• 대한교통학회지
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• 제22권4호
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• pp.147-158
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• 2004

SWP(Stochastic Wave Propagation: 확률파장전파) 모형은 Cellular Automata(CA) 이론을 기반으로한 간략한 차량모형을 이용하여 개별차량의 확률적 형태와 혼잡의 전파를 모사하고, 통계물리학을 기반으로 교통류를 거시적으로 해석한다. SWP모형은 이산적 시공간 구조와 정수형 자료를 이용한 프로그램 지향적 모형구조를 가지며 연산수행속도가 빨라 대규모 가로망의 실시간 시뮬레이션을 가능하게 하였다. 그러나 비현실적인 충돌회피과정으로 인한 자연발생적 혼잡(Spontaneous jam)의 형성 때문에 미시적으로는 혼잡내에서 잠금현상(Lockup)이 발생하여 혼잡내 차량의 저속을 설명할 수 없고, 거시적으로는 혼잡의 밀도와 전파속도를 설명하기 어렵다는 한계를 가지고 있다. 본 연구에서는 비현실적인 차량의 정지과정을 보다 현실적으로 모사하기 위한 정지조작규칙(SMR: Stopping Maneuver Rule)과 혼잡내에서 차량의 낮은 가속을 설명하기 위한 저가속규칙(LAR: Low Acceleration Rule)을 기존의 SWP모형인 NaSch모형에 추가하였다. 이를 통해 미시적으로 보다 현실적인 차량의 정지과정을 모사하면서 혼잡내에서 잠금현상을 방지하고, 거시적으로 혼잡의 밀도와 전파속도를 설명함으로써 보다 다양하게 연속 교통류를 구현하는 모형을 구축하였다.

• 한국항행학회논문지
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• 제25권1호
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• pp.1-7
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• 2021

무인항공기의 운항에 필수적인 탐지 회피 시스템은 침입기를 감지하여 위험을 벗어나는 데에 필요한 선회 또는 상승/하강 기동의 범위를 제시하여 준다. 본 연구에서는 탐지 회피 알고리즘으로 NASA에서 개발한 DAIDALUS (detect and avoid alerting logic for unmanned systems)를 활용하였다. DAIDALUS는 회피 기동의 범위만을 보여주기 때문에, 실제로 기동의 정도와 방향, 그리고 회피 후 원래 경로나 임무로 복귀하는 시점은 무인항공기 조종사의 결정 사항이다. 이는 실제로 조종사가 개입하는 실시간 HiTL(human-in-the loop) 시뮬레이션에서는 유용하나, 조종사의 개입 없이 시뮬레이션을 진행해야 하는 배속 시뮬레이션에서는 조종사의 의사결정 모델이 필요하다. 본 연구에서는 DAIDALUS 결과를 바탕으로 기동하는 조종사의 의사결정 모델을 제시하고 이를 RTCA (radio technical commission for aeronautics) MOPS (minimum operational performance standards)에서 제시하는 표준 조우 벡터를 이용하여 검증하였다. 조우 형상에 따라 최대 위험도가 달라지지만, loss of well clear 상황은 발생하지 않았다. 이러한 모델은 무인항공기가 포함된 대규모 교통량에 대한 배속 시뮬레이션에서 유용하게 활용될 수 있을 것이다.

• 한국전산유체공학회지
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• 제11권3호
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• pp.22-27
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• 2006

Flow around a guided missile in high maneuver, i.e. at a high angle of attack, shows complex phenomena. It is well known that even in geometrically symmetric conditions the flow around a missile at high angles of attack can generate unexpected large side forces and yaw moments due to asymmetric vortices. In this paper, a CFD code (FLUENT) based on the Navier-Stokes equations was used for the numerical analysis to find a suitable numerical mechanism for generation of asymmetric vortices. It is shown that a numerical technique of applying different surface roughness to a specific area of the missile nose surface gives the best fit in comparison with the experimental results. In addition, a numerical investigation of variations of side forces and pressure distributions with angle of attack and roll angle was conducted for the purpose of identifying the source of vortex asymmetries.

• 한국군사과학기술학회지
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• 제13권3호
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• pp.343-348
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• 2010

Recently, unmanned electric vehicles are increasingly interested among all of the world since they can provide low exhaust gas, high efficiency and high mobility. To exploit their silent maneuver and high mobility, unmanned electric vehicles have been developed since early 1980's for military. However, it is not easy to design and control a power system satisfying operating duration and mobility performance requirements based on various mission profiles for military use under the conditions of limited space and weight. Moreover it is also necessary to prevent over-charge, over-discharge and voltage unbalance between cells of battery to secure high voltage battery which is serially connected with muti-cells. In this paper, we presents power control and optimal management method for the dog-horse robot which adopts a electric power system and suggests a guide-line to manage and control to secure high voltage battery.

