Dynamic behavior of composite marine propeller blades

Abrate, Serge

doi:10.1016/b978-0-08-100887-4.00002-0

Cited by 3 publications

(2 citation statements)

References 146 publications

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“…Динамічну поведінку композитних лопатей морського гвинта розглянуто в [2]. Зазначено необхідність моделювання композиційного ламінату з анізотропними шарами відповідної товщини, кількістю та орієнтацією волокон у кожному шарі.…”

Section: метод чисельного визначення динамічних характеристик лопаті ...unclassified

Метод Чисельного Визначення Динамічних Характеристик Лопаті Повітряного Гвинта З Композиційного Матеріалу

Morozov

2024

aktt

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The subject matter of this article is the dynamic characteristics of a composite propeller blade. Determination of the modes and frequencies of natural vibrations is necessary to predict the dangerous resonance modes of aircraft engines and to identify the most stressed local zones of the blade surface. The goal of this study is to develop a verified method for determining the dynamic characteristics of composite rotor parts of aircraft engines based on the known properties of the structural components of the composite material. A general mathematical statement of the problem of elasticity theory for the analysis of the dynamic characteristics of composite structures is described. A complete system of equations that describes the mechanical state of the body within the framework of the continuum mechanics approach was developed. Geometric modeling of the propeller blades was performed. Modeling and numerical investigation of the natural frequencies and mode shapes of the propeller blade were performed using the finite element method using the ANSYS software package. Based on the results of numerical research of the stressed and deformed state of the propeller blade, the first five natural vibration frequencies and the distribution of the local stress field were determined. The most stressed local zones on the blade surface were determined for each form of natural vibration. The propeller blade model was verified using an experimental study of the first five forms and frequencies of natural blade vibrations. The eigenfrequencies of the blade vibration were experimentally determined using the method of free (natural) vibrations. The resonance method was used to experimentally determine the resonant frequencies and vibration modes of the blade. The distribution of the blade deformation field was investigated using the strain gauge method. The highest error in the verification of numerical and experimental research is 4.11% for the fourth vibration frequency. Conclusions. The scientific novelty of the results obtained is that the effective elastic properties of the composite material for calculations should be determined using the procedure of numerical homogenisation of composite materials of different reinforcement structures by the properties of the matrix and fibers. The method does not require experimental determination of the effective elastic constants for the layers of blade components of different weave architecture patterns.

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Section: метод чисельного визначення динамічних характеристик лопаті ...unclassified

Метод Чисельного Визначення Динамічних Характеристик Лопаті Повітряного Гвинта З Композиційного Матеріалу

Morozov

2024

aktt

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“…Aerodynamic models of standard propellers and quadrotors have been established and well developed [38], [39], [40]. The most important factors of aerodynamic parameters, the forces, including the normal force (F n ), tangential force (F t ), lift force (F l ), and drag force (F d ) [see Fig.…”

Section: A Revisit Of the Aerodynamic Model Of A Classical Propellermentioning

confidence: 99%

TomboPropeller: Bioinspired Deformable Structure Toward Collision-Accommodated Control for Drones

et al. 2023

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There is a growing need for vertical takeoff and landing vehicles, including drones, which are safe to use and can adapt to collisions. The risks of damage by collision, to humans, obstacles in the environment, and drones themselves, are significant. This has prompted a search into nature for a highly resilient structure that can inform a design of propellers to reduce those risks and enhance safety. Inspired by the flexibility and resilience of dragonfly wings, we propose a novel design for a biomimetic drone propeller called Tombo propeller. Here, we report on the design and fabrication process of this biomimetic propeller that can accommodate collisions and recover quickly, while maintaining sufficient thrust force to hover and fly. We describe the development of an aerodynamic model and experiments conducted to investigate performance characteristics for various configurations of the propeller morphology and related properties, such as generated thrust force, thrust force deviation, collision force, recovery time, lift-to-drag ratio, and noise. Finally, we design and showcase a control strategy for a drone equipped with Tombo propellers that collides in midair with an obstacle and recovers from collision continuing flying. The results show that the maximum collision force generated by the proposed Tombo propeller is less than two-thirds that of a traditional rigid propeller, which suggests the concrete possibility to employ deformable propellers for drones flying in a cluttered environment. This research can contribute to the morphological design of flying vehicles for agile and resilient performance.

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Add force and/or change underlying projection method to improve accuracy of explicit Robin-Neumann and fully decoupled schemes for the coupling of incompressible fluid with thin-walled structure

Huang¹

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Dynamic behavior of composite marine propeller blades

Cited by 3 publications

References 146 publications

Метод Чисельного Визначення Динамічних Характеристик Лопаті Повітряного Гвинта З Композиційного Матеріалу

Метод Чисельного Визначення Динамічних Характеристик Лопаті Повітряного Гвинта З Композиційного Матеріалу

TomboPropeller: Bioinspired Deformable Structure Toward Collision-Accommodated Control for Drones

Add force and/or change underlying projection method to improve accuracy of explicit Robin-Neumann and fully decoupled schemes for the coupling of incompressible fluid with thin-walled structure

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