摘要 :
This paper presents a MATLAB suite of codes entitled getPROP for designing, analyzing, and optimizing low-noise signature propellers. The getPROP package has been developed to perform end-to-end analysis, from an initial propeller...
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This paper presents a MATLAB suite of codes entitled getPROP for designing, analyzing, and optimizing low-noise signature propellers. The getPROP package has been developed to perform end-to-end analysis, from an initial propeller design to a low-signature optimized configuration that meets the operational requirements. The presented getPROP code framework covers various modules: propeller design, aerodynamic database, performance, noise prediction, atmospheric attenuation, psychoacoustic, and optimization. A complete analysis with the getPROP suite is presented through the optimization of a commercial off-the-shelf APC 14" x 5.5" propeller into a low-noise signature design, thus demonstrating the software applicability for improving multi-copters propellers.
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摘要 :
The annoying sound produced by a multi-rotor vehicle can bring a severe acoustic nuisance to an urban soundscape. Hence, it is essential to find a solution to attenuate the acoustic signature of a multi-rotor platform for further ...
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The annoying sound produced by a multi-rotor vehicle can bring a severe acoustic nuisance to an urban soundscape. Hence, it is essential to find a solution to attenuate the acoustic signature of a multi-rotor platform for further development and acceptance of these vehicles by the public. In this paper, an attempt is made to apply a phase control technique to attenuate acoustic signature, and the feasibility and potential are explored through an experiment. Phase control is a noise reduction technique that leverages destructive interference of the coherent acoustic source field between a system of propellers. The measurements were conducted in the newly established anechoic chamber at the Faculty of Aerospace Engineering at the Technion - Israel Institute of Technology. An array of 15 microphones were placed 1.5 m away from the center of a four-rotor rig on a spherical arc. The aerodynamic forces and moments were measured with load cells. Carefully selecting the relative azimuths blade angle (phase), the overall directivity and level of the tonal component at the blade passage frequency can be attenuated. It was found that with 90° phase between neighboring rotors, a reduction of 8 dB and at 3000 RPM and by 5 dB at 4100 RPM was observed at θ = 45°, in comparison to uncontrolled configuration.
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摘要 :
This document contains the work done for an undergraduate final design project at the Aerospace Engineering faculty of the Technion during the academic year 2018-2019. Based on given operational requirements, a small drone was des...
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This document contains the work done for an undergraduate final design project at the Aerospace Engineering faculty of the Technion during the academic year 2018-2019. Based on given operational requirements, a small drone was designed, with the abilities to perform vertical takeoff and landing, horizontal flight and endurance flight. The work described in this document is a follow-up to the work done during 2016-2018 academic years, which included aerodynamic and configuration design of the entire drone and straight, level, and vertical flight control. This academic year, the project continuing the collaboration with San Diego State University (SDSU). The work done this year included development of the lateral flight control of the UAV in fixed wing flight mode, designing a downsized model for testing the operational requirements, theoretical examination of the aerodynamic configuration and wind tunnel test operation.
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摘要 :
This document contains the work done for an undergraduate final design project at the Aerospace Engineering faculty of the Technion during the academic year 2018-2019. Based on given operational requirements, a small drone was des...
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This document contains the work done for an undergraduate final design project at the Aerospace Engineering faculty of the Technion during the academic year 2018-2019. Based on given operational requirements, a small drone was designed, with the abilities to perform vertical takeoff and landing, horizontal flight and endurance flight. The work described in this document is a follow-up to the work done during 2016-2018 academic years, which included aerodynamic and configuration design of the entire drone and straight, level, and vertical flight control. This academic year, the project continuing the collaboration with San Diego State University (SDSU). The work done this year included development of the lateral flight control of the UAV in fixed wing flight mode, designing a downsized model for testing the operational requirements, theoretical examination of the aerodynamic configuration and wind tunnel test operation.
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