• Journal of Aerospace System Engineering
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• v.12 no.1
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• pp.1-9
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• 2018

In this study, a hybrid control method that adjusts for the existing force control technique has been presented for consideration. The proposed hybrid control technique does away with the chattering phenomenon occurring in existing force control technique and provides high shock absorption efficiency. In order to design the controller for the landing gear with MR damper, the equation of motion of the landing gear was derived. The hybrid controller was designed after constructing a simulation model using Recur-Dyne, multi-body dynamic analysis software. The hybrid controller can reduce the maximum strut force and displacement based on the skyhook controller, and is able to get the high efficiency by making it work for the additional force control technique. In addition, an effective switching control technique and input shaping technique was applied to prevent the chattering in the drop simulation. Finally, the performance of the landing characteristics was evaluated throughout the various drop simulations.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.6
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• pp.530-536
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• 2016

The handling quality simulator including high fidelity flight mechanics model is indispensable component to design and verify the flight control system. Korea Aerospace Industries, LTD. (KAI) has been performing LCH (Light Civil Helicopter) core technology development program regarding automatic flight control system (AFCS) software development. And KAI has been developing flight mechanics model using FLIGHTLAB to design and evaluate the AFCS flight control law. This paper presents the handling quality assessment environment development results through the combining FLIGHTLAB with a legacy simulator. And this paper details the FLIGHTLAB model, application development process and FLIGHTLAB interface design. The developed handling quality assessment environment has been demonstrated with the ADS-33E hover and pirouette MTE (Mission Task Element) maneuver simulation.

• Proceedings of the Korea Water Resources Association Conference
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• 2019.05a
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• pp.266-266
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• 2019

금강의 주요 지류인 미호천과 갑천은 대전광역시와 청주시가 위치하고 있으며, 두 도시지역에서 유입되는 오염물질로 인하여 금강 본류에 높은 오염부하를 제공하고 있다. 따라서 본 연구에서는 3차원 수리동역학 모델인 EFDC 모델을 사용하여 미호천과 갑천의 수질개선이 금강의 수질에 미치는 효과를 분석하였다. 대상유역은 대청댐부터 백제보 까지 70km 구간이며, 모델의 격자는 Curvilinear-Orthogonal Coordinate를 사용하였으며 횡단방향 8개로 분할하여 총 6,698개의 격자로 구성하였다. 경계조건구성 및 모델의 보정은 국가정보 포털인 수자원관리종합정보시스템(WAMIS), 물환경정보시스템(WEIS), 국가기후데이터센터(data,kma,go,kr) 등에서 제공하는 유량, 수질, 기상 등 데이터를 활용하였으며, 모의 기간은 2017년이다. 수질의 보정은 대상유역 내 6곳의 수질 측정 지점에서 수행되었으며, 적합성 평가를 위해 R-square와 NSE(Nash-Sutcliffe Efficiency) 두 가지의 통계 지표를 활용하였다. 수질의 경우 TN, TP, TOC, Chl-a 순으로 평균 R-square값은 0.75, 0.51, 0.36, 0.57이고 평균 NSE (Nash-Sutcliffe Efficiency)값은 0.59, -0.18, -1.10, 0.27으로 모의 값과 실측값 사이의 상관관계는 TN에서 가장 높았으며 반대로 TOC는 가장 낮았다. 모의결과가 실측값을 정확히 반영하지는 못했지만, 수질의 평균적인 현상은 반영한 것으로 판단된다. 두 주요 지류의 수질이 동시에 15% 또는 30% 개선되었을 경우를 모의하여 금강 본류의 수질변화를 6곳의 수질 측정 지점에서의 실측값과 비교하여 분석하였다. 두 지류가 동시에 15%의 수질 개선 시에는 금강 본류 수질은 TN, TP, TOC, Chl-a 순으로 평균 11.80%, 7.90%, 8.63%, 7.04%의 개선되었으며, 30% 수질 개선 시에는 평균 23.66%, 15.92%, 17.36%, 14.26%의 개선되었다. 각 지점에서 고른 개선이 확인되었으며, 개선 효과는 TN이 가장 컸고, 반대로 Chl-a가 가장 적었다. 갑천과 미호천의 수질이 별개로 개선되었을 경우를 모의한 결과, 미호천의 개선이 갑천에 비해 금강의 수질 개선에 영향이 컸다. 이는 두 지류의 수질 농도는 비슷하나 갑천에 비해 유량이 많은 미호천의 오염 부하량이 높은 것으로 분석된다. 연구 결과 금강의 수질을 개선하기 위해서는 두 지류의 수질 개선이 필수적인 것으로 판단된다. 금강의 TN 농도는 두 지류의 영향이 가장 컸으며, 개선 효과는 Chl-a에서 가장 적었다. 또한 갑천에 비해 미호천이 금강 수질에 영향이 큼을 확인하였다.

• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
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• 2007.11a
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• pp.502-502
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• 2007

A catenary system should be designed to have an uniform elasticity over a span in order to maintain the lowest possible loss of contact between a pantograph and a contact wire. A elasticity uniformity of a catenary can be regarded as a important design factor used for predicting the current collection performance for a catenary. There are a couple of formulas to calculate the degree of elasticity uniformity of a catenary according to the literature survey. The effectiveness of these formulas is reviewed by performing catenary elasticity and loss of contact analysis for various different configurations of catenary systems using a beam element based FEM program. The results reveals that these formulas are not suitable to predict the current collection performance for a catenary. Therefore, a new formula based on the standard deviation of the elasticity over a span is proposed in this study. The analysis results show that the new formula for an elasticity uniformity of a catenary is very effective in predicting the current collection performance for a catenary.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.38 no.7
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• pp.751-756
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• 2014

The dynamic behavior of numerous grains interacting with each other can be easily observed. In this study, this dynamic behavior was analyzed based on the contact between numerous grains. The discrete element method was used for analyzing the dynamic behavior of each particle and the neighboring-cell algorithm was employed for detecting their contact. The Hertzian and tangential sliding friction contact models were used for calculating the contact force acting between the particles. A GPU-based parallel program was developed for conducting the computer simulation and calculating the numerous contacts. The dam break experiment was performed to verify the simulation results. The reliability of the program was verified by comparing the results of the simulation with those of the experiment.

• Composites Research
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• v.30 no.5
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• pp.323-330
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• 2017

In this study, multiscale analysis in which the information obtained from molecular dynamics simulation is applied to the continuum mechanics level is conducted to investigate the effects of clustering of silicon carbide nanoparticles reinforced into polypropylene matrix on mechanical behavior of nanocomposites. The elastic behavior of polymer nanocomposites is observed for various states of nanoparticulate agglomeration according to the model reflecting the degradation of interphase properties. In addition, factors which mainly affect the mechanical behavior of the nanocomposites are identified, and new index 'clustering density' is defined. The correlation between the clustering density and the elastic modulus of nanocomposites is understood. As the clustering density increases, the interfacial effect decreased and finally the improvement of mechanical properties is suppressed. By considering the random distribution of the nanoparticles, the range of elastic modulus of nanocomposites for same value of clustering density can be investigated. The correlation can be expressed in the form of exponential function, and the mechanical behavior of the polymer nanocomposites can be effectively predicted by using the nanoparticulate clustering density.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.5
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• pp.385-392
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• 2018

This paper suggests a new method to estimate the roll and pitch damping moment coefficients of a flying disc through sensor data from the onboard IMU module. This method can be easily performed than wind tunnel or computational fluid dynamics methods because it estimates aerodynamic coefficients simply after accumulating the inertial data through several repeated flight experiments. Estimated coefficients are applied to a simulator which is based on the flight dynamics of a flying disc. Finally, the predicted flight trajectory is compared with the true position provided by GPS, which demonstrated the validity of the proposed estimation method.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2009.05a
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• pp.180-185
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• 2009

Actuator-induced disturbance is one of the crucial factors of spacecraft attitude pointing and stability in fine attitude control problems. The control moment gyros (CMGs) are known as very attractive actuators from the point of high power and low weight. In order to develop a CMG as an actuator for fine controls, CMG-induced disturbances should be analyzed. Therefore, this paper aims to develop an analytic model and predict the effect of disturbances of CMGs by assuming static and dynamic imbalances. The proposed model is induced by the Lagrangian method on the basis of the small signal assumption. In this research, mechanical system of the CMG is designed and the main components of CMG are producted.

• Journal of Aerospace System Engineering
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• v.11 no.4
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• pp.22-29
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• 2017

A study is performed for the effective detection method of a fault which is occurred during operation in a small turbojet engine with non-linear characteristics used by unmanned air vehicle. For this study the non-linear dynamic model of the engine is derived from transient thermodynamic cycle analysis. Also for inducing real operation conditions the controller is developed associated with unscented Kalman filter to estimate noises. Sequential probability ratio test is introduced as a real time method to detect a fault which is manipulated for simulation as a malfunction of rotational speed sensor contaminated by large amount of noise. The method applied to the fault detection during operation verifies its effectiveness and high feasibility by showing good and definite decision performances of the fault.

• Tribology and Lubricants
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• v.35 no.5
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• pp.310-316
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• 2019

This paper presents two methods for designing a high-speed air spindle operated over the rotational speed of 50,000 rpm. The first method is an approximate method, which assumes a symmetric spindle shape even though it is not symmetric in reality. The second is an analysis of rotordynamics using beam and solid models. The approximate method can be used to calculate the bearing load capacities, stiffness and damping coefficients, stability of the shaft system, and response of the forced excitation from the unbalanced mass. Designers can use this method to determine the dimensions of the desired spindle at the first stage of the design. The more detailed behavior of the spindle can be calculated using the rotordynamics theory using beam and solid models based on the Finite Element Method. In this paper, a spindle, with two air bearings, one motor at the end, and two air thrust bearings, is newly developed. The solutions from the two rotordynamics theories are compared with the solution obtained using the approximate method. The three calculations are in agreement, and the procedure for the design of a spindle system, supported on the externally pressurized air bearings, ispresented and discussed.