• 제목/요약/키워드: Aircraft Vibration

검색결과 349건 처리시간 0.026초

Dynamic modeling of nonlocal compositionally graded temperature-dependent beams

  • Ebrahimi, Farzad;Fardshad, Ramin Ebrahimi
    • Advances in aircraft and spacecraft science
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    • 제5권1호
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    • pp.141-164
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    • 2018
  • In this paper, the thermal effect on buckling and free vibration characteristics of functionally graded (FG) size-dependent Timoshenko nanobeams subjected to an in-plane thermal loading are investigated by presenting a Navier type solution for the first time. Material properties of FG nanobeam are supposed to vary continuously along the thickness according to the power-law form and the material properties are assumed to be temperature-dependent. The small scale effect is taken into consideration based on nonlocal elasticity theory of Eringen. The nonlocal equations of motion are derived based on Timoshenko beam theory through Hamilton's principle and they are solved applying analytical solution. According to the numerical results, it is revealed that the proposed modeling can provide accurate frequency results of the FG nanobeams as compared to some cases in the literature. The detailed mathematical derivations are presented and numerical investigations are performed while the emphasis is placed on investigating the effect of the several parameters such as thermal effect, material distribution profile, small scale effects, aspect ratio and mode number on the critical buckling temperature and normalized natural frequencies of the temperature-dependent FG nanobeams in detail. It is explicitly shown that the thermal buckling and vibration behaviour of a FG nanobeams is significantly influenced by these effects. Numerical results are presented to serve as benchmarks for future analyses of FG nanobeams.

Disturbance observer based anti-disturbance fault tolerant control for flexible satellites

  • Yadegari, Hamed;Khouane, Boulanouar;Yukai, Zhu;Chao, Han
    • Advances in aircraft and spacecraft science
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    • 제5권4호
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    • pp.459-475
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    • 2018
  • In the field of aerospace engineering, accurate control of a spacecraft's orientation is often very important to mission success. Therefore, attitude control is a technically plentiful and extensively studied subject in controls literature during recent decades. This investigation of spacecraft attitude control is assumed to address two important aspects of the problem solutions. One sliding mode anti-disturbance control for utilization of faulty actuator components and another one disturbance observer based control to improve the pointing accuracy in the absence of anti-vibration equipment for the elastic appendages like a solar panel. Simultaneous occurrence of vibration due to flexible appendages and reaction degradation due to failure in attitude actuators complicates this case. The advantage of this method is acquisition proper control by the combination of disturbance observer and sliding mode compensation that form a fault tolerant control for the concerned satellite attitude control system. Furthermore, the proposed composite method indicates that occurrence the failure in actuators and even elastic solar panel vibration effect may be handled directly without reconfiguring the control components or providing piezoelectric devices. It's noteworthy, attitude quaternion and angular velocity commands are robustly tracked via controllers to become inclined to zero.

항공기용 하니콤 트림판넬의 능동제어 (Active Control of Honeycomb Trim Panels for Aircrafts)

  • ;정의봉;홍진숙
    • 한국소음진동공학회:학술대회논문집
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    • 한국소음진동공학회 2006년도 추계학술대회논문집
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    • pp.464-473
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    • 2006
  • This paper summarises theoretical and experimental work on the feedback control of sound radiation from honeycomb panels using piezoceramic actuators. It is motivated by the problem of sound transmission in aircraft, specifically the active control of trim panels. Trim panels are generally honeycomb structures designed to meet the design requirement of low weight and high stiffness. They are resiliently-mounted to the fuselage for the passive reduction of noise transmission. Local coupling of the closely-spaced sensor and actuator was observed experimentally and modelled using a single degree of freedom system. The effect of the local coupling was to roll-off the response between the actuator and sensor at high frequencies, so that a feedback control system can have high gain margins. Unfortunately, only relatively poor global performance is then achieved because of localisation of reduction around the actuator. This localisation prompts the investigation of a multichannel active control system. Globalised reduction was predicted using a model of 12 channel direct velocity feedback control. The multichannel system, however, does not appear to yield a significant improvement in the performance because of decreased gain margin.

