• 기술사
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• 제32권5호
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• pp.118-125
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• 1999

Air pollutant emissions from airplane engines are estimated about 2 to 4 % of mobile source of USA and European countries which is not a large portion of current air pollution. But the passengers and airfreights are continuously increasing 5 to 7% annually and potential demands of air transportation services come to present, it could effect air pollutant emissions of USA will increase within 15 years. In case of our country, there has been continuous increase of air transportation service due to considerable economic growth in recent years and increase of air pollutant emissions of major international airports has followed. Rapid increase of air transportation due to launching of Inchon International Airport could effect air pollution dominantly. By this circumstance environmental specialist as well as mass communication raised necessity of air pollutant emission regulation from airplane engines. It is estimated that air pollutant emissions from airplane engines in our country is 2.7% of automobile sources, 10,809 ton, which is the same level as USA and European countries. It is increased by 12,2% compared to air pollutant emissions during 1996 and it will be increased more than a half of current air pollutant emission within 15 years due to our country's economic condition. Therefore implementation of airplane engine emissions regulation as well as test standards and accumulation of technology about characteristics of airplane engine emission and reduction method are needed. And continuous estimation of air pollutant emission from airplane engines and monitoring of increment as well as development of countermeasures by long term are necessary.

• 한국해양공학회지
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• 제15권1호
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• pp.26-30
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• 2001

Up to now, Most studies of hydroelasticity are about frequency domain analysis. Those aren't suited for analysis of the landing take-off, and dropping of aircraft on a structure. So, the concern of this paper is the transient behavior of a VLFS subjected to dynamic load, induced by airplane landing and take-off. To predict the added mass, damping coefficient, and wave exciting force, the source-dipole distribution method was used in the frequency domain. The responses are accomplished by using the FEM scheme. A time domain analysis method is based on the Newmark β method to pursue the time step procedure, taking advantage of memory effect function for hydrodynamic effects.

• Advances in aircraft and spacecraft science
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• 제4권6호
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• pp.651-677
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• 2017

For the past ten years' efforts have been made to introduce environmentally-friendly "green" electric-taxi and maneuvering airplane systems. The stated purpose of e-taxi systems is to reduce the taxiing fuel expenses, expedite pushback procedures, reduce gate congestion, reduce ground crew involvement, and reduce noise and air pollution levels at large airports. Airplane-based autonomous traction electric motors receive power from airplane's APU(s) possibly supplemented by onboard batteries. Using additional battery energy storages ads significant inert weight. Systems utilizing nose-gear traction alone are often traction-limited posing serious dispatch problems that could disrupt airport operations. Existing APU capacities are insufficient to deliver power for tractive taxiing while also providing for power off-takes. In order to perform comparative and objective analysis of taxi tractive requirements a "standard" taxiing cycle has been proposed. An analysis of reasonably expected tractive resistances has to account for steepest taxiway and runway slopes, taxiing into strong headwind, minimum required coasting speeds, and minimum acceptable acceleration requirements due to runway incursions issues. A mathematical model of tractive resistances was developed and was tested using six different production airplanes all at the maximum taxi/ramp weights. The model estimates the tractive force, energy, average and peak power requirements. It has been estimated that required maximum net tractive force should be 10% to 15% of the taxi weight for safe and expeditious airport movements. Hence, airplanes can be dispatched to move independently if the operational tractive taxi coefficient is 0.1 or higher.

• 한국항공운항학회:학술대회논문집
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• 한국항공운항학회 2005년도 추계학술발표대회 논문집
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• pp.102-111
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• 2005

• 한국해양공학회:학술대회논문집
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• 한국해양공학회 2000년도 추계학술대회 논문집
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• pp.63-67
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• 2000

Up to this day, Most studies of hydroelasticity are inclined to frequency domain atnlysis. Thos amlysis Q the landing, take-4, and dropping of airaqft on a structure. So, the concern of this prrper is a tra a VLFS subjected to dymmic lazd induced by airplane larndirrg and take-off. To predict added mass, dampr exciting force, the source-dipole distribution method were used The responses are accomplished by Fdoimain analysis method is based on Newmark $\beta$ method to pursuit time step pnzcedure taking advantage function for hvdrodvnumic effects.

