• Journal of the Society of Naval Architects of Korea
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• v.44 no.2 s.152
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• pp.180-188
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• 2007

In this paper the longitudinal control problem for the large WIG(wing-in-ground effect) craft is considered in the sense of the control augmentation system(CAS) derived by control surface of elevator. In order to achieve longitudinally stable systems, two modes of CAS are applied to the control systems which are pitch rate hold mode and pitch hold mode for steady flight. Since the employed CASs include the dynamic properties of the actuator time delay and the low pass filter, it provides the possible solution to be applicable to real systems. Nonlinear model simulations are fulfilled to investigate the effectiveness of the applied CASs with wind disturbance.

• 제어로봇시스템학회:학술대회논문집
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• 1997.10a
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• pp.1684-1687
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• 1997

A dynamic load simulator which can reproduce on-ground the hinge moment of aircraft control surface is and essential rig for the loaded performance test of aircraft test of aircraft acutation system. The hinge moment varies wide in the aricraft flight enveloped depending on specific flight condition and maneuvering status. To replicate the wide spectrum of this hinge moment variation within some accuracy bounds, a force controller is designed based on the Quantiative Feedback Theory (AFT). Through the analysis on hinge moment dynamics, a design specification for the force controller is suggested. The efficacy of QFT force controller is verivied by simulation, in which combined aricraft dynamics/flight control law and hydraulic actuation system dynamics of aircraft control surface are considered.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.25 no.3
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• pp.478-485
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• 2001

A dynamic load simulator(DLS) which can reproduce on-ground the aerodynamic hinge moment of control surface is an essential rig for the performance and stability test of aircraft actuation system. By setting up load actuator as counter acting with the control surface driving actuator and designing an appropriate force control system for load actuator, DLS can be mechanized. Obtaining an accurate mathematical model for the DLS is the first step to successfully design an aerodynamic load replicati on system. Two theoretical models are presented and tested for their validities with the experimental results, which turns out to be not successful. An alternative way of using system identification approaches in investigated to develop a good nominal model for DLS dynamics, and suitable uncertainty bounds for this nominal model are proposed with the consideration of experimental results.

• Journal of Aerospace System Engineering
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• v.6 no.3
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• pp.24-28
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• 2012

An actuator should be added to a existing control linkage to make manned aircraft to unmanned. But it is quiet difficult to synchronize actuator with control surface because non-linear error necessarily occurs when four-bar linkage acts in three dimensional motion. In addition, in point of controller design view, while a real-time model needs the control surface deflection as its input, controller needs the actuator command as its output. Hence, the relation between both should be investigated. In this paper, the mathematical relation between actuator and control surface deflection investigated by kinematic analysis of a plant aircraft. The performance margin of the selected actuator also was verified.

• Journal of Aerospace System Engineering
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• v.5 no.1
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• pp.1-6
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• 2011

It is very important to correctly set control surface linkage. But a lot of bad setting case has been seen in especially remote controled airplanes and middle size UAVs. In this paper, a three dimensional linkage from control surface to deflection sensor was analyzed kinematically and a position analysis was simulated using algebraic algorithm in terms of nonlinear error of deflection angle. Three correct settings of the linkage came out of this research. One is two-dimensional motion, another is link ratio of 1 and the other is that effective lever of the control surface should be perpendicular to a pushrod in their neutral position.

• Journal of Aerospace System Engineering
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• v.3 no.3
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• pp.13-16
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• 2009

Aircraft flight control surfaces which are one of the most important elements of safety allow a pilot to adjust and control the aircraft's flight attitude. This paper is described of the control surface deflection angle measuring device. Data analysis through ground test and flight test can provide reliability of this device using the present system. It is also shown that measuring system is capable of detecting failure of control surfaces.

• Aerospace Engineering and Technology
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• v.1 no.2
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• pp.11-18
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• 2002

The structural load analysis of 50m class airship was performed. The airship maneuver condition for analysis was defined. Aerodynamic, inertia and buoyance models were built. Control surface motion to make defined maneuver condition were calculated. Load factors, load, shear and bending moment envelops were developed for full airship and tailwing. Gondola design loads were developed.

• Proceedings of the Korea Information Processing Society Conference
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• 2009.11a
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• pp.83-84
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• 2009

최근 다양한 센싱장치와 HCI 디바이스를 결합하여 로봇이나 기계장치를 구동하려는 연구가 활발하게 진행되고 있다. 또한 기존의 RC방식의 무인비행체 조작은 관련분야의 전문성을 필요로 할 만큼 접근하기 어려운 면이 있었다. 이에 본 논문에서는 소형 무인비행체(UAV)의 움직임 제어를 위해 데이터 글로브의 손가락 구부러짐을 인식하여 이를 통해 무인비행체를 조작하는 원격조종장치에 관한 시스템 구조 및 프로토콜을 제안한다. 이 시스템을 통해 비전문가로 하여금 무인비행체의 접근성을 높이며 다양한 분야에 활용 할 수 있는 가능성을 제시하고자 한다. 이를 위해 데이터 글로브의 센싱 데이터에 대한 조합 및 해석방식을 정의하고, 이를 데이터 글로브의 손가락 구부러짐 해석에 적용하였다. 또한 조합된 명령신호를 전송하는 무인비행체의 구동 제어를 위한 비동기 Uplink 프로토콜을 제안하였다.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2015.10a
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• pp.100-103
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• 2015

본 연구에서는 선박의 내항 및 조종성능평가를 위해 사용되는 2차원부가질량계수와 파랑감쇠계쉬를 desingularized indirect boundary integral method를 이용하여 주파수영역에서 계산하였다. 본 방법을 Rankine source를 유체경계면 전체에 분포하는 방법으로 수학적으로 간단하고 경계조건의 변경 및 적용이 용이하다는 장점이 있다. 하지만 물체표면, 자유수면 그리고 방사경계면의 계산영역 및 요소의 배치에 따라 계산정확도에 차이가 발생한다. 따라서 본 연구에서는 수치시험을 통해, 자유수면과 방사계면의 적절한 계산영역과 요소의 개수를 결정하였다. 계산의 정도와 효율성을 확보하기 위하여, 자유수면과 방사경계면의 계산영역과 요소의 분포를 파의주파수에 따라 달리 적용하였다. 본 연구에서 제안된 수치방법을 활용하여 계산된 동유체력과 실험에서 계측된 동유체력을 비교하여 본 방법의 정도를 확인하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.1
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• pp.59-66
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• 2022

In order to solve the problem of urban traffic congestion, Urban Air Mobility (UAM) concept using Electric Vertical Take-off and Landing (eVTOL) aircraft has been gaining popularity, and many domestic and international studies are underway. However, since these aircraft inevitably fly over densely populated areas, it is essential to ensure safety, which starts with accurately analyzing the crash risk. In this paper, the locations and impact speeds of crash are computed using six degree-of-freedom simulations of an eVTOL aircraft in a fixed-wing mode. System malfunction was modeled by a sudden loss of thrust with control surfaces being stuck during cruise. Because most of these eVTOL aircraft are still under development, a methodology of constructing a six degree-of-freedom dynamics model from generic specification is also developed. The results show that the crash locations are highly concentrated right under the aircraft within a square that has an edge length similar to the cruise altitude. Speed distribution is more complicated because almost identical crash locations can be achieved by two very different paths resulting in a large variation in the speeds.