Parameter optimization to avoid propeller-induced structural resonance of quadrotor type Unmanned Aerial Vehicle

Tullu, Abera; Byun, Young-Seop; Kim, Jae-Nam; Kang, Beom-Soo

doi:10.1016/j.compstruct.2018.03.014

Cited by 9 publications

(4 citation statements)

References 38 publications

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“…Thus, the driving frequency that will not stimulate the resonance can be determined. It is presented that the error between experimental results and simulations can become 7.99% for the whole models due to number of reasons such as the increased number of joints among components and the effect of the suspension rubber used to hang the bi-copter to the ceiling [7].…”

Section: Natural Frequenciesmentioning

confidence: 99%

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Parameter Optimization of a Bi-copter Type Unmanned Aerial Vehicle to Avoid Propeller-induced Vibrations During Hovering

Akyildiz¹,

Kaçar

Yalçın³

2020

Sakarya University Journal of Science

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The vibration parameters of a bi-copter-type unmanned aerial vehicle is optimized by considering operational vibration with payloads. The double electric ducted fan loads, which transmit excitations to the fuselage, are predicted and compared using optimization methods. While the minimum vibration amplitude for stress will be achieved at 7.69 Hz, it will be 9.80 Hz. for minimum deformation without sacrificing safety factor requirement. It ensures sensitive vertical acceleration. It is not seen significant differences on results from screening and genetic algorithm methods. Correlations between frequencies and structural responses are determined. It is observed that the stress and deformation amplitudes of the structure decreases at increasing frequencies up to the next natural frequency. While the highest amplitude is seen at the first frequency, it decreases in increasing modes. The airframe structural model's operational frequency must be 7.69 or 9.80 Hz to achieve sensitive vertical acceleration. Subsequently, it is aimed to develop an autonomous task by the implemented system controlled by various algorithm as a future work.

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Section: Natural Frequenciesmentioning

confidence: 99%

“…Since UAV's are constrained to have lower weight as little as possible for energy efficiency, optimizing the material properties is an important task for both its own or any attachment's stabilization such as cameras during service life [6,7]. The stiffness of the material affects vibration characteristics.…”

Section: Introductionmentioning

confidence: 99%

Parameter Optimization of a Bi-copter Type Unmanned Aerial Vehicle to Avoid Propeller-induced Vibrations During Hovering

Akyildiz¹,

Kaçar

Yalçın³

2020

Sakarya University Journal of Science

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“…EI-Gazzar [12] used the FEA to detect the variation of the vibration characteristics of the motor structure and the influence of the structural stiffness on the structural resonance. Tullu et al [13] used the FEA to establish the propeller model and used the nonlinear sequence quadratic programming algorithm to obtain the optimal parameters of the first fundamental frequency of the structure to avoid the resonance problem. Tompkins et al [14] used the FEA to calculate the natural frequency of the pump structure and modeled the possible modifications to eliminate the harmful resonance effects.…”

Section: Introductionmentioning

confidence: 99%

Research on a Multinode Joint Vibration Control Strategy for Controlling the Steering Wheel of a Commercial Vehicle

Tang

Ye³

et al. 2020

Shock and Vibration

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The vibration degree of a steering wheel has important reference significance for drivers to evaluate the ride comfort of the whole vehicle. To solve the jitter problem of the steering wheel of a commercial vehicle at idle speed, this work proposes a multinode joint vibration control strategy (MDVC) based on the associated vibration path of the steering wheel. Based on the analysis of the associated vibration transfer paths of the steering wheel, the whole vehicle was divided into a system comprising several nodes. For the decomposed node system, taking the vibration transmission path associated with the target as the research direction, the vibration reduction design of each node system is analyzed step by step. After exploring the possible causes of abnormal vibration of the steering wheel through experimental tests, the abnormal node structure interval was determined. By further extracting the structural model of the steering system from the vehicle, the hammering method was applied to test its modal and related frequency. Furthermore, an improved structure of steering support was also designed, and its fitting degree and modal characteristics were analyzed and compared to the original scheme. The following test results show that the structure improvement greatly reduces the vibration level of the steering wheel, meets the ideal design requirements of the steering wheel vibration reduction, and provides the possibility of weighing the correlation between these hierarchical node systems in whole vehicle.

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“…In [8] an active camera mount system using an inertial piezostack actuator in the conventional rubber mount for controlling unwanted vibrations in a UAV is proposed and experimentally validated. In [9] it is demonstrated that propeller induced structural resonance of quadrotor UAVs can be avoided by optimizing the lengths, diameters, and initial and final fiber orientation angles of the arms and landing gears. In [4] the main vibration sources in UAVs are analyzed and a survey of the available methodologies for designing a stabilized optical imaging system is presented.…”

Section: Introductionmentioning

confidence: 99%

Modeling and Identification of Vibrations in a UAV for Aerial Manipulation

Cocuzza

Doria

2020

Mechanisms and Machine Science

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Aerial manipulators have many important application scenarios, such as inspection and maintenance, search and rescue, structure assembly, and logistics. One important challenge in aerial manipulation is related to the vibrations induced on the manipulator and its end-effector by the Unmanned Aerial Vehicle (UAV), which significantly affect the grasping and manipulation precision/performance. In this paper, vibration analysis of a heavy payload octocopter has been carried out using Experimental Modal Analysis (EMA). A simplified Mass-Spring-Damper (MSD) dynamic model of the system has then been proposed, whose dynamic parameters have been identified by analyzing selected experimental modes of vibration. The identified model will be useful for the design of the manipulator and related vibrations isolation system.

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Parameter optimization to avoid propeller-induced structural resonance of quadrotor type Unmanned Aerial Vehicle

Cited by 9 publications

References 38 publications

Parameter Optimization of a Bi-copter Type Unmanned Aerial Vehicle to Avoid Propeller-induced Vibrations During Hovering

Parameter Optimization of a Bi-copter Type Unmanned Aerial Vehicle to Avoid Propeller-induced Vibrations During Hovering

Research on a Multinode Joint Vibration Control Strategy for Controlling the Steering Wheel of a Commercial Vehicle

Modeling and Identification of Vibrations in a UAV for Aerial Manipulation

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