• 감성과학
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• 제10권4호
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• pp.539-554
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• 2007

대형 비행기 조종사들은 지상으로부터 높은 조종실의 위치, 빠른 접근속도와 수직강하속도로 인하여 불충분한 시각정보를 바탕으로 착륙 조작을 하여야만 한다. 본 연구에서는 이러한 대형 비행기의 특징으로 인하여 비행기 착륙의 최종 조작인 당김(flare) 조작을 할 때 대형 비행기 조종사들이 정확한 높이지각을 하기 어렵다는 사실을 검증하였다. 연구 1에서는 조종석 외부로 보이는 공항에 대한 사진을 제시하고 높이 추정을 하도록 하여 정적 시각 단서만으로 정확한 높이지각이 가능한지를 살펴보았다. 85feet의 고도에서는 정확한 높이지각을 하나 당김 조작을 준비해야 하는 높이인 55feet부터 낮은 고도에서는 정확한 높이를 추정하지 못하였다. 연구 2에서는 착륙의 전 과정을 녹화한 화면을 보여주어 높이 추정을 하도록 하여 동적 시각 단서와 정적 시각 단서를 모두 제공하여 주었다. 시각단서가 연구 1보다 풍부하였으므로 50feet까지 정확한 높이지각을 하였으나 연구 1의 결과와 마찬가지로 당김 조작을 시작하는 높이인 30feet 이하의 저고도에서의 높이지각이 모두 부정확하였다. 시각 단서의 해석에 경험이 중요한 요인이므로 경험이 많은 기장과 경험이 적은 부기장 간의 높이 추정에 차이가 있는지를 연구 1과 연구 2에서 모두 비교하여 보았으나 차이는 유의하지 않았다.

• 항공우주시스템공학회지
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• 제4권3호
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• pp.17-23
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• 2010

GPS sensors provide accurate position and velocity of moving vehicles. However, GPS is weak at intermittent signal loss and large position error. Combination with INS improves the GPS position accuracy during the GPS signal loss. In this paper, a fusion filter using GPS and INS is developed and its perfomance is analyzed with RC car and RC airplane experiments.

• 한국해양공학회:학술대회논문집
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• 한국해양공학회 2001년도 추계학술대회 논문집
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• pp.45-49
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• 2001

The length and the breadth or a very large floating airport are determined by airplane types and airport facilities. However, the depth affect not only the structural strength but also the functional requirement such as a possibility of taking off and landing. The optimization problem for determining the depth is to select a design so that the cost is minimized. In this paper, a general arrangement and a method to decide the depth are proposed. Strength, functional requirement, and possibility of occurrence of deck wetness and slamming are considered in order to determine the depth of structure. Hydrodynamic forces of the diffraction and radiatin problems are predicted by applying the source-dipole distribution method, and the structural responses are obtained by the finite element method.

• 한국컴퓨터산업교육학회:학술대회논문집
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• 한국컴퓨터산업교육학회 2003년도 제4회 종합학술대회 논문집
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• pp.33-38
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• 2003

Reports have a significant meaning in time-constrained large transaction environments, such as airplane control systems or wargame simulations. This is due to the necessity of generating reports within a limited scope of time without restraining the operation performance of large transaction environments. In order to generate reports in large transaction environments while satisfying time - constrained requirements, this paper propose a model which combines the incremental operation mechanism and materialized view mechanism using triggers and stored procedures. Further, the implementation and evaluation of the preposed model provides analysis for model characteristics.

• 정보처리학회논문지D
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• 제11D권3호
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• pp.533-544
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• 2004

항공관제 시스템, 워게임 등과 같이 시간제약을 갖는 대규모 트랜잭션 환경에서 보고서의 의미는 특별하다 이는 대규모 트랜잭션 연산을 수행하면서 성능의 제약 없이 제한된 시간 내에 보고서를 생성할 수 있어야 하기 때문이다. 이와 같이 대규모 트랜잭션 환경에서 시간제약을 만족하면서 보고서를 생성할 수 있도록 하기 위하여 이 논문에서는 점진적 연산 기법과 형성뷰 기법을 트리거와 저장 프로시져를 이용하여 결합시킨 모델을 제안한다. 아울러 제안 모델에 대한 구현 및 평가를 통해 제안 모델의 특성을 분석한다.