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  • 1.
    Borglund, Dan
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    A case study of peer learning in higher aeronautical education2007In: European Journal of Engineering Education, ISSN 0304-3797, E-ISSN 1469-5898, Vol. 32, no 1, p. 35-42Article in journal (Refereed)
    Abstract [en]

    In order to improve student learning in an advanced course in aeronautics, lectures are replaced with more student-centred sessions based on peer learning. The course is organised in student teams, with the main task of delivering lecture requests for full class discussions. For the same reason, the written theory exam is replaced by a peer review of student reports. The new approach is found to result in a substantial increase of student–student and student–teacher interaction, leading to observable improvements in the course results. Finally, some feedback from the students is presented, being in great favour of the peer learning approach.

  • 2.
    Borglund, Dan
    KTH, Superseded Departments, Aeronautical Engineering.
    Active nozzle control and integrated design optimization of a beam subject to fluid-dynamic forces.1999In: Journal of Fluids and Structures, ISSN 0889-9746, E-ISSN 1095-8622, Vol. 13, no 2, p. 269-287Article in journal (Refereed)
    Abstract [en]

    Active nozzle control is used to improve the stability of a beam subject to forces induced by fluid flow through attached pipes. The control system has a significant effect on the structural stability, making both flutter and divergence type of instabilities possible. The stability analysis is carried out using a state-variable approach based on a finite element formulation of the structural dynamics. The simultaneous design of the control system and the beam shape minimizing structural mass is performed using numerical optimization. The inclusion of the control system in the optimization gives a considerable reduction of the structural mass but results in an optimal design which is very sensitive to imperfections. Using a simple model of the control system uncertainties, a more robust design is obtained by solving a modified optimization problem. Throughout the study, the theoretical findings are verified by experiments.

  • 3.
    Borglund, Dan
    KTH, Superseded Departments, Aeronautical Engineering.
    Aeroservoelastic design optimization with experimental verification2001In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, Vol. 38, no 5, p. 958-961Article in journal (Refereed)
    Abstract [en]

    A demonstration of integrated design optimization of an aeroservoelastic system was presented. It was shown that the simultaneous design of structural and control system required a two-step procedure to result in a minimum weight design and a control law that is well-designed for all operating conditions. The essential dynamics was predicted using a aeroservoelastic model, and final design with 42% less weight penalty was obtained using the integrated approach.

  • 4.
    Borglund, Dan
    KTH, Superseded Departments, Aeronautical Engineering.
    Control and optimization of pipes conveying fluid1998Licentiate thesis, comprehensive summary (Other scientific)
  • 5.
    Borglund, Dan
    KTH, Superseded Departments, Aeronautical Engineering.
    Control and optimization of structures with fluid interaction2000Doctoral thesis, comprehensive summary (Other scientific)
    Abstract [en]

    Various problems on the optimal design of elastic structures subject to nonconservative fluid-dynamic forces are considered. The optimal design problem istypically posed as minimizing structural weight subject to constraints on structural stability. Traditionally, structural dimensions and orientations of fibercomposite materials are common design variables. It is demonstrated that the structural weight can be reduced further by including the design of a stabilizingcontrol system in the structural design optimization, giving an integrated optimization problem where both structural and control system parameters are used as design variables. The integrated approach may result in a design with significantly improved performance compared to traditional methods, both in terms of reduced structural weight and control system performance. Using optimization for design of mechanical systems with nonconservative external load tends to increase the likelihood of obtaining a design which is very sensitive to imperfections. As a result, the predicted performance of the optimal design may not be achieved in practice. The importance of this fundamental difficulty is emphasized throughout the thesis by comparing numerically obtained results to experiments.

    The first part of the thesis is concerned with the stability and optimal design of a beam subject to forces induced by fluid flow through attached pipes. A nozzle control system deflecting the fluid jet at the beam tip is used to improve the stability of the system. The simultaneous design of the control system and the beam shape minimizing structural mass is performed using numerical optimization. The inclusion of the control system in the optimization gives a considerable reduction of the beam weight but results in an optimal design which is very sensitive to imperfections. An optimal design with improved robustness is obtained by solving a modified optimization problem. The stability of a flexible wing structure with a controllable trailing edge flap is investigated. Due to uncertainties in the numerical stability analysis, the wing is predicted to become unstable at a significantly higher speed than what is observed in wind tunnel tests. Two different approaches to stabilize the wing in flutter is demonstrated. First, numerical optimization is used to design a controller which at each flow speed maximizes the damping of the flutter mode observed in the wind tunnel experiment. Second, an integrated approach is adopted, where a simultaneous mass balancing and control law design is performed. It is argued that a two-step procedure may be required to obtain a design with minimum weight and a control law that is well-defined for all operating conditions.

