• 대한전기학회논문지
• /
• 제43권4호
• /
• pp.638-647
• /
• 1994

This paper describes the real time Hardware-In-the Loop Simulation(HILS) that is an efective tool for design, testing and performance evaluation of the guidanc eflight system. The real time HILS was performed by using a 3-axis flight motion simulator, real time computer, I/O system and flight control system hardware along with the assumed flight trajectory of the guidance flight system. Also, we proved the validity of the real time HILS is the guidance flight system by comparing its simulation results with the software simulation data and telemetry data.

• 항공우주시스템공학회지
• /
• 제7권3호
• /
• pp.45-50
• /
• 2013

This is a research report about the method of how to maintain qualification of certification flight test crews. KCA(Korea Certification Agency) have completed the KC-100 airplane certification flight tests which is the first time experienced flight tests operation. After the certification flight test, it has been found that annual flying time requirement of 100 hours to the certification flight test pilot is too strict, and other several requirements to maintain the qualification of the certification test crew such as aircraft certification introduction training, initial flight test pilot and flight test engineer certification training, crew resource management training, aviation physiology training, and survival training was difficult to implement in Korean civil aviation environments. In this study, it was suggested that 30 hours of flying time for maintaining certification flight test pilot qualification could be applied to contribute for safe operation of certification flight test and the other training requirements of the certification flight test crew could be fulfilled using self made training courses, existing FAA training courses and Korean Air Force training resources. Therefore, it is recommended that the regulation of maintaining the certification flight test crew qualification should be refined to implement the requirement practically.

• 경영과학
• /
• 제21권1호
• /
• pp.39-55
• /
• 2004

Efficient crew scheduling for cockpit crew is important in airline industry due to operational safety and cost associated with the flight duty time. Because of complexity of regulations imposed to the cockpit crew. it is complicated to generate an efficient schedule. Schedule of cockpit crew can be generated through two steps; selecting of flight patterns. and scheduling of them to the specific time horizon. Heuristic method is developed and applied with massive data in a limited time of computation. A set of flight patterns is selected from all possible flight patterns. which are generated by composing the flight leg based on regulations. by using the set partitioning problem with objective function of oversea stay cost. The selected set of flight patterns found at the first step is allocated to 4 week crew schedule to minimize the variance of total fight time assigned to each crew. The crew schedules obtained are evaluated and compared with the ones currently used in one of major airline company.

• 항공우주정책ㆍ법학회지
• /
• 제20권2호
• /
• pp.253-276
• /
• 2005

자격유지기록부란 조종사의 비행경력을 입증하기 위한 비행일지를 말하며 조종사의 비행경력 확인을 위한 필수적인 자료이다. 이러한 비행시간을 산정하여 자격유지기록부를 유지하는 이유는 자격시험에 있어서의 자격검토, 경력관리에 있어서의 문제, 직업의 특수성으로 인한 경력의 글로벌 스탠다드를 위한 것이다. 본 논문은 이러한 비행시간 산정 항목 중 특히 계기비행과 관련된 자격유지 기록에 초점을 맞추어 실제 국내에서 요구되는 비행시간 산정의 항목들과 해외의 항목들 간의 정의 및 구성요소들을 확인하여 국내에서 적용하고 있는 항목들의 차이점 및 문제점은 무엇이고 각 항목에 대한 정의가 어떻게 내려져야 할지를 집중적으로 분석하였다.

• 제어로봇시스템학회논문지
• /
• 제14권12호
• /
• pp.1244-1252
• /
• 2008

This paper presents the analysis results obtained by the flight test of reconfiguration flight control system for an aircraft. The reconfiguration flight control system was designed by using control allocation scheme that automatically distributes the demanded control moments determined by control law to each actual control surface. In this paper, some control allocation algorithms for reconfiguration control of general aircraft with redundant control surfaces are summarized and their performance evaluation results through nonlinear simulation and Hardware-In-the-Loop-Simulation (HILS) test are shown. Also, Unmanned Aerial Vehicle (UAV) system adopted as a platform for the flight test of reconfiguration flight controller and the implementation procedure of reconfiguration flight controller into real-time UAV system were introduced. Finally, flight test results were analyzed.

