The Experts below are selected from a list of 1836 Experts worldwide ranked by ideXlab platform
Zbigniew Ulanowski - One of the best experts on this subject based on the ideXlab platform.
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design and field campaign validation of a multirotor uav and optical particle counter
Atmospheric Measurement Techniques Discussions, 2020Co-Authors: Joseph Girdwood, Helen Smith, Warren Stanley, Zbigniew Ulanowski, Chris Stopford, Charles Chemel, Konstantinosmatthaios Doulgeris, David BrusAbstract:Abstract. Small unmanned aircraft (SUA) have the potential to be used as platforms for the measurement of atmospheric particulates. The use of an SUA platform for these measurements provides benefits such as high manoeuvrability, re-usability, and low-cost when compared with traditional techniques. However, the complex aerodynamics of an SUA (particularly for multirotor Airframes), combined with the miniaturisation of particle instruments poses difficulties for accurate and representative sampling of particulates. The work presented here relies on computational fluid dynamics with Lagrangian particle tracking (CFD-LPT) simulations to influence the design of a bespoke meteorological sampling system: the UH-AeroSAM. This consists of a custom built airframe, designed to reduce sampling artefacts due to the propellers, and a purpose built open-path optical particle counter–the Ruggedised Cloud and Aerosol Sounding System (RCASS). OPC size distribution measurements from the UH-AeroSAM are compared with the Cloud and Aerosol Precipitation Spectrometer (CAPS) for measurements of Stratus cloud during the Pallas Cloud Experiment (PaCE) in 2019. Good agreement is demonstrated between the two instruments. The integrated dN/dlog(Dp) is shown to have a coefficient of determination of 0.8, and a regression slope of 0.9 when plotted 1:1.
Katon Matzaini - One of the best experts on this subject based on the ideXlab platform.
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Design for modularity of Blended Wing Body (BWB) baseline ii-E2 Unmanned Aerial Vehicle (UAV) / Matzaini Katon
2014Co-Authors: Katon MatzainiAbstract:This thesis describes the strategy used for designing the structural modular layout for the Blended Wing Body (BWB) Baseline II-E2 Unmanned Aerial Vehicle (UAV) airplane. In order to give UAV more flexibility in terms of availability of flight mission, there was a need for a quick and ease of assembly and disassembly’s process for the airframe. The goal of this research was to design a BWB modular airframe, focusing on the ease of airframe assembly and disassembly. Morphological Method and Pugh Method were used as the concept generation and evaluation tools in designing the BWB airframe. The BWB was divided into 5 main modules; wing-body module, starboard and portside module and, right-side and left-side canards module. CATIA, a Computational Aided Design (CAD) software was used to build the three dimensional (3-D) model of the airframe. MSC Patran/Nastran was used as the finite element (FE) analysis tool to analyze the BWB airframe static strength. Analysis was done focusing on the stress and deflections results. FE models for the airframe were developed in MSC Patran. CQUAD4, CTRIA3, CBEAM and CBAR elements were used to represent the individual components of the airframe such as spar and frames. Validation of FE static analysis was done using the static theoretical analysis in the form of stress calculations using simple beam theory. The airframe design was based on the +3.8 g flight load. Sizing of joints between modules was done through the use of empirical analysis. Internal forces induced in the connector between modules were used to size the joints. Approach using the CAD and Computational Aided Engineering (CAE) platform for designing the modular BWB airplane has been shown in this research. Design of the airframe proposed here had been analytically proven to be safe
Matzaini Katon - One of the best experts on this subject based on the ideXlab platform.
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design for modularity of blended wing body bwb baseline ii e2 unmanned aerial vehicle uav matzaini katon
2014Co-Authors: Matzaini KatonAbstract:This thesis describes the strategy used for designing the structural modular layout for the Blended Wing Body (BWB) Baseline II-E2 Unmanned Aerial Vehicle (UAV) airplane. In order to give UAV more flexibility in terms of availability of flight mission, there was a need for a quick and ease of assembly and disassembly’s process for the airframe. The goal of this research was to design a BWB modular airframe, focusing on the ease of airframe assembly and disassembly. Morphological Method and Pugh Method were used as the concept generation and evaluation tools in designing the BWB airframe. The BWB was divided into 5 main modules; wing-body module, starboard and portside module and, right-side and left-side canards module. CATIA, a Computational Aided Design (CAD) software was used to build the three dimensional (3-D) model of the airframe. MSC Patran/Nastran was used as the finite element (FE) analysis tool to analyze the BWB airframe static strength. Analysis was done focusing on the stress and deflections results. FE models for the airframe were developed in MSC Patran. CQUAD4, CTRIA3, CBEAM and CBAR elements were used to represent the individual components of the airframe such as spar and frames. Validation of FE static analysis was done using the static theoretical analysis in the form of stress calculations using simple beam theory. The airframe design was based on the +3.8 g flight load. Sizing of joints between modules was done through the use of empirical analysis. Internal forces induced in the connector between modules were used to size the joints. Approach using the CAD and Computational Aided Engineering (CAE) platform for designing the modular BWB airplane has been shown in this research. Design of the airframe proposed here had been analytically proven to be safe.
David Brus - One of the best experts on this subject based on the ideXlab platform.