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초음파 진동에 따른 CFRP의 출구 구멍 버 생성 (The Exit Hole Burr Generation of CFRP with Ultrasonic Vibration)

  • 원성재;이상평;박기문;고태조
    • 한국기계가공학회지
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    • 제16권1호
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    • pp.134-140
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    • 2017
  • CFRP has many industrial applications due to its low weight and high strength properties. CFRP is a composite material composed of carbon fibers embedded in a polymer matrix; it provides excellent resistance to fatigue wear, corrosion, and breakage due to fatigue. It is increasingly demanded in aircraft, automotive, and medical industries due to its superior properties to aluminum alloys, which were once considered the most suitable for specific applications. The basic machining methods of CFRP are drilling and route milling. However, in the case of drilling, the delamination of each layer, uncut fiber, resin burning, spalling, and exit burrs are barriers to successful application. This paper investigates the occurrence of exit burrs when drilling holes with ultrasonic vibration. Depending on design parameters such as the point angle, the characteristics of hole drilling were identified and appropriate machining conditions were considered.

지지구조물과 부시스템으로 이루어진 계의 동적 특성 (Dynamic Characteristics of a System Composed of a Supporting Structure and Subsystems)

  • 이건명
    • 한국소음진동공학회논문집
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    • 제26권4호
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    • pp.406-411
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    • 2016
  • 지지구조물 위의 부시스템으로 이루어진 계의 고유 진동수와 모드형을 근사적으로 구하는 식을 유도하였다. 이 계는 이산계로 모형화되었고, 부시스템의 질량은 지지구조물의 질량에 비하여 매우 작다고 가정하였다. 기본진동수는 지지구조물에 대응하고, 고차 진동수는 각각의 부시스템에 대응한다는 것이 밝혀졌다. 또한 지지구조물이 조화력에 의해 가진될 때 지지구조물과 부시스템의 진동 진폭 사이의 관계를 유도하였다.

전투기 레이다용 전자부품 수명평가를 위한 Steinberg 피로한계식 적용방안 연구 (A Study on the Application Method of Steinberg Fatigue Limit Equation for Electronic Part Life Assessment of Fighter Aircraft Radar)

  • 김덕주;하승룡;강민성;허재훈
    • 한국군사과학기술학회지
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    • 제23권4호
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    • pp.319-327
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    • 2020
  • In this study a methodology to evaluate fatigue life of the electronic parts for the fighter radar unit under random vibration loading is presented. To do this, one parameter for the 3-σ RMS quation of Steinberg fatigue model is modified to come up with a printed circuit board(PCB) with multiple electronic parts, while fundamental frequency and dynamic deflection of the PCB are calculated from a MATLAB based finite element computer code. For the RIFA structure selected in this study, the 3-σ RMS fatigue limit displacement is reduced to 0.741 times as much as the Steinberg model. This investigation allows to assess the life of multiple electronic parts mounted on the PCB with reinforced metal cover/body showing non-sinusoidal deflection patterns.

A novel first order refined shear-deformation beam theory for vibration and buckling analysis of continuously graded beams

  • Bekhadda, Ahmed;Cheikh, Abdelmadjid;Bensaid, Ismail;Hadjoui, Abdelhamid;Daikh, Ahmed A.
    • Advances in aircraft and spacecraft science
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    • 제6권3호
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    • pp.189-206
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    • 2019
  • In this work, a novel first-order shear deformation beam theory is applied to explore the vibration and buckling characteristics of thick functionally graded beams. The material properties are assumed to vary across the thickness direction in a graded form and are estimated by a power-law model. A Fourier series-based solution procedure is implemented to solve the governing equation derived from Hamilton's principle. The obtained results of natural frequencies and buckling loads of functionally graded beam are checked with those supplied in the literature and demonstrate good achievement. Influences of several parameters such as power law index, beam geometrical parameters, modulus ratio and axial load on dynamic and buckling behaviors of FGP beams are all discussed.

Dynamic characterization of 3D printed lightweight structures

  • Refat, Mohamed;Zappino, Enrico;Sanchez-Majano, Alberto Racionero;Pagani, Alfonso
    • Advances in aircraft and spacecraft science
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    • 제9권4호
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    • pp.301-318
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    • 2022
  • This paper presents the free vibration analysis of 3D printed sandwich beams by using high-order theories based on the Carrera Unified Formulation (CUF). In particular, the component-wise (CW) approach is adopted to achieve a high fidelity model of the printed part. The present model has been used to build an accurate database for collecting first natural frequency of the beams, then predicting Young's modulus based on an inverse problem formulation. The database is built from a set of randomly generated material properties of various values of modulus of elasticity. The inverse problem then allows finding the elastic modulus of the input parameters starting from the information on the required set of the output achieved experimentally. The natural frequencies evaluated during the experimental test acquired using a Digital Image Correlation method have been compared with the results obtained by the means of CUF-CW model. The results obtained from the free-vibration analysis of the FDM beams, performed by higher-order one-dimensional models contained in CUF, are compared with ABAQUS results both first five natural frequency and degree of freedoms. The results have shown that the proposed 1D approach can provide 3D accuracy, in terms of free vibration analysis of FDM printed sandwich beams with a significant reduction in the computational costs.

