• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.10
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• pp.34-39
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• 2003

Morphing wing sections actuated by piezoceramic actuator LIPCA have been designed and their actuation displacements estimated by using the therml analogy and MSC/NASTRAN based on the linear elasticity. The wing sections are fabricated as the design and tested for evaluation. Measured actuation displacements were larger than the estimated values mainly due to the material non-linearity of the PIT wafer. The morphing wing sections can be used for control surfaces of small scale UAVs or MAVs.

• Composites Research
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• v.30 no.1
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• pp.15-20
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• 2017

In this study, LIPCA-S2 actuator with a piezoelectric single crystal layer and a carbon/epoxy layer was designed and evaluated to increase actuation performance of piezo-composite unimorph actuator. A curvature change model generated by the induced strain of a piezoelectric layer was used to predict the tip displacement of the piezo-composite unimorph cantilever. However, we found that there was big difference between the predicted and the measured tip displacement of LIPCA-S2 cantilever actuator when we used the previous linear prediction model. A new prediction model considering the change of piezoelectric strain coefficient and elastic modulus for the compression stress variation of the PMN-29PT single crystal layer was used and it was found that the difference between the predicted and the measured tip displacement reduced considerably.

• Journal of KSNVE
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• v.5 no.3
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• pp.292-302
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• 1995

압전재료를 이용한 능동진동제어에 관한 연구동향과 연구결과를 살펴보았다. 능동 진동제어에 사용되고 있는 감지기/작동기들 중 압전세라믹은 몇 가지 장점을 지니고 있어 그 적용에 관한 연구가 활발하게 진행되고 있는 것이 현실이며 실제 구조 물로의 적용이 이루어지고 있다. 압전세라믹을 이용한 진동제어는 박판으로 이루어진 국부구조물의 진동제어에 적합하며 그래서 자동차의 진동소음제어, 위성체 태양판의 진동제어에 사용할 수 있고 또한 겹쳐놓은 형태의 압전세라믹은 트러스 구조물의 능동 멤버로 활용할 수 있다. 이렇게 겹쳐놓은 압전세라믹 구조는 진동 고립(vibration isolation)을 원하는 장비의 지지대로 사용할 수 있어 그 응용분야가 넓다. 최근까지 도 압전세라믹을 이용한 진동제어는 주로 외팔보, 또는 평판과 같은 단순한 기하학적 형상을 가진 구조물에 국한되어 연구가 진행되어 왔고 제어기법 또한 그동안 전기 제어분야에서 개발되어 온 기법들을 적용하는 현상을 보였는데 구조물의 자유도가 무한대임을 고려할때 앞으로 구조물에 합당한 제어기법의 개발이 요망된다고 하겠다. 이 논문에서 선보인 PPF와 SRF 제어 기법은 필자가 간단히 회로를 구성하여 실험을 수행하였는데 압전재료의 진동제어 기법으로 단순하면서도 효율적인 제어기법이라고 말할 수 있다. 압전재료를 이용한 진동제어에 관한 국내의 연구활동이 미미한 상태 이으로 이분야에 대한 연구자들의 관심을 모을 필요가 있다. 압전세라믹 감지기와 작동기의 설치는 그동안 압전세라믹 판을 직접 구조물에 접착시킨 형태로 진행되었 는데 새로운 형태의 압전세라믹 작동기의 개발이 시급하다. 이는 높은 전압을 필요로 하는 진동제어는 필수적으로 커다란 부대시설을 요구하게 됨으로 전압을 높이지 않고 도 진동제어를 효율적으로 할 수 있는 압전세라믹의 제조가 필요하다고 하겠다. 필자 는 이런 목적으로 다층 압전세라믹(multilayer piezoceramic plate)을 제작한 적이 있었는데 실험결과는 신통치 않았다. 또한 압전세라믹을 길고 얇은 조각으로 잘라 사용하는 방법로 있었으나 세라믹의 절단시 다이아몬드 컷터를 사용해야 되어 제작이 곤란했다. 또한 압전세라믹이 부서지기 쉬운점을 개선한다면 진동제어에 있어 아주 효과적인 감지기/작동기가 될 수 있을 것이다.

• Journal of KSNVE
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• v.6 no.1
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• pp.11-19
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• 1996

지금까지의 항공기 날개에 공력 탄성학적 제어를 위해 압전재료를 작동기로 사용하는 연구는 아직은 완전하지 못하지만 실용화 가능성을 조사하기 위해 집중적인 투자가 행해지고 있다. 본 글에서 언급한 예 외에도 압전재를 이용 날개의 익형을 능동적으로 조절함으로써 천음속에서의 저항을 줄이기 위한 연구(transonic drag reduction with piezos), 압전재로 작동하는 제어면을 부착하여 헬리쿱터 블레이드 의 진동을 제어하기 위한 실험적 연구, 항공기 외부 장착물에 의해 발생되는 불안정 성을 제어하기 위한 압전작동기를 사용한 pylon decoupler 설계 등 다양한 분에에서 연구가 되고 있다. 하지만 아직까지는 제어에 필요한 충분한 제어력을 얻는 문제, 주 구조물과 압전재료의 강성도의 차이, 가용한 압전재의 실용화, 내구성 문제 등 항공 기에의 응용을 위한 새로운 재료의 개발이 요구되고 있다. 그리고 사용에 필요한 전력을 공급하는 문제는 지상에서 작동되는 시스템과는 달리 항공기에서는 해결해야 될 큰 문제점이며, 이에 대한 연구가 요구되고 있으며, 실용 가능성이 보일 경우 재료의 내구성, 제어 성능, 번개 등 외력에 대한 손상 예측 등 광범위한 연구가 이어 질 것으로 예측된다.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.16 no.2
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• pp.183-195
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• 2003