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design and field campaign validation of a multirotor uav and optical particle counter
Atmospheric Measurement Techniques Discussions, 2020Co-Authors: Joseph Girdwood, Helen Smith, Warren Stanley, Zbigniew Ulanowski, Chris Stopford, Charles Chemel, Konstantinosmatthaios Doulgeris, David BrusAbstract:Abstract. Small unmanned aircraft (SUA) have the potential to be used as platforms for the measurement of atmospheric particulates. The use of an SUA platform for these measurements provides benefits such as high manoeuvrability, re-usability, and low-cost when compared with traditional techniques. However, the complex aerodynamics of an SUA (particularly for multirotor Airframes), combined with the miniaturisation of particle instruments poses difficulties for accurate and representative sampling of particulates. The work presented here relies on computational fluid dynamics with Lagrangian particle tracking (CFD-LPT) simulations to influence the design of a bespoke meteorological sampling system: the UH-AeroSAM. This consists of a custom built airframe, designed to reduce sampling artefacts due to the propellers, and a purpose built open-path optical particle counter–the Ruggedised Cloud and Aerosol Sounding System (RCASS). OPC size distribution measurements from the UH-AeroSAM are compared with the Cloud and Aerosol Precipitation Spectrometer (CAPS) for measurements of Stratus cloud during the Pallas Cloud Experiment (PaCE) in 2019. Good agreement is demonstrated between the two instruments. The integrated dN/dlog(Dp) is shown to have a coefficient of determination of 0.8, and a regression slope of 0.9 when plotted 1:1.
Van, Wyk David - One of the best experts on this subject based on the ideXlab platform.
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Guidance, navigation and control of a small, unharmed blended wing body aircraft
'University of Babylon - Department of Mechanical Engineering Faculty of Engineering', 2020Co-Authors: Van, Wyk DavidAbstract:The purpose of this research is to document the design and optimisation of a full suite of guidance, navigation and control (GNC) algorithms for a small unmanned aerial vehicle (UAV), the Skywalker X8. This was performed so as to fill a void in the available literature on the selected airframe, which currently only focuses on aspects such as aerodynamic modelling, advanced controller design, or uses of the airframe to perform higher level tasks. All of these research areas make use of off-the-shelf flight controllers, but these are not always the most appropriate foundations for more advanced work as they are inherently sluggish so as to be broadly applicable to a variety of Airframes. Subsequently, the Skywalker X8 airframe was modelled, using existing literature, and then characterised so as to establish what the goals might be for an optimal set of controllers. An autopilot was then designed which was optimised so as to be as close to the identified optimal performance characteristics as possible, with effort being put into ensuring that all non-linearities and disturbances were taken into account. This included advanced modelling of sensors, actuators, the environment, and the system itself. The autopilot design was then extended with a set of guidance and navigation algorithms, also developed as part of this research. This consisted of both path planning and path following algorithms which allowed for the synthesis of general classes of paths useful to the application. With both the autopilot and guidance laws developed, the system could be tested under several atmospheric flight conditions. These took the form of various wind directions and intensity levels being applied to the airframe whilst transitioning between a range of different waypoint configurations. The system was subsequently shown to be able to follow a set of waypoints very accurately, even with winds and turbulence with magnitudes of in excess of 60% of the aircraft's nominal airspeed. With a strong autopilot designed and illustrated in a high fidelity simulation environment, this work can now easily be extended into many fields. All of the tools used for this research are available and well documented, and the processes followed repeatable with all justification available in the text. As such, should a project which aims to extend this work wish to adjust the autopilot design or guidance laws, based on different requirements, this is easily accomplished and recommendations of starting points are provided. The system model and autopilot are also made available and are usable exactly as they are should one wish to undertake additional research which does not aim to modify, but to extend this work
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Guidance, navigation and control of a small, unmanned blended wing body aircraft
'University of Babylon - Department of Mechanical Engineering Faculty of Engineering', 2020Co-Authors: Van, Wyk DavidAbstract:The purpose of this research is to document the design and optimisation of a full suite of guidance, navigation and control (GNC) algorithms for a small unmanned aerial vehicle (UAV), the Skywalker X8. This was performed so as to fill a void in the available literature on the selected airframe, which currently only focuses on aspects such as aerodynamic modelling, advanced controller design, or uses of the airframe to perform higher level tasks. All of these research areas make use of off-the-shelf flight controllers, but these are not always the most appropriate foundations for more advanced work as they are inherently sluggish so as to be broadly applicable to a variety of Airframes. Subsequently, the Skywalker X8 airframe was modelled, using existing literature, and then characterised so as to establish what the goals might be for an optimal set of controllers. An autopilot was then designed which was optimised so as to be as close to the identified optimal performance characteristics as possible, with effort being put into ensuring that all non-linearities and disturbances were taken into account. This included advanced modelling of sensors, actuators, the environment, and the system itself. The autopilot design was then extended with a set of guidance and navigation algorithms, also developed as part of this research. This consisted of both path planning and path following algorithms which allowed for the synthesis of general classes of paths useful to the application. With both the autopilot and guidance laws developed, the system could be tested under several atmospheric flight conditions. These took the form of various wind directions and intensity levels being applied to the airframe whilst transitioning between a range of different waypoint configurations. The system was subsequently shown to be able to follow a set of waypoints very accurately, even with winds and turbulence with magnitudes of in excess of 60% of the aircraft's nominal airspeed. With a strong autopilot designed and illustrated in a high fidelity simulation environment, this work can now easily be extended into many fields. All of the tools used for this research are available and well documented, and the processes followed repeatable with all justification available in the text. As such, should a project which aims to extend this work wish to adjust the autopilot design or guidance laws, based on different requirements, this is easily accomplished and recommendations of starting points are provided. The system model and autopilot are also made available and are usable exactly as they are should one wish to undertake additional research which does not aim to modify, but to extend this work