedly be made more detailed. For this purpose, knowledge-based aircraft conceptual design applications Tango (Matlab) and RAPID (CATIA) are being developed at Linköping University. Based on a parametric data definition in XML, this approach allows for a full 3D CAD integration. The one-database approach, also explored by many research organizations, enables the flexible and efficient integration of the different multidisciplinary processes during the whole conceptual design phase. This paper describes the knowledge-based design automated methodology of RAPID, data processing between RAPID and Tango and its application in the courses ‘‘Aircraft conceptual design’’ and ‘‘Aircraft project course’’ at Linköping University. A multifaceted user interface is developed to assist the whole design process."

Place, publisher, year, edition, pages
Springer, 2016
Keywords
Aircraft conceptual design, Knowledge based, XML database
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:liu:diva-126689 (URN)10.1007/s13272-015-0174-z (DOI)
Projects
NFFP5/NFFP6
Available from: 2016-04-01 Created: 2016-04-01 Last updated: 2018-02-07
Staack, I., Chaitanya Munjulury, R., Melin, T., Abdalla, A. M. & Krus, P. (2014). CONCEPTUAL AIRCRAFT DESIGN MODEL MANAGEMENTDEMONSTRATED ON A 4TH GENERATION FIGHTER. In: : . Paper presented at 29th Congress of the International Council of the Aeronautical Sciences. St. Petersberg, Russia
Open this publication in new window or tab >>CONCEPTUAL AIRCRAFT DESIGN MODEL MANAGEMENTDEMONSTRATED ON A 4TH GENERATION FIGHTER
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2014 (English)Conference paper, Published paper (Refereed)
Abstract [en]

Model management during conceptual aircraftdesign is an important issue. This paper showsthe basic ideas and capabilities of the conceptualaircraft design framework developed atLinköping University with focus on efficient lowfidelity geometry definition. As an example, theanalysis of an F-16 fighter is presented.

Place, publisher, year, edition, pages
St. Petersberg, Russia: , 2014
Keywords
model management, conceptual aircraft design, sensitivity analysis
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:liu:diva-114909 (URN)
Conference
29th Congress of the International Council of the Aeronautical Sciences
Available from: 2015-03-05 Created: 2015-03-05 Last updated: 2015-03-20
Munjulury, R. C., Staack, I., Abdalla, A. M., Melin, T., Jouannet, C. & Krus, P. (2014). Knowledge-based design for future combat aircraft concepts. In: : . Paper presented at 29th Congress of the International Council of the Aeronautical Sciences, St. Petersburg, Russia. St. Peterberg
Open this publication in new window or tab >>Knowledge-based design for future combat aircraft concepts
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2014 (English)Conference paper, Published paper (Refereed)
Abstract [en]

A new fighter aircraft will most likely be acollaborative project. In this study conceptualknowledge-based design is demonstrated, usingmodels of comparable fidelity for sizing, geometrydesign, aerodynamic analysis and system simulationfor aircraft conceptual design. A newgeneration fighter is likely to involve advancedcontrol concept where an assessment of feasibilitythrough simulation is needed already atthe conceptual stage. This co-design leads to adeeper understanding of the trade-offs involved.In this paper a study for a future combat aircraftis made. Conceptual knowledge-based design isdemonstrated by optimizing for a design mission,including a super-cruise segment.

Place, publisher, year, edition, pages
St. Peterberg: , 2014
Keywords
Conceptual design, Aircraft design, Engine design, Knowledge-based
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:liu:diva-114902 (URN)
Conference
29th Congress of the International Council of the Aeronautical Sciences, St. Petersburg, Russia
Projects
NFFP5/NFFP6
Available from: 2015-03-05 Created: 2015-03-05 Last updated: 2017-05-30Bibliographically approved
Scholz, D., Seresinhe, R., Staack, I. & Lawson, C. (2013). Fuel Consumption Due to Shaft Power Off-takes from The Engine. In: Frank Thielecke (Ed.), Proceedings of the 4th International Workshop on Aircraft System Technologies: . Paper presented at 4th International Workshop on Aircraft System Technologies (AST 2013), 23-24 April 2013, Hamburg, Germany (pp. 169-179). Aachen: Shaker Verlag
Open this publication in new window or tab >>Fuel Consumption Due to Shaft Power Off-takes from The Engine
2013 (English)In: Proceedings of the 4th International Workshop on Aircraft System Technologies / [ed] Frank Thielecke, Aachen: Shaker Verlag, 2013, p. 169-179Conference paper, Published paper (Other academic)
Abstract [en]