In this study, the method of the finite element modeling for free vibration control of beam-type smart structures with bonded plate-type piezoelectric sensors and actuators is proposed. Constitutive equations for the direct piezoelectric effect and converse piezoelectric effect of piezoelectric materials are considered. By using the variational principle, the equations of motion for the smart beam finite element are derived. The proposed 2-node beam finite element is an isoparametric element based on Timoshenko beam theory. Therefore, by analyzing beam-type smart structures with smart beam finite elements, it is possible to simulate the control of the structural behavior by applying voltages to piezoelectric actuators and monitoring of the structural behavior by sensing voltages of piezoelectric sensors. By using the smart beam finite element and constant-gain feed back control scheme, the formulation of the free nitration control for the beam structures with bonded plate-tyPe Piezoelectric sensors and actuators is proposed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.11
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• pp.1063-1071
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• 2008

A piezoceramic unimoph actuator can produce a relatively larger actuation force and actuation displacement when a proper compressive load is applied during operation, because the compressive stress causes material nonlinear behavior in the piezoceramic layer and triggers mechanical buckling. In this paper, we examined effects of the actuator under compression on the flapping angle and aerodynamic force generation capability. Effects of wing shape and passive wing rotation angle on the aerodynamic force production were also investigated. The average vertical force acquired by a 2D CFD simulation for an artificial wing showed a good agreement with the measured one by the experiment.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.3
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• pp.37-44
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• 2004

This paper deals with the performance analysis of LIPCA(Light-weight Piezo-Composite actuator) including the material nun-linearity of the embedded 3203HD PZT wafer. For this analysis, we used a piezo-shell element code based on a nine-node assumed strain shell element formulation. The material non-linearity was implemented in the formulation due to a large observed discrepancy between the measured displacement and the computed actuation displacement based on the linear analysis. An experimentally extracted piezo-strain function of the PZT wafer and incremental formulation were incorporated into the linear finite element code to improve the accuracy of the estimated actuation displacement of the LIPCA. The non-linear piezo-shell program was used to predict the non-linear performance of the LIPCA. The simulated actuation displacement from the non-linear code showed much better agreement with the measured data.

• Transactions of the Korean Society of Mechanical Engineers
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• v.17 no.1
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• pp.90-100
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• 1993

A finite element formulation of vibration control of a laminated plate with piezoelectric sensor/ actuators is presented. Classical lamination theory with the induced strain actuation and Hamilton's principle are used to formulate the equations of motion of the system. The total charge developed on the sensor layer is calculated from the direct piezoelectric equation. The equations of motion and the total charge are discretized with 4 node, 12 degrees of freedom quadrilateral plate bending elements with one electrical degree of freedom. The mass and stiffness of the piezoelectric layer are introduced by treating them as another layer in laminated plate. Piezoelectric sensor/actuators are distributed, but discrete due to the geometry of electrodes. By defining an i.d. number of electrode for each element, modelling of electrodes with variable geometry can be achieved. The static response of a piezoelectric bimorph beam to electrical loading and sensor voltage to given displacement are calculated. For a laminated plate under the negative velocity feedback control, the direct time response by the Newmark-.betha. method and damped frequencies and modal damping ratios by modal state space analysis are derived.

• Composites Research
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• v.16 no.2
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• pp.41-47
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• 2003

This paper is concerned with the performance evaluation and comparison analysis fur several kinds of LIPCA (Lightweight Piezo-Composite Actuator) device system. LIPCA device system is composed of a piezoelectric ceramic layer and fiber reinforced light composite layers, typically a PZT ceramic layer was sandwiched by a top fiber layer with low CTE (coefficient of thermal expansion) and base layers with high CTE. To investigate the effect of lay-up structure of the LIPCA on the actuating performance, four kinds of actuator with different lay-up stacking sequence were designed, manufactured, and tested. The performance of each actuator was evaluated using an actuator test system consisted of an actuator supporting jig, a high voltage actuating power supplier, and a non-contact laser measuring system. From the comparison of the performance of the LIPCA prototypes, it was found that the actuator with higher coefficient of unimorph actuator can generate larger actuating displacement.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.6
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• pp.35-41
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• 2006

In this paper, we focus on improving the performance of the piezoelectric diaphragms of valveless micropumps. A circular lightweight piezoelectric composite actuator (LIPCA) with a high level of displacement and output force has been developed for piezoelectrically actuated micropumps. We used numerical and experimental methods to analyze the characteristics of the actuator to select optimal design. With the developed circular LIPCA, we fabricated a valveless micropump by photo-lithography and PDMS molding techniques. The displacement of the diaphragm, the flow rate and the back pressure of the micropump were evaluated and discussed. With a semi-empirical method, the flow rate with respect to driving frequency was predicted and compared with experimental one. The test results confirm that the circular LIPCA is a promising candidate for micropump application and can be used as a substitute for a conventional piezoelectric actuator diaphragm.