• 항공우주시스템공학회지
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• 제11권6호
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• pp.17-25
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• 2017

항공기가 지상에서 주행할 때 지면과 타이어 사이에 걸리는 수직하중 정보는 마찰력, 횡력 계산 시 사용되는 등 항공기 거동에 있어서 주요한 변수이다. 그러나 실제 항공기 주행 시 실시간으로 수직하중 정보를 얻기 힘들고, 실제 시험에서 발생 가능한 비정상적 활주 상황을 방지하기 위하여 사전 해석을 통해 타이어 수직하중 및 항공기 지상 거동 특성을 예측해 볼 필요가 있다. 본 논문에서는 VI-Aircraft S/W를 이용하여 착륙장치 및 Full-Aircraft 모델을 구성하였고 조향 해석 및 활주시험 상황 모사 해석을 통하여 항공기 지상 거동 특성에 대하여 분석하였다.

• International Journal of Aeronautical and Space Sciences
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• 제2권1호
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• pp.28-43
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• 2001

Developed in these two series of paper is a complex dynamic model representing the motion of aircraft on the ground and a computer program for numerical simulation. The first part of paper presents the theoretical derivation of equations of motion of the landing gear system based on the physical principle. Developed model is 'structured' in the sense that the undercarriage system is regarded as an assembly of strut, tire, and wheel, where each component is modeled by a separate module. These modules are linked with two external modules-the aircraft and the runway characteristics-to carry out dynamic analysis and numerical simulation of the aircraft motion on the ground. Three sets of coordinate system associated with strut, wheel/tire and runway are defined, and external loads to each component and response characteristics are examined. Lagrangian formulation is used to derive the undercarriage equations of motion relative to the moving aircraft, and the resultant forces and moments from the undercarriage are transformed to aircraft body axes.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2003년도 추계학술대회논문집
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• pp.718-723
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• 2003

The number of jet aircraft is increasing. The aircraft noise making people near airports nervous have become a serious social problem. The aircraft noise can be classified into two groups; noise being generated at take-off or landing and noise form run-up test on the ground. In this paper, we consider the aircraft noise from run-up test on the pound and we suggest the noise suppression system.

• 한국항공운항학회지
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• 제25권2호
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• pp.18-24
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• 2017

Results of the experimental research are described in this thesis, which are about braking characteristics of aircraft ABS brake system with different ground conditions. Dynamo-tests were conducted with the state of the application aircraft condition and with two different ground conditions. The Braking characteristics on each ground condition were drawn from the results of occurrence of skid, braking distance and deceleration. The braking performance of the application aircraft could be anticipated and the efficient range of braking operation could be set with those results.

• 한국항공운항학회지
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• 제27권4호
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• pp.27-36
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• 2019

An accurate trajectory prediction is a key to the safe and efficient operations of aircraft. One way to improve trajectory prediction accuracy is to develop a model for aircraft ground speed prediction. This paper proposes a generative model for posterior aircraft ground speed prediction. The proposed method fits the Gaussian Mixture Model(GMM) to historical data of aircraft speed, and then the model is used to generates probabilistic speed profile of the aircraft. The performances of the proposed method are demonstrated with real traffic data in Incheon Flight Information Region(FIR).

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1991년도 한국자동제어학술회의논문집(국내학술편); KOEX, Seoul; 22-24 Oct. 1991
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• pp.361-366
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• 1991

A ground and airborne control system for remotely piloted vehicle (RPV) is described. 1) Ground control system 2) airborne control system 3) the method of measuring aircraft attitude and heading 4) autopilot 5) the method of treating emergency status 6) the method of transmitting and receiving communication data 7) the method of displaying aircraft status 8) the characteristics of the aircraft control system are discussed in some detail.

• 한국군사과학기술학회지
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• 제24권6호
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• pp.602-609
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• 2021

Aircraft radar has special function which is ranging from aircraft to ground of antenna boresight. Because ranging information is used to calibrate altitude of aircraft or to drop a conventional bomb, the measuring have to be precise and robust. Therefore, we propose a simple and efficient method using monopulse radar for ground ranging. Proposed method calculates balancing weight according to linearity of monopulse ratio and mixes two ranging measurements in proportional to the weight. By exploiting balancing weight, radar is able to react to various environment as monopulse ratio contains characteristics of clutter environment. As a result, robust ranging information can be achieved. We use DEM(Digital Elevation Model) in order to simulate heterogeneous environment. In experimental result, it is shown that proposed method shows better accuracy and precision in any environment.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2005년도 춘계학술대회논문집
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• pp.754-757
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• 2005

Aircraft noise is the serious problem for inhabitants near an air force base. Noise by ground test of aircraft, however, can be minimized through test room construction. In this study, environmental effects of the noise by aircraft ground test were investigated by experiments under the standard act and by performance, prediction of the Hush house, constructed for the noise reduction.

• 한국국방경영분석학회지
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• 제24권2호
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• pp.1-16
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• 1998

Aircraft combat survivability(ACS) can be defined here as the probability of an aircraft to accomplish a given mission and not to be killed by enemy threats. The purpose of this thesis is to obtain analytically the combat survivability of the military aircraft according to the enemy and operation environment. Five factors under which a mission is being carried out are considered in this study. These factors are types and performance of enemy threats, aircraft susceptibility, aircraft vulnerability, ECM(electronic counter measures) capability, and pilot's capability. The model constructed in this study would be a useful tool to analyze ACS based on analytical method. It is also able to provide a better input data for wargaming simulation and present a criterion on determining optimal sorties for aircraft's air-to-ground mission.

• 시스템엔지니어링학술지
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• 제6권1호
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• pp.41-46
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• 2010

The ground high/low temperature test objective is to check the normal ground operation of FA-50 aircraft in the extreme ground ambient conditions. The aircraft was exposed in climatic conditions of the basic climatic category according to the MIL-HDBK-310. For verified normal operation in the extreme high temperature, the high temperature test was performed in the hot regional type conditions and accentuated solar radiation heat. This test was performed at the test chamber in ADD where is in Haemi. This paper was described about the test procedure of FA-50 high/low temperature including preparation, testing and results.