This paper looks at fuel consumption due to shaft power off-takes from the engine and the related increase in the aircraft’s fuel consumption. It presents a review and comparison of published and unpublished data on this kind of consumption. The paper presents results from the TURBOMATCH engine simulation model, calibrated to real world engine data. A generic equation is derived for the calculation of fuel consumption due to shaft power extraction. Main result is the shaft power factor kP found to be in the order of 0.002 N/W for a typical cruise flight. This yields an amazingly high efficiency for power generation by shaft power extraction from a turbo fan engine of more than 70 %.

Place, publisher, year, edition, pages
Aachen: Shaker Verlag, 2013
Keywords
engine propulsion, efficiency, shaft power off-takes, thrust specific fuel consumption
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:liu:diva-103200 (URN)978-3-8440-1850-9 (ISBN)
Conference
4th International Workshop on Aircraft System Technologies (AST 2013), 23-24 April 2013, Hamburg, Germany
Available from: 2014-01-15 Created: 2014-01-15 Last updated: 2014-02-12Bibliographically approved
Munjulury, V. R., Staack, I. & Krus, P. (2013). Integrated Aircraft Design Network. In: Tomas Melin, Petter Krus, Emil Vinterhav, Knut Övrebo (Ed.), CEAS 2013 The International Conference of the European Aerospace Societies: 4:th CEAS conference, 2013. Paper presented at CEAS 2013 - International Conference of the European Aerospace Societies, 16-19 September 2013, Linköping, Sweden (pp. 263-269). Linköping
Open this publication in new window or tab >>Integrated Aircraft Design Network
2013 (English)In: CEAS 2013 The International Conference of the European Aerospace Societies: 4:th CEAS conference, 2013 / [ed] Tomas Melin, Petter Krus, Emil Vinterhav, Knut Övrebo, Linköping, 2013, p. 263-269Conference paper, Published paper (Refereed)
Abstract [en]

This paper describes the XML basedmultidisciplinary tool integration in aconceptual aircraft design framework,developed by the Division of Fluid andMechatronic Systems (FluMeS), LinköpingUniversity. Based on a parametric datadefinition in XML, this approach allows for afull 3D CAD integration. The one-databaseapproach, also conducted by many researchorganizations, enables the flexible and efficientintegration of the different multidisciplinaryprocesses during the whole conceptual designphase. This central database approach with adetailed explanation of the developed geometrydescription and the data processing, focusing onthe CAD integration is presented. Applicationexamples of the framework are presentedshowing the data build up and data handling.

Place, publisher, year, edition, pages
Linköping: , 2013
Keywords
aircraft conceptual design, parametric modeling, Knowledge based, sizing, XML database
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:liu:diva-103178 (URN)978-91-7519-519-3 (ISBN)
Conference
CEAS 2013 - International Conference of the European Aerospace Societies, 16-19 September 2013, Linköping, Sweden
Available from: 2014-01-14 Created: 2014-01-14 Last updated: 2014-05-27Bibliographically approved
Staack, I. & Krus, P. (2013). Integration of On-Board Power Systems Simulation in Conceptual Aircraft Design. In: Tomas Melin, Petter Krus,Emil Vinterhav, Knut Övrebö (Ed.), Proceedings of the 4th CEAS Conference in Linköping: . Paper presented at 4th European Air & Space Conference (CEAS 2013), 16-19 September 2013, Linköping, Sweden (pp. 709-718). Linköping, Sweden: Linköping University Electronic Press
Open this publication in new window or tab >>Integration of On-Board Power Systems Simulation in Conceptual Aircraft Design
2013 (English)In: Proceedings of the 4th CEAS Conference in Linköping / [ed] Tomas Melin, Petter Krus,Emil Vinterhav, Knut Övrebö, Linköping, Sweden: Linköping University Electronic Press, 2013, p. 709-718Conference paper, Published paper (Other academic)
Abstract [en]

This paper describes the methodology of generating simulation models out of basic information, available during conceptual design phase. The implementation of an aircraft system is shown as an example using the simulation software HOPSAN.