  • 6.
    Borglund, Dan
    KTH, Superseded Departments, Aeronautical Engineering.
    On the optimal design of pipes conveying fluid.1998In: Journal of Fluids and Structures, ISSN 0889-9746, E-ISSN 1095-8622, Vol. 12, no 3, p. 353-365Article in journal (Refereed)
    Abstract [en]

    The stability and optimal design of a beam subject to forces induced by fluid flow through attached pipes is investigated. The structure is assumed to have the same dynamics as a fluid-conveying pipe, and the dynamic stability is analysed using a finite element formulation of the linear equation of motion. The optimal design problem of minimizing the structural mass at fixed critical flow speed is solved. The numerical results are compared to experiments with satisfactory agreement, provided that the lower bounds of the beam dimensions are properly chosen. The influence of structural damping on the critical flow speed is significant, and is found to be strongly design-dependent.

  • 7.
    Borglund, Dan
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
    Robust Aeroelastic Analysis in the Laplace Domain: The μ-p Method2007In: IFASD 2007: International Forum on Aeroelasticity and Structural Dynamics, 2007Conference paper (Other academic)
    Abstract [en]

    In this work the so-called μ-k method for robust flutter analysis is generalized to theLaplace domain. Although the generalization as such is a straightforward matter, the resultingμ-p method is far more versatile than the previous formulation. With the new method, a singlestructured singular value (or μ) evaluation can be used to determine if a certain eigenvalue p is asolution to the uncertain flutter equation or not. This result makes it possible to compute regionsof feasible eigenvalues in the complex plane, as well as extreme eigenvalues that can be used topredict damping bounds and perform robust flutter analysis. The capability to predict dampingbounds at any flight condition is a very attractive feature of the μ-p method, as flight testing israrely taken to the flutter point. This feature also makes it possible to estimate the magnitude ofthe uncertainty based on the measured frequency and/or damping of a particular mode, whichcan reduce the potential conservativeness of the robust analysis. Finally, the capabilities of thenew method is demonstrated by applying it to a low-speed wind tunnel model.

  • 8.
    Borglund, Dan
    KTH, Superseded Departments, Aeronautical and Vehicle Engineering.
    Robust aeroelastic stability analysis considering frequency-domain aerodynamic uncertainty2003In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, Vol. 40, no 1, p. 189-193Article in journal (Refereed)
    Abstract [en]

    The problem of modeling frequency-domain aerodynamic uncertainty for a slender wing structure is investigated. Based on an unsteady lifting-line theory used for the generalized aerodynamic forces, a quite versatile uncertainty description with a clear physical interpretation is proposed. The uncertainty description is easily put in a form suitable for application of the mu framework in robust linear control. Because only frequency response matrices are required for the mu computations, the proposed uncertainty description can be used for robust stability and performance analysis without rational function approximations of the aerodynamic transfer function matrices. The usefulness of the uncertainty description and the methods available for robust aeroelastic stability analysis is demonstrated by performing aeroelastic wind-tunnel experiments.

  • 9.
    Borglund, Dan
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
    Robust Eigenvalue Analysis Using the Structured Singular Value: The mu-p Flutter Method2008In: AIAA Journal, ISSN 0001-1452, E-ISSN 1533-385X, Vol. 46, no 11, p. 2806-2813Article in journal (Refereed)
    Abstract [en]

    This paper introduces a new technique for robust aeroelastic analysis that extends standard linear flutter analysis to take deterministic uncertainty and variation into account. The basic principle of the proposed mu-p method is to exploit structured-singular-value (or mu) analysis to investigate if the system uncertainties can make the flutter determinant zero for a given flutter eigenvalue p. This makes it possible to compute regions of feasible eigenvalues in the complex plane as well as extreme eigenvalues that can be used to predict damping bounds and perform robust flutter analysis. The capability to predict damping bounds at subcritical flight conditions is a very attractive feature of the new method, as flight testing is rarely taken to the flutter point. The A-p formulation also opens up new possibilities to bound the magnitude of the system uncertainties based on frequency and/or damping estimates from flight testing. In the final part of the paper, the mu-p framework is successfully applied to perform robust aeroelastic analysis of a low-speed wind-tunnel model.

  • 10.
    Borglund, Dan
    KTH, Superseded Departments, Aeronautical and Vehicle Engineering.
    The mu-k method for robust flutter solutions2004In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, Vol. 41, no 5, p. 1209-1216Article in journal (Refereed)
    Abstract [en]

    A straightforward frequency-domain method for robust flutter analysis is presented. First, a versatile uncertainty description for the unsteady aerodynamic forces is derived by assigning uncertainty to the frequency-domain pressure coefficients. The uncertainty description applies to any frequency-domain aerodynamic method, benefits from the same level of geometric detail as the underlying aerodynamic model, exploits the modal formulation of the flutter equation, and is computed by simple postprocessing of standard aerodynamic data. Next, structured singular value analysis is applied to derive an explicit criterion for robust flutter stability based on the flutter equation and a parametric uncertainty description. The resulting procedure for computation of a worst-case flutter boundary resembles a p-k or g-method flutter analysis, produces match-point flutter solutions and allows for detailed aerodynamic uncertainty descriptions. Finally, the proposed method is successfully applied to a wind-tunnel model in low-speed airflow.

  • 11.
    Borglund, Dan
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
    Upper-bound flutter speed estimation using the mu-k method2005In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, Vol. 42, no 2, p. 555-557Article in journal (Refereed)
    Abstract [en]

    The use of upper-bound μ-k estimation method in the development of robust flutter analysis and flutter testing, was described. Since only the frequency-domain aerodynamic forces are required to compute μ(k), established aerodynamic methods can be used for the robust flutter analysis. A robust flutter analysis considering wing-tip aerodynamic uncertainty was developed in MATLAB® for a wind-tunnel model in low-speed airflow. The results show that the extended procedure for robust flutter analysis was successfully applied to a wind-tunnel model in low-speed airflow.

  • 12.
    Borglund, Dan
    et al.
    KTH, School of Industrial Engineering and Management (ITM), Learning.
    Carlsson, Ulf
    KTH, School of Engineering Sciences (SCI).
    Colarieti-Tosti, Massimiliano
    KTH, School of Engineering Sciences in Chemistry, Biotechnology and Health (CBH).
    Edström, Simon
    Havtun, Hans
    KTH, School of Industrial Engineering and Management (ITM), Energy Technology, Applied Thermodynamics and Refrigeration.
    Henriksson, Ann-Sofie
    KTH, School of Industrial Engineering and Management (ITM), Learning.
    Hjelm, Niclas
    KTH, School of Engineering Sciences in Chemistry, Biotechnology and Health (CBH), Biomedical Engineering and Health Systems, Basic Science.
    Naimi-Akbar, Ida
    KTH, School of Education and Communication in Engineering Science (ECE), Learning, Learning in Engineering Sciences.
    Collaborative Course Evaluation and Development at KTH: Progress, Lessons Learned and Way Forward2017In: 6th USIU Conference, 2017, article id 68Conference paper (Refereed)
  • 13.
    Borglund, Dan
    et al.
    KTH, School of Industrial Engineering and Management (ITM), Learning.
    Carlsson, Ulf
    KTH, School of Engineering Sciences (SCI).
    Colarieti-Tosti, Massimiliano
    KTH, School of Engineering Sciences in Chemistry, Biotechnology and Health (CBH).
    Edström, Simon
    Havtun, Hans
    KTH, School of Industrial Engineering and Management (ITM), Energy Technology, Applied Thermodynamics and Refrigeration.
    Hjelm, Niclas
    KTH, School of Engineering Sciences in Chemistry, Biotechnology and Health (CBH).
    Naimi-Akbar, Ida
    KTH, School of Industrial Engineering and Management (ITM), Learning.
    Collaborative course analysis and development at KTH: What's the next step and who needs to do what to make it happen?2017In: KTH SoTL, 2017Conference paper (Refereed)
  • 14.
    Borglund, Dan
    et al.
    KTH, Superseded Departments, Aeronautical and Vehicle Engineering.
    Kroo, I. M.
    Aeroelastic design optimization of a two-spar flexible wind-tunnel model2002In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, Vol. 39, no 6, p. 1074-1076Article in journal (Refereed)
  • 15.
    Borglund, Dan
    et al.
    KTH, Superseded Departments, Aeronautical Engineering.
    Kuttenkeuler, Jakob
    KTH, Superseded Departments, Aeronautical Engineering.
    Active wing flutter suppression using a trailing edge flap2002In: Journal of Fluids and Structures, ISSN 0889-9746, E-ISSN 1095-8622, Vol. 16, no 3, p. 271-294Article in journal (Refereed)
    Abstract [en]

    The aeroservoelastic behaviour of a thin rectangular wing with a controllable trailing edge flap is investigated. A rather high aspect ratio motivates a numerical model based on linear beam theory for the structural dynamics and strip theory for the unsteady aerodynamic loads. Experimental flutter testing shows good agreement with the numerical stability analysis, and the impact of the trailing edge flap on the dynamics is verified by open-loop testing. The problem of stabilizing the wing utilizing the trailing edge flap is posed, and the design of a fixed-structure feedback controller is performed using numerical optimization. The problem of maximizing closed-loop modal damping with constraints on actuator performance is solved for a sequence of flow speeds and the obtained controller is synthesized using gain scheduling. The fairly large predicted increase in critical speed is experimentally verified with satisfactory accuracy.

  • 16.
    Borglund, Dan
    et al.
    KTH, Superseded Departments, Aeronautical and Vehicle Engineering.
    Nilsson, Ulrik
    KTH, Superseded Departments, Aeronautical and Vehicle Engineering.
    Robust wing flutter suppression considering aerodynamic uncertainty2004In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, Vol. 41, no 2, p. 331-334Article in journal (Refereed)
    Abstract [en]

    A robust aeroservoelastic stability analysis considering frequency-domain aerodynamic uncertainty is utilized for robust control law design for flutter suppression of a flexible wing. The problem of stabilizing the wing in flutter using a minimum amount of control power is posed. For this purpose, numerical optimization is used to minimize the norm of a simple low-order controller subject to constraints on robust closed-loop stability. Robust stability is enforced in the optimization problem by posing constraints on the upper bounds on structured singular values and eigenvalues obtained from a linear stability analysis. The resulting controller is synthesized using gain scheduling, and robust wing flutter suppression is demonstrated in wind-tunnel testing.

  • 17.
    Borglund, Dan
    et al.
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
    Ringertz, Ulf
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
    Efficient computation of robust flutter boundaries using the mu-k method2006In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, Vol. 43, no 6, p. 1763-1769Article in journal (Refereed)
    Abstract [en]

    A simple and efficient algorithm for robust flutter analysis is presented. First, a general linear fractional transformation formulation of the mu-k method is provided, making it straightforward to pose the uncertain flutter equation in a form suitable for structured singular value analysis. The new formulation establishes a close connection between mu-k flutter analysis and traditional frequency-domain flutter analysis, which is used to formulate an efficient algorithm for computation of robust flutter boundaries. The proposed method is successfully applied to an F-16 sample test case with uncertain external stores aerodynamics, showing that standard tools for structural dynamics and unsteady aerodynamics can be used to perform robust flutter analysis with only modest additional modeling.

  • 18.
    Borglund, Dan
    et al.
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
    Ringertz, Ulf
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
    Solution of the Flutter Eigenvalue Problem with Mixed Structural/Aerodynamic Uncertainty2011In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, Vol. 48, no 1, p. 343-348Article in journal (Refereed)
    Abstract [en]

    The solution of the flutter eigenvalue problem with mixed structural/aerodynamic uncertainty was examined. A delta-wing wind-tunnel model was used as a test case. The model had a simple structural design and was made of glass-fiber and carbon-fiber composite materials. It had a semispan of 0.88 m and mean chord of 0.70m and was mounted vertically in the low-speed wind tunnel L2000. The numerical analysis was based on a NASTRAN model with shell elements for the wing, mass elements for the missile, and aerodynamic panels for doublet-lattice aerodynamic loads. The relatively stiff missile was modeled as a rigid body attached to the wing tip. The nominal eigenvalue was always an interior point of the corresponding eigenvalue set. A parameter sweep taking only aerodynamic uncertainty into account was performed by solving the eigenvalue problem for a set of parameter values. The eigenvalue sets based on one patch and seven patches, respectively, showed only slight difference.

  • 19.
    Borglund, Dan
    et al.
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
    Ringertz, Ulf
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
    Solution of the uncertain flutter eigenvalue problem using the μ-p method2009In: IFASD 2009: International Forum on Aeroelasticity and Structural Dynamics, 2009Conference paper (Other academic)
  • 20.
    Fredriksson, Mats H.
    et al.
    KTH, Superseded Departments, Mechanics.
    Borglund, Dan
    KTH, Superseded Departments, Aeronautical Engineering.
    Nordmark, Arne B.
    KTH, Superseded Departments, Mechanics.
    Experiments on the Onset of Impacting Motion Using a Pipe Conveying Fluid1999In: Nonlinear dynamics, ISSN 0924-090X, E-ISSN 1573-269X, Vol. 19, no 3, p. 261-271Article in journal (Refereed)
    Abstract [en]

    The transition from stable periodic nonimpacting motion to impacting motion, due to variations of parameters, is observable in a wide range of vibro-impact systems. Recent theoretical studies suggest a possible scenario for this type of transition. A key element in the proposed scenario is fulfilled if the oscillatory motion involved in the transition is born in a supercritical Hopf bifurcation. If the onset of impacting motion is close to the Hopf bifurcation, the impacting motion is likely to be chaotic. A numerical simulation of a system of articulated pipes conveying fluid is used to illuminate the theory. An experimental setup is presented, where a cantilevered pipe conveying fluid is unilaterally constrained. Results from experiments are found to be in good qualitative agreement with the theory.

  • 21.
    Heinze, Sebastian
    et al.
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
    Borglund, Dan
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
    On the influence of modeshape variations in robust flutter analysis2005Report (Other academic)
  • 22.
    Heinze, Sebastian
    et al.
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    Borglund, Dan
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    Robust Flutter Analysis Considering Mode Shape Variations2008In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, Vol. 45, no 3, p. 1070-1074Article in journal (Refereed)
    Abstract [en]

    A study was conducted to perform robust flutter analysis, considering mode shape variation problems. The study demonstrated that the assumption of a fixed modal base can lead to incorrect flutter results. It was demonstrated the nominal model can act as the basis for performing robust flutter analysis. The study assumed that the critical flutter mode shape can be represented by a linear combination of eigenmodes. The study also demonstrated that the modal base method can be used, to solve the problem of mode shape variations. It was also demonstrated that results of mode shape variation problems can be improved significantly, by adding structural eigenvectors.

  • 23.
    Heinze, Sebastian
    et al.
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    Ringertz, Ulf
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
    Borglund, Dan
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
    Assessment of Uncertain External Store Aerodynamics Using mu -p Flutter Analysis2009In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, Vol. 46, no 3, p. 1062-1068Article in journal (Refereed)
  • 24.
    Heinze, Sebastian
    et al.
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    Ringertz, Ulf
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    Borglund, Dan
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    On the Uncertainty Modeling for External Stores AerodynamicsManuscript (Other academic)
    Abstract [en]

    A wind tunnel model representing a generic delta wing configurationwith external stores is considered for flutter investigations. Complexeigenvalues are estimated for the wind tunnel model for airspeeds up tothe flutter limit, and compared to eigenvalues predicted by a numericalmodel. The impact of external stores mounted to the wing tip is investigatedboth experimentally and numerically, and besides the impact of thestores as such, the capability of the numerical model to account for increasingmodel complexity is investigated. An uncertainty approach basedon robust flutter analysis is demonstrated to account for modeling imperfections.Uncertainty modeling issues and the reliability of uncertaintymodels are discussed. Provided that the present uncertainty mechanismcan be determined, it is found that available uncertainty tools may beused to efficiently compute robust flutter boundaries.

  • 25.
    Heinze, Sebastian
    et al.
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
    Ringertz, Ulf
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
    Borglund, Dan
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
    On Uncertainty Modeling and Validation for External Store Aerodynamics2007In: IFASD 2007: International Forum on Aeroelasticity and Structural Dynamics, 2007Conference paper (Other academic)
  • 26.
    Rosén, Anders
    et al.
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Naval Systems.
    Edström, Kristina
    KTH, School of Education and Communication in Engineering Science (ECE), Learning.
    Borglund, Dan
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
    Kuttenkeuler, Jakob
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Naval Systems.
    Hallström, Stefan
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Lightweight Structures.
    Garme, Karl
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Naval Systems.
    3+2≠5 eller Programmål för ingenjörsutbildningar i ljuset av Bolognareformen2011In: 3:e Utvecklingskonferensen för Sveriges ingenjörsutbildningar, 2011, p. 47-52Conference paper (Refereed)
    Abstract [sv]

    KTH har infört en ny utbildningsstruktur, som innebär att de två sista åren på civilingenjörsutbildningen utgörs av masterprogram samt att studenterna ska vara behöriga att ta ut en kandidatexamen efter tre års studier. Man kan därmed säga att både kandidat och master ligger inbäddade i den femåriga civilingenjörsutbildningen. Kombinationen av utbildningsprogram, examina och utbildningsmål väcker några principiellt intressanta frågeställningar med långtgående konsekvenser för ingenjörsutbildningen. Vi har analyserat dessa frågeställningar och identifierat att vi står inför ett strategiskt vägval där det nu gäller att långsiktigt slå vakt om ingenjörsutbildningens värde som professionsutbildning. En väl genomförd implementering av den nya utbildningsstrukturen kan förena vetenskaplighet med ingenjörsmässighet och därmed väsentligt stärka ingenjörsutbildningen.

  • 27.
    Rosén, Anders
    et al.
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    Edström, Kristina
    KTH, School of Education and Communication in Engineering Science (ECE), Learning.
    Borglund, Dan
    KTH, School of Education and Communication in Engineering Science (ECE), Learning, Organisation and leadership.
    Kuttenkeuler, Jakob
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    Hallström, Stefan
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    Garme, Karl
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    Programmål inom den nya utbildningsstrukturen på KTH2010Report (Other academic)
  • 28.
    Sundberg, Torbjörn
    et al.
    KTH, School of Electrical Engineering (EES), Space and Plasma Physics.
    Ivchenko, Nickolay
    KTH, School of Electrical Engineering (EES), Space and Plasma Physics.
    Borglund, Dan
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
    Ahlén, Per
    KTH, School of Electrical Engineering (EES), Space and Plasma Physics.
    Gustafsson, M.
    KTH, School of Electrical Engineering (EES), Space and Plasma Physics.
    Jonsson, C.
    Juhlen, J.
    KTH, School of Electrical Engineering (EES), Space and Plasma Physics.
    Neuner, Oliver
    KTH, School of Electrical Engineering (EES), Sound and Image Processing (Closed 130101).
    Sandström, J.
    KTH, School of Electrical Engineering (EES), Space and Plasma Physics.
    Sund, E.
    KTH, School of Electrical Engineering (EES), Space and Plasma Physics.
    Wartelski, Matías
    KTH, School of Electrical Engineering (EES), Space and Plasma Physics.
    Westlund, C.
    KTH, School of Electrical Engineering (EES), Space and Plasma Physics.
    Xin, L.
    KTH, School of Electrical Engineering (EES), Space and Plasma Physics.
    Small recoverable payload for deployable sounding rocket experiments2009In: Proceedings of the 19th Esa Symposium on European Rocket and Balloon Programmes and Related Research, 2009, p. 281-284Conference paper (Refereed)
    Abstract [en]

    We present a design of a small payload for deployment from sounding rockets. The payload is intended for measurements in the ionosphere and the acquired data is stored onboard. For a secure recovery of the data and possible re-use of the payload, an inflatable structure is deployed during the payload descent. This reduces the payload speed and protects it from ground impact. On the ground, a localization system is activated, sending the payload position via a satellite link, and providing a radio beacon signal. The proposed small payload will allow high time resolution multipoint measurements in the ionosphere with small separation distances, thus allowing to address a number of unresolved questions in the field.

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  • sv-SE
  • Other locale
More languages
Output format
  • html
  • text
  • asciidoc
  • rtf