• 대한조선학회지
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• 제21권1호
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• pp.3-12
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• 1984

Up to now, it has been common to treat the maneuvering motion of a ship as a 3-degree-freedom motion i.e. surge, sway and yaw on the sea surface, for the simplicity and mathematical calculation, and it is quite acceptable in the practical point of view. Meanwhile, considering the maneuverability of a ship under the special conditions such as in irregular waves, in wind or at high speed with small GM value, it is required that roll effect must be considered in the equation of ship motion. In this paper the author tried to build up the 4-degree-freedom motion equation by adding roll. And then, applying the M.M.G.'s mathematical model and with captive model test results the roll-coupled hydrodynamic derivatives were found. With these the author could make some simulating program for turning and zig-zag steering. Through the computer simulations, the effect of roll to the ship maneuver became clear. The effect of the wind force to the maneuverability was also found. Followings are such items that was found. 1) When roll is coupled in the maneuvering motion, the directional stability becomes worse and the turning diameter becomes smaller as roll becomes smaller as roll becomes larger. 2) When maneuver a ship in the wind, the roll becomes severe and the directional stability becomes worse. 3) When a ship turns to the starboard side, the wind blowing from 90 degree direction to starboard causes the largest roll and the largest turning diameter, and the wind from other direction doesn't change the turning diameter. 4) When a ship is travelling with a constant speed with rudder amidship, if steady wind blows from one direction, the ship turns toward that wind. This phenomenon is observed in the actual seaways.

• Journal of Gastric Cancer
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• 제19권4호
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• pp.473-483
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• 2019

Surgical therapy for adenocarcinoma of the esophagogastric junction II requires distal esophagectomy, in which a transhiatal management of the lower esophagus is critical. The 'dorsal track control' (DTC) maneuver presented here facilitates the atraumatic handling of the distal esophagus, in preparation for a circular-stapled esophagojejunostomy. It is based on a ventral semicircular incision in the distal esophagus, with an intact dorsal wall for traction control of the esophagus. The maneuver facilitates the proper placement of the purse-string suture, up to its tying (around the anvil), thus minimizing the manipulation of the remaining esophagus. Furthermore, the dorsally-exposed inner wall surface of the ventrally-opened esophagus serves as a guiding chute that eases anvil insertion into the esophageal lumen. We performed this novel technique in 21 cases, enabling a safe anastomosis up to 10 cm proximal to the Z-line. No anastomotic insufficiency was observed. The DTC technique improves high transhiatal esophagojejunostomy.

• 한국항공우주학회지
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• 제39권10호
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• pp.935-945
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• 2011

네 개의 반작용휠과 두 개의 제어모멘트자이로를 이용하여 X축 또는 Y축으로 위성을 고기동 시키는 자세제어방법에 대해서 연구해보았다. 일반적인 위성은 동일한 구동기들을 사용하므로 위성자세제어기를 먼저 설계하고 여기에서 나온 토크를 각 구동기에 할당하면 된다. 하지만 우리 위성은 출력토크 차이가 큰 반작용휠과 제어모멘트자이로로 이루어져 있기에 이러한 방법을 적용하는데 어려움이 있다. 이에 본 논문에서는 구동기 출력토크명령설계에 위성자세제어기를 포함시키는 방법을 사용하였다. 시뮬레이션을 통하여, 설계된 제어기법이 위성을 고기동 시키는 것을 확인하였다.

• 한국응용과학기술학회지
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• 제37권2호
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• pp.296-302
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• 2020

The purpose of this study was to assess knee joint loading in the target knee during a golf swing compared to loading rates of high impact activities such as cutting and drop landings. Nine healthy competitive golfers completed golf swings with the target foot both straight and externally rotated 30 degrees, as well as drop landings and cutting maneuvers. Motion capture data was collected at 240 Hz and ground reaction force data was collected at 2400 Hz. The frontal and transverse knee moments were examined using repeated measures ANOVA through SPSS. The abduction moments were higher in golf swings as compared to the other high impact activities (p=.010), while the external rotation moments were lower (p=.003). There were no significant differences between externally rotated and neutral golf swings. These results suggest moments applied to the knee during a golf swing are similar to those applied during a high impact activity.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1996년도 Proceedings of the Korea Automatic Control Conference, 11th (KACC); Pohang, Korea; 24-26 Oct. 1996
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• pp.24.1-24
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• 1996

The development of future aircraft that involves the expanded flight envelop will place increased performance requirements on the design of the flight control system. Maneuvering areas are expanding into flight envelopes characterized by significantly larger levels of modeling uncertainty than encountered in present flight control designs. Conventional flight control techniques that ignore the effects of large parameter variations, modeling uncertainties and nonlinearities, will likely produce designs with poor performance and robustness. Recent advances in modern control theories called advanced control theories, most notably the H$\_$.inf./ synthesis technique, adaptive control and neural network application, offer the promise of a design technique that can produce both high performance and robust controllers for next generation aircraft. This special lecture will survey the recent development in advanced flight control and review the possible application of advanced control theories.

• International Journal of Automotive Technology
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• 제6권4호
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• pp.359-365
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• 2005

The absolute longitudinal speed of a vehicle is estimated by using data from an accelerometer of the vehicle and wheel speed sensors of a standard 50-tooth antilock braking system. An intuitive solution to this problem is, 'When wheel slip is low, calculate the vehicle velocity from the wheel speeds; when wheel slip is high, calculate the vehicle speed by integrating signal of the accelerometer.' The speed estimator weighted with fuzzy logic is introduced to implement the above concept, which is formulated as an estimation method. And the method is improved through experiments by how to calculate speed from acceleration signal and slip ratios. It is verified experimentally to usefulness of estimation speed of a vehicle. And the experimental result shows that the estimated vehicle longitudinal speed has only a $6\%$ worst-case error during a hard braking maneuver lasting a few seconds.