Because of the limited direct project-related data available at the conceptual stage, the traditional method of creating physical simulation models by the bottom up approach with the help of (standard) component libraries is not applicable. Instead, the respective systems’ architecture as well as their composition has to be descriptively predefined in a flexible, wide-range applicable manner, known as the knowledge base (KB) approach. These system technology driven design declarations – combined with project related data – result in roughly pre-tuned system simulation models, which may help when conducting more detailed investigations of the project such as performance analysis.

This (system architecture) knowledge-based approach is shown on the whole aircraft system level down to the detailed implementation of the control surface actuator systems of the primary flight control system.

Place, publisher, year, edition, pages
Linköping, Sweden: Linköping University Electronic Press, 2013
Keywords
Conceptual aircraft design, system simulation, onboard power systems, knowledge based engineering
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:liu:diva-103197 (URN)78-91-7519-519-3 (ISBN)
Conference
4th European Air & Space Conference (CEAS 2013), 16-19 September 2013, Linköping, Sweden
Funder
Vinnova, NFFP5
Available from: 2014-01-15 Created: 2014-01-15 Last updated: 2014-02-12Bibliographically approved
Amadori, K., Melin, T., Staack, I. & Krus, P. (2013). Multidisciplinary Optimization of Wing Structure Using Parametric Models. In: : . Paper presented at 51st AIAA Aerospace Sciences Meeting, 7-10 January 2013, Grapevine, Texas.
Open this publication in new window or tab >>Multidisciplinary Optimization of Wing Structure Using Parametric Models
2013 (English)Conference paper, Published paper (Other academic)
Abstract [en]

Aircraft design is an inherently multidisciplinary activity that requires integrating different models and tools to reach a well-balanced and optimized product. At Linköping University a design framework is being developed to support the initial design space exploration and the conceptual design phase. Main characteristics of the framework are its flexible database in XML format, together with close integration of automated CAD and other tools, which allows the developed geometry to be directly used in the subsequent preliminary design phase. In particular, the aim of the proposed work is to test the framework by designing, optimizing and studying a transport aircraft wing with respect to aerodynamic, geometry, structural and accessability constraints. The project will provide an initial assessment of the capability of the framework, both in terms of processing speed and accuracy of the results.

National Category
Aerospace Engineering
Identifiers
urn:nbn:se:liu:diva-88322 (URN)10.2514/6.2013-140 (DOI)978-1-62410-181-6 (ISBN)
Conference
51st AIAA Aerospace Sciences Meeting, 7-10 January 2013, Grapevine, Texas
Projects
NFFP5
Available from: 2013-01-31 Created: 2013-01-31 Last updated: 2014-12-04Bibliographically approved
Staack, I., Ellström, H., Bergman, M., Sarwe, P. & Krus, P. (2012). More  electrical environmental control system simulation. In: Proceedings 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. Brisbane: ICAS
Open this publication in new window or tab >>More  electrical environmental control system simulation
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2012 (English)In: Proceedings of the 28th  International Congress of the Aeronautical Sciences, Brisbane: ICAS , 2012Conference paper, Oral presentation only (Other academic)
Abstract [en]

This paper describes the development of a scalable simulation model of a bleed-less, fully electric Environmental Control System (ECS). The focus during development of the model was on fast execution speed and system architecture in order to enable optimization algorithms for system efficiency optimization to be constructed. Classical sensitivity and robustness analysis were used during model development. ECS architecture functionality and reliability has been proven for different flight mission working conditions as well as different failure modes. For this purpose, an analysis tool related to the simulation model and active simulation model control was developed.

Place, publisher, year, edition, pages
Brisbane: ICAS, 2012
Keywords
environmental control system, scalable model, sensitivity analysis
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:liu:diva-87268 (URN)
Conference
28th Congress of the International Council of the Aeronautical Sciences (ICAS 2012), 23-28 September 2012, Brisbane, Australia
Projects
NFFP5
Funder
Vinnova
Available from: 2013-01-15 Created: 2013-01-15 Last updated: 2013-01-29
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
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