• Journal of Mechanical Science and Technology
• /
• 제20권8호
• /
• pp.1224-1231
• /
• 2006

The stability and control derivatives of DURUMI-lI UAV using the flight test are obtained. The flight test data is gathered from the normal flight condition (normal mode) and the flight condition assumed as the right elevator fixed (fault mode). Using real-time parameter estimation techniques, applied to Fourier transform regression method, simulates the aircraft motion. From the result, the fault of control surface is to be detected. In this paper, the results of the real- time parameter estimation techniques are compared with the results of the Advanced Aircraft Analysis (AAA). Using the aerodynamic derivatives, it provides the base line of normal/failure for the control surface by using the on-line parameter estimation of Fourier transform regression. In flight, this approach maybe helpful to detect and isolate the fault of primary control surface. It is explained how to perform the flight condition assumed as the right elevator fixed in the flight test. Also, it is mentioned how to switch between the normal flight condition and the assumed fault flight condition.

• 한국HCI학회:학술대회논문집
• /
• 한국HCI학회 2008년도 학술대회 1부
• /
• pp.708-711
• /
• 2008

Time-of-flight(ToF) cameras deliver intensity data as well as range information of the objects of the scene. However, systematic problems during the acquisition lead to distorted values in both distance and amplitude. In this paper we propose a method to acquire reliable distance information over the entire scene correcting each information based on the other data. The amplitude image is enhanced based on the depth values and this leads depth correction especially for far pixels.

• Bulletin of the Korean Chemical Society
• /
• 제18권2호
• /
• pp.171-174
• /
• 1997

The initial kinetic energy of laser-ablated Zn cation has been investigated via time-of-flight mass spectrometry. The flight times of the ions have been measured with a high voltage pulse on the extract electrode in the mass spectrometer, which has been delayed from the laser pulse. The time-of-flight equation including the initial kinetic energy term of the ion has been derived for the mass spectrometer. The optimum value of the initial kinetic energy has been extracted by fitting the measured flight times into the time-of-flight equation. The initial kinetic energy of the ions generated by Nd:YAG laser (532 nm) at the power density of 5 × 107 W/cm2 has been determined to be 22-44 kJ/mol.

• 제어로봇시스템학회논문지
• /
• 제10권2호
• /
• pp.112-124
• /
• 2004

A neural network based adaptive reconfigurable flight controller is presented for a class of discrete-time nonlinear flight systems in the presence of variations of aerodynamic coefficients and control effectiveness decrease caused by control surface damage. The proposed adaptive nonlinear controller is developed making use of the backstepping technique for the angle of attack, sideslip angle, and bank angle command following without two time separation assumption. Feedforward multilayer neural networks are implemented to guarantee reconfigurability for control surface damage as well as robustness to the aerodynamic uncertainties. The main feature of the proposed controller is that the adaptive controller is developed under the assumption that all of the nonlinear functions of the discrete-time flight system are not known accurately, whereas most previous works on flight system applications even in continuous time assume that only the nonlinear functions of fast dynamics are unknown. Neural networks learn through the recursive weight update rules that are derived from the discrete-time version of Lyapunov control theory. The boundness of the error states and neural networks weight estimation errors is also investigated by the discrete-time Lyapunov derivatives analysis. To show the effectiveness of the proposed control law, the approach is i]lustrated by applying to the nonlinear dynamic model of the high performance aircraft.

• 항공우주시스템공학회지
• /
• 제9권1호
• /
• pp.12-18
• /
• 2015

The inter-conversion between different control laws in flight has a lot of risk. The SWM(Switching Mechanism) including logic and stand-by mode is designed to analyze the transient response of aircraft during inter-conversion between different control laws, based on the in-house software for non-real-time and real-time simulation. The SWM applies the fader logic of TFS(Transient Free Switch) to minimize the transient response of an aircraft during the inter-conversion, and applies the reset '0' type of the stand-by mode to prevent surface saturation due to integrator effect in the disengaged flight control law. The transition time is also important to minimize the objectionable transient response in the inter-conversion, as well as the transition control law design. This paper addresses the results of non-real-time simulation for the characteristics of transient response to different transition time to select the adequate transient time, and the real-time pilot evaluation, using SSWM(Software Switching Mechanism) and HSWM(Hardware Switching Mechanism), which is met for