The Dynamics of Noise and Vibration Engineering Vibrant as ever, for years to come

  • Leuridan, Jan
    • 한국소음진동공학회:학술대회논문집
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    • 한국소음진동공학회 2010년도 춘계학술대회 논문집
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    • pp.47-47
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    • 2010
  • Over the past 20 years, constant progress in noise and vibration (NVH) engineering has enabled to constantly advance quality and comfort of operation and use of really any products - from automobiles to aircraft, to all kinds of industrial vehicles and machines - to the extend that for many products, supreme NVH performance has becomes part of its brand image in the market. At the same time, the product innovation agenda in the automotive, aircraft and really many other industries, has been extended very much in recent years by meeting ever more strict environmental regulations. Like in the automotive industry, the drive towards meeting emission and CO2 targets leads to very much accelerated adoption of new powertrain concepts (downsizing of ICE, hybrid-electrical...), and to new vehicle architectures and the application of new materials to reduce weight, which bring new challenges for not only maintaining but further improving NVH performance. This drives for innovation in NVH engineering, so as to succeed in meeting a product brand performance for NVH, while as the same time satisfying eco-constraints. Product innovation has also become increasingly dependent on the adoption of electronics and software, which drives for new solutions for NVH engineering that can be applied for NVH performance optimization of mechatronic products. Finally, relentless pressure to shorten time to market while maintaining overall product quality and reliability, mandates that the practice and solutions for NVH engineering can be optimally applied in all phases of product development. The presentation will first review the afore trends for product and process innovation, and discuss the challenges they represent for NVH engineering. Next, the presentation discusses new solutions for NVH engineering of products, so as to meet target brand values, while at the same time meeting ever more strict eco constraints, and this within a context of increasing adoption of electronics and controls to drive product innovation. NVH being very much defined by system level performance, these solutions implement the approach of "Model Based System Engineering" to increase the impact of system level analysis for NVH in all phases of product development: - At the Concept Phase, to be able to do business case analysis of new product concepts; to arrive at an optimized and robust product architecture (e.g. to hybrid powertrain lay-out, to optimize fuel economy); to enable target cascading, to subsystem and component level. - In Development Phase, to increase realism and productivity of simulation, so as to frontload virtual validation of components and subsystems and to further reduce reliance on physical testing. - During the final System Testing Phase, to enable subsystem testing by a combination of physical testing and simulation: using simulation models to simulate the final integration context when testing a subsystem, enabling to frontload subsystem testing before final system integration is possible. - To interconnect Mechanical, Electronical and Controls engineering, in all phases of development, by supporting model driven controls engineering (MIL, SIL, HIL). Finally, the presentation reviews examples of how LMS is implementing such new applications for NVH engineering with lead customers in Europe, Asia and US, with demonstrated benefits both in terms of shortening development cycles, and/or enabling a simulation based approach to reduce reliance on physical testing.

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부분구조합성법을 이용한 전차량 모델의 진동 특성 분석 (Analysis of Vibration Characteristics of a Full Vehicle Model Using Substructure Synthesis Method)

  • 김범석;김봉수;유홍희
    • 대한기계학회논문집A
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    • 제34권5호
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    • pp.519-525
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    • 2010
  • 승용 차량과 항공기와 같은 대형 구조물에 대한 해석에는 유한요소법이 일반적으로 사용되고 있다. 그러나 대형 구조물을 유한요소로 모델화 하여 해석하는 경우에는 자유도의 수가 수천에서 수만에 이르게 되어 이를 직접 해석하기 위해서는 많은 시간과 노력이 필요하다. 따라서 차량 모델과 같은 대형 복잡 구조물을 효율적으로 해석하기 위해 부분구조 합성법이 많이 사용되고 있다. 본 연구에서는 Craig-Bampton 방법을 이용한 전차량 모델링 방법을 제안하고 전차량 모델의 진동 특성을 분석하였다. 차량 모델을 구성하는 각 부분을 각각 부분구조 모델로 치환한 후 다시 합성하여 전차량 모델을 구성하였다. 또한, 서브프레임 주요 설계변수, 즉 마운트 위치나 프레임 크기의 편차가 전체 시스템의 모드 특성의 통계적 변화에 미치는 영향을 살펴보았다.