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  • 101.
    Staack, Ingo
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Chaitanya Munjulury, Raghu
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Melin, Tomas
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Abdalla, Alvaro Martins
    The University of São Paulo (USP), Brazil.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    CONCEPTUAL AIRCRAFT DESIGN MODEL MANAGEMENTDEMONSTRATED ON A 4TH GENERATION FIGHTER2014Konferansepaper (Fagfellevurdert)
    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.

  • 102.
    Staack, Ingo
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Ellström, Hans
    Saab Aeronautics.
    Bergman, Mats
    Saab Aeronautics.
    Sarwe, Pål
    Saab Aeronautics.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    More  electrical environmental control system simulation2012Inngår i: Proceedings of the 28th  International Congress of the Aeronautical Sciences, Brisbane: ICAS , 2012Konferansepaper (Annet vitenskapelig)
    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.

  • 103.
    Staack, Ingo
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Integration of On-Board Power Systems Simulation in Conceptual Aircraft Design2013Inngår i: Proceedings of the 4th CEAS Conference in Linköping / [ed] Tomas Melin, Petter Krus,Emil Vinterhav, Knut Övrebö, Linköping, Sweden: Linköping University Electronic Press, 2013, s. 709-718Konferansepaper (Annet vitenskapelig)
    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.

  • 104.
    Turetta, F. M. S.
    et al.
    EMBRAER, Department of Systems Modeling and Simulation, Brazil.
    Ayala, H. V. H.
    EMBRAER, Department of Systems Modeling and Simulation, Brazil.
    Trabasso, Luís Gonzaga
    Linköpings universitet, Institutionen för datavetenskap, Interaktiva och kognitiva system. Linköpings universitet, Tekniska fakulteten. SAAB, Aeronautics Human Machine Interaction.
    Alfredson, Jens
    Linköpings universitet, Institutionen för datavetenskap, Interaktiva och kognitiva system. Linköpings universitet, Tekniska fakulteten. SAAB, Aeronautics Human Machine Interaction.
    Data-driven Pilot Behavior Modeling Applied to a VMCG Determination Flight Test Task2016Inngår i: Proceedings of the Aerospace Technology Congress / [ed] Kaj Lundahl, Roland Karlsson, Björn Jonsson and Knut Övrebö, Stockholm, 2016, Vol. 1, s. 1-10, artikkel-id 1Konferansepaper (Fagfellevurdert)
    Abstract [en]

    Human models have been studied and used in engineering analysis for over 70 years to allow predictions of the pilot-vehicle system behavior. The difficulties in pilot modeling are evident due to the complexity of the brain, lack of repeatability in behavior and the great number of variables that can affect the human performance. This complexity, associated with the fact that there are no explicit laws to allow modeling based in first principles, could indicate that data-driven modeling techniques would be the most efficient way to obtain pilot models, such as black-box system identification methods that construct dynamic models according to measured input and output data, and where the parameters have no physical meaning. With this approach, it is advantageous to seek knowledge from other fields to allow a better understanding of the pilot behavior, select adequate input/output variables and define the experimental conditions and data. Criteria for evaluating the modeling approaches include adaptability as well as feasibility. Adaptability concerns coping with dynamic and uncertain conditions and feasibility refers to the models contribution to an applied context. This paper presents the results of the application of data-driven theoretical linear dynamic models in the task of representing the behavior of the pilot trying to keep the centerline of the runway after an engine failure. Real data is used, where PID with anti-windup and Hammerstein-Wiener model structures are compared. Results show that the Hammerstein-Wiener structure seems more appropriate to represent this specific behavior.

  • 105.
    Uebel, Karl
    et al.
    Volvo Construct Equipment, Sweden.
    Raduenz, Henrique
    Univ Fed Santa Catarina, Brazil.
    Krus, Petter
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska fakulteten.
    de Negri, Victor Juliano
    Univ Fed Santa Catarina, Brazil.
    DESIGN OPTIMISATION STRATEGIES FOR A HYDRAULIC HYBRID WHEEL LOADER2018Inngår i: PROCEEDINGS OF THE BATH/ASME SYMPOSIUM ON FLUID POWER AND MOTION CONTROL, 2018, AMER SOC MECHANICAL ENGINEERS , 2018, artikkel-id V001T01A001Konferansepaper (Fagfellevurdert)
    Abstract [en]

    This paper deals with design optimisation of hydraulic hybrid drivelines during early concept design phases. To set the design parameters of a hybrid driveline such as gear ratios, pump/motor displacements and size of energy storage, the energy management of the hybrid machine needs to be considered as well. This is problematic since a nested design and control optimisation normally requires substantial computer power and is time-consuming. Few previous studies have treated combined design and control optimisation of hydraulic hybrid vehicles using detailed, non-linear component driveline models. Furthermore, previously proposed design optimisation methods for on road vehicles are not suitable for heavy off-road machines operating in short repetitive cycles with high transient power output. The paper demonstrates and compares different optimisation approaches for design and control optimisation combining deterministic dynamic programming and non-gradient based numerical optimisation. The results show that a simple rule-based energy management strategy can be sufficient to find the optimal hardware design even though non-optimal control laws are used.

