Publications
131 results found
Zang C, Schwingshackl CW, Ewins DJ, 2008, Model validation for structural dynamic analysis: An approach to the Sandia structural dynamics challenge, Validation Methodology Workshop, Publisher: ELSEVIER SCIENCE SA, Pages: 2645-2659, ISSN: 0045-7825
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- Citations: 25
Schwingshackl CW, Zang C, Massei L, et al., 2008, The Simulation of a Full-field Vibration Measurement of Cylindrical Structures Using a Continuous Scanning LDV Technique, 8th International Conference on Vibration Measurements by Laser Techniques, Publisher: SPIE-INT SOC OPTICAL ENGINEERING, ISSN: 0277-786X
Zang C, Schwingshackl C, Ewins DJ, 2008, Error localization in an FE model in model updating process using supermodels, International Conference on Noise and Vibration Engineering, Publisher: KATHOLIEKE UNIV LEUVEN, DEPT WERKTUIGKUNDE, Pages: 1923-1936
Zang C, Schwingshackl C, Ewins DJ, 2007, Supermodel validation for structural dynamic analysis of aero-engine components, ISSN: 2191-5644
This paper discusses validation for aero-engine components using supermodel. A supermodel is a very detailed solid finite element model. It is usually created with a much finer mesh and can be considered to be capable of reliably representing all geometric features such as holes, flanges, fillets of the actual structure, and its dynamic properties, i.e. the natural frequencies and mode shapes. Therefore, information provided from a supermodel can be treated as a trusted source of reference which, to some extent, closely represents the experimental data measured on a component and can be employed in virtual experiments, where the boundary conditions can easily be controlled to simulate the response behaviour. It would obviously be advantageous to help to construct and update the design model in the early stage of design process in order to massively reduce the design process cycles if such an approach was itself proven to be effective. However, the concept of 'supermodel' requires itself to be validated before it can be used in the validation of aero-engine models in the design process in the aeronautics industry. This paper explores the feasibility of creating supermodels for aero-engine components and the reliability of replacing test data by the information from supermodels in model validation. An intermediate casing, which is a complex component in a whole engine model, and a Combustor Outer Casing (COC) are used as examples to demonstrate that dynamic properties of supermodels are capable of closely representing those of the actual structures. Criteria and guidelines for the creation of 'supermodels' that have the capability of producing reliable reference data to replace practical testing of prototypes of aero-engine components are also discussed.
Schwingshackl CW, Stanbridge AB, Zang C, et al., 2007, Full-field vibration measurement of cylindrical structures using a Continuous Scanning LDV technique, ISSN: 2191-5644
A major motivation for structural vibration testing is the need of high - quality measurement data for finite element (FE) model validation. The ever increasing accuracy of FE models thereby challenges the measurement techniques to provide higher data resolution for a successful model validation. The full-field technique of a Continuous Scanning Laser Doppler Vibrometer (CSLDV) is an excellent source for such high resolution data. A major drawback of the method is its restricted field of view when applied to cylindrical or conical structures. A method to overcome these limitations is presented which provides high resolution 360° area coverage for a hollow cylindrical structure. A 'lighthouse'-like CSLDV system is used to measure the operating deflection shape (ODS) of the inner surface of a cylindrical component. Signal demodulation techniques are applied for a high resolution ODS, allowing for the identification of and allowance for discontinuities such as holes in the structure.
Aglietti GS, Schwingshackl CW, Roberts SC, 2007, Multifunctional structure technologies for satellite applications, Shock and Vibration Digest, Vol: 39, Pages: 381-391, ISSN: 0583-1024
Conventional spacecraft subsystems are designed and manufactured separately, and are integrated only during the final stages of satellite development. This requires containers for the subsystems' hardware, mechanical interfaces, panels, frames, bulky wire harnesses, etc., which add considerable mass and volume. As all subsystems are generally secured to the structure, the multifunctional structure approach aims at merging these elements into the structure, so that the structure also carries out some of the typical functions of the subsystems (e.g. electrical energy storage). The main advantages are as follows: (i) removal of the bolted mechanical interfaces and most of the subsystems' containers; (ii) reduction of the satellite structure mass, as the strength of the parts of the subsystem imbedded into the structure are exploited, and substitute purely structural parts; (iii) reduction of the overall satellite volume, as elements such as battery packs or electronic harnesses can be built into the structure's volume. There are still issues that need to be addressed to allow a wider utilization of multifunctional structures. However, the development of concurrent engineering approaches, to carry out an integrated design of the spacecraft, together with advances in the subsystems' disciplines, will help to promote the further diffusion of multifunctional structures. © 2007 SAGE Pulications.
Schwingshackl CW, Aglietti GS, Cunningham PR, 2007, Experimental determination of the dynamic behavior of a multifunctional power structure, AIAA JOURNAL, Vol: 45, Pages: 491-496, ISSN: 0001-1452
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- Citations: 13
Schwingshackl CW, Aglietti GS, Cunningham PR, 2006, The dynamic behaviour of mulifunctional power strucutres, Pages: 5266-5275
New design approaches will be required to increase the payload to mass fraction for future satellite generations. The multifunctional design concept, where spacecraft subsystems are integrated into the load bearing structure of the satellite, is one considered technology. This paper describes the design, analysis and manufacture of a particular multifunctional power structure with a special focus on its dynamic response. An analytical and a finite element analysis of ten proposed multifunctional power structures, based on a sandwich panel configuration, are presented. The theoretical out-of-plane material properties for the investigated designs are derived with the help of the virtual displacement method. These theoretical properties are compared to finite element models and subsequently used in a parameter optimisation of the dynamic response of the ten introduced sandwich panels. The optimisation allows the identification of the most favourable multifunctional power structure. The experimental dynamic response of a manufactured multifunctional power panel is presented and compared to a conventional honeycomb panel for a successful evaluation of the introduced multifunctional approach. The results of this work show the ability of the presented multifunctional design to successfully combine the structural and power storage functions which makes the multifunctional power structure an excellent design approach for future space missions.
Schwingshackl CW, Aglietti GS, Cunningham PR, 2006, Parameter optimization of the dynamic behavior of inhomogeneous multifunctional power structures, AIAA JOURNAL, Vol: 44, Pages: 2286-2294, ISSN: 0001-1452
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- Citations: 12
Schwingshackl CW, Aglietti GS, Cunningham PR, 2006, Determination of honeycomb material properties: Existing theories and an alternative dynamic approach, JOURNAL OF AEROSPACE ENGINEERING, Vol: 19, Pages: 177-183, ISSN: 0893-1321
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- Citations: 61
Schwingshackl CW, Cunningham PR, Aglietti GS, 2005, Honeycomb elastic material properties: A review of some existing theories and a new dynamic approach, International Conference on Modal Analysis, Noise and Vibration Engineering, Publisher: KATHOLIEKE UNIV LEUVEN, DEPT WERKTUIGKUNDE, Pages: 1353-1366
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