• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.423-427
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• 2003

In this paper, it is to development of brake system with ABS function for aircraft. The test of brake system is required before applying on aircraft. The real-time dynamic simulator with 5-D.O.F. aircraft dynamic model is developed for braking performance test of ABS (Anti-skid Brake System) control h/w with anti-skid brake functions. The dynamic simulator is real-time interface system that is composed of dynamic simulation parts, master control parts, digital and analog in/out interface parts, and user interface parts. The 5-D.O.F. aircraft dynamic model is composed of a big contour and a little contour by simulation s/w. The big contour represents the interactions of forces in airframe, nose and main landing gear, and engines on the center of gravity. The little contour represents interactions of wheel, braking units, hydraulic units and a control unit. ABS control h/w unit with ABS control algorithm is also developed and is tested with simulator under the some conditions of gripping coefficient. We have known that ABS control h/w unit on wet or snowy runway as well as dry runway very well protects wheel skid.

• 한국생산제조학회지
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• 제21권6호
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• pp.968-975
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• 2012

ABS(Anti-skid Brake System) had been developed on purpose of most effect at breaking in limited runway. An aircraft has a large amount of kinetic energy on landing. When the brakes are applied, the kinetic energy of the aircraft is dissipated as heat energy in the brake disks between the tire and the ground. The optimum value of the slip during braking is the value at the maximum coefficient of friction. An anti-skid system should maintain the brake torque at a level corresponding to this optimum value of slip. This system is electric control system for brake control valve at effective control to prevent slip and wheel speed or speed ratio. In this study we measured the thickness of the carbon disk before and after to find its wear and it shows that carbon disk brake has higher stiffness and strength than metal disk at high temperature. In addition, thermal structural stability and appropriate frictional coefficient of the carbon disk brake prove its possible substitution of metal disk brake.

• 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.

• 한국정밀공학회지
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• 제20권11호
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• pp.127-133
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• 2003

Pin-on-disk and hardness tests using mechanical components of M-20J aircraft braking system were performed to identify the friction and wear characteristics. The intention of this work was also to analyze a 5-year term maintenance record of an M-20J aircraft. used for flight training at Hankook Aviation University, and to determine the reliability of the brake system of an M-20J aircraft. The mean wear coefficients of the lining sliding against the brake disk were compared between the test and reliability estimation to obtain a predictive wear model.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2005년도 ICCAS
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• pp.535-538
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• 2005

Today, most fixed-wing aircrafts are equipped with the antiskid brake system. It can modulate braking moments in the wheels optimally, when an aircraft is landing. So it can reduce landing distance and increase safeties. The antiskid brake system for an aircraft are mainly composed of braking moment modulators (hydraulic control valves) and brake control unit. In this paper, a Mark IV type - fully digital - brake controller is studied. For the development of its control algorithms, a 5-DOF (Degree of Freedom) aircraft landing model is composed in the form of matlab/simulink model at first. Then, braking moment control algorithms using wheel decelerations and slips are made. The developed algorithms are tested in software simulations using state-flow toolboxes in matlab/simulink model. Also, a real-time simulation systems are made, which use hydraulic brake systems of a real aircraft, pressure control valves and its controller as hardware components of HIL(Hardware In-the-Loop) simulation. Algorithms tested in software simulations are coded into the controller and the real-time landing simulations are made in very severe road conditions. The real-time simulation results are presented.

• 한국군사과학기술학회지
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• 제20권5호
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• pp.597-607
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• 2017

The general control method for Anti-lock Brake System(ABS) is that the wheel slip ratio is observed and the braking force is controlled in real time in order to keep the wheel slip ratio under the value of the best slip ratio. When a wheel runs on the state of the best slip ratio, the ground friction of the wheel approaches the highest value. The value of best slip ratio, theoretically, is known as the value between 10 and 20 % and it is dependant on the ground condition such as dry, wet and ice. It is an important parameter for the braking performance and affects the braking stability and efficiency. In this thesis, an experimental method is suggested, which is a reliable way to decide the best slip ratio through dynamo tests simulating aircraft taxiing conditions. The obtained best slip ratio is proved its validity by results of aircraft taxiing tests.

• 항공우주기술
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• 제7권1호
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• pp.8-14
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• 2008

항공기 휠브레이크용 축압기에 대하여 기본적인 특성을 조사하였다. 휠브레이크용 축압기는 주기시 제동유압을 유지하고, 비상시 휠브레이크에 유압을 공급한다. 휠브레이크용 축압기의 설계요구조건을 분석하고, 이를 토대로 설계에 필요한 기본 치수를 결정하였으며, 실린더와 브레이크 컨트롤 모듈로 구성된 축압기의 상세 구성요소와 기본 형상을 제시하였다. 또한, 예비 설계를 위하여 정적구조해석을 NASTRAN/PATRAN으로 수행하였다.

• 한국항행학회논문지
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• 제27권6호
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• pp.821-827
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• 2023

본 연구에서는 국내 및 미국의 항공기 기술기준과 기술표준품 표준서를 분석하여 수송류 항공기용 금속계 제동패드의 비행시험 인증을 위한 합치성 증명 시 요구되는 다이나모시험절차를 도출하였다. 제동장치의 설계개조는 중대한 변경으로 분류되어 부가형식증명 및 부품등제작증명이 동시에 요구된다. 다이나모시험 항목은 미국의 제동장치 기술표준품 표준서인 TSO-C135a 규정에 따라 비행시험의 적합성을 판단하는 기준으로 비행시험 시 요구되는 주요 시험항목 중 설계착륙-정지 시험, 가속-정지 시험 및 최대 하중상태의 착륙-정지 시험을 선정하였다. 다이나모시험 조건은 항공기 제조사가 제공하는 주요 사양에 따라 정해지며, 제동패드의 조건, 감속도 및 시험횟수 등은 TSO-C135a 규정에 따라 정의하였다.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2005년도 학술대회 논문집 정보 및 제어부문
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• pp.222-224
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• 2005

In the development of Antiskid Brake System(ABS) for a fixed-wing aircraft, the braking efficiency is the most essential parameters to evaluate the ABS, especially in slippery road conditions. The braking distance and landing distance of the aircraft depends on it. Since the ABS has been designed and implemented as a subsystem of the aircrafts, the braking performance was evaluated under dynamometer test, where the dynamometer emulates the aircraft mass. Under simulated wet road conditions, the dynamometer starts to be braked. This paper suggests practical braking efficiency calculation methods and the results and finally compares each method.

• 대한전자공학회:학술대회논문집
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• 대한전자공학회 2008년도 하계종합학술대회
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• pp.1083-1084
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• 2008

This paper proposes the design of anti-braking system on aircraft and wheel slip ratio control using adaptive slide mode control. By maintaining the desired wheel slip ratio under runway conditions, we can obtain the maximal frictional force and reduce the braking range. In this paper, we apply an adaptive sliding mode control to aircraft brake system and it can guarantee the robustness under variations in brake characteristics. The performance of proposed controller is verified in simulations.