  • 106.
    Unnikrishnan, Vishnu
    et al.
    Linköpings universitet, Institutionen för systemteknik, Elektroniska Kretsar och System. Linköpings universitet, Tekniska fakulteten.
    Rao Pathapati, Srinivasa
    Linköpings universitet, Institutionen för systemteknik, Elektroniska Kretsar och System. Linköpings universitet, Tekniska fakulteten.
    Vesterbacka, Mark
    Linköpings universitet, Institutionen för systemteknik, Elektroniska Kretsar och System. Linköpings universitet, Tekniska fakulteten.
    A Fully Synthesized All-Digital VCO-Based Analog-to-Digital Converter2015Inngår i: 2015 NORDIC CIRCUITS AND SYSTEMS CONFERENCE (NORCAS) - NORCHIP and INTERNATIONAL SYMPOSIUM ON SYSTEM-ON-CHIP (SOC), Institute of Electrical and Electronics Engineers (IEEE), 2015Konferansepaper (Fagfellevurdert)
    Abstract [en]

    Synthesis of all-digital ADCs leads to significant reduction in design cost and design time, besides improving cross-technology portability. In this work, an ADC which is fully described in digital HDL is synthesized, placed and routed using standard digital design tools. A VCO-based architecture is chosen for its synthesizability. The design flow employed is discussed. The circuit is synthesized using the standard cell library in a 65 nm CMOS process, delivering a resolution of 9 ENOB over 10 MHz bandwidth according to post layout parasitic extracted simulations using the Spectre simulator. Post synthesis and post place-and-route performances are provided.

  • 107.
    Venkata, Raghu. C. M.
    et al.
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Tarkian, Mehdi
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Maskinkonstruktion. Linköpings universitet, Tekniska högskolan.
    Jouannet, Christopher
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Fluida och mekatroniska system. Linköpings universitet, Tekniska högskolan.
    Model Based Aircraft Control System Design And Simulation2010Inngår i: 27th Congress of the International Council of the Aeronautical Sciences 2010 (ICAS 2010), Proceedings of a meeting held 19-24 September 2010, Nice, France. / [ed] Professor I Grant, Optimage Ltd. on behalf of the International Council of the Aeronautical Sciences (ICAS) , 2010, s. 3338-3347Konferansepaper (Fagfellevurdert)
    Abstract [en]

    Development of modern aircrafts has become more and more expensive and time consuming. In order to minimize the development cost, an improvement of the conceptual design phase is needed. The desired goal of the project is to enhance the functionality of an in house produced framework conducted at theDepartment of Machine Design, Link¨ping University, consisting of parametric aircraft models used for conceptual design. The former part of the work consists of the construction of geometric aircraft control surfaces such as flaps, aileron, rudder and elevator parametrically in CATIA V5. The next part of the work involves designing and simulating an Inverse dynamic model in Dymola software. An Excel interface has been developed between CATIA and Dymola. Parameters can be varied in the interface as per user specification; these values are sent to CATIA or Dymola and vice versa. The constructed concept model of control surfaces has been tested for different aircraft shapes and layout. An interface is developed between CATIA, Dymola and Tornado. An optimization case is performed to visualize the automation capability of choosing an actuator from a database for the proposed framework, and enhance the early design phases for aircraft conceptual design.

  • 108.
    Wang, Lieke
    et al.
    Siemens Ind Turbomachinery AB, Sweden.
    Kinell, Mats
    Siemens Ind Turbomachinery AB, Sweden.
    Nadali Najafabadi, Hossein
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Mekanisk värmeteori och strömningslära. Linköpings universitet, Tekniska fakulteten.
    Karlsson, Matts
    Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, Mekanisk värmeteori och strömningslära. Linköpings universitet, Tekniska fakulteten.
    A THREE-REGIME BASED METHOD FOR CORRELATING FILM COOLING EFFECTIVENESS FOR CYLINDRICAL AND SHAPED HOLES2015Inngår i: ASME TURBO EXPO: TURBINE TECHNICAL CONFERENCE AND EXPOSITION, 2015, VOL 5B, AMER SOC MECHANICAL ENGINEERS , 2015, nr UNSP V05BT12A004Konferansepaper (Fagfellevurdert)
    Abstract [en]

    To cope with high temperature of the gas from combustor, cooling is often used in the hot gas components in gas turbines. Film cooling is one of the effective methods used in this application. Both cylindrical and fan-shaped holes are used in film cooling. There have been a number of correlations published for both cylindrical and fan-shaped holes regarding film cooling effectiveness. Unfortunately there are no definitive correlations for either cylindrical or fan-shaped holes. This is due to the nature of the complexity of film cooling where many factors influence its performance, e.g., blowing ratio, density ratio, surface angle, downstream distance, expansion angle, hole length, turbulence level, etc. A test rig using infrared camera was built to test the film cooling performance for a scaled geometry from a real nozzle guide vane. Both cylindrical and fan-shaped holes were tested. To correlate the experimental data, a three-regime based method was developed for predicting the film cooling effectiveness. Based on the blowing ratio, the proposed method divides the film cooling performance in three regimes: fully attached (or no jet lift-off), fully jet lift-off, and the transition regime in between. Two separate correlations are developed for fully attached and full jet lift-off regimes, respectively. The method of interpolation from these two regimes is used to predict the film cooling effectiveness for the transition regime, based on the blowing ratio. It has been found this method can give a good correlation to match the experimental data, for both cylindrical and fan-shaped holes. A comparison with literature was also carried out, and it showed a good agreement.

123 101 - 108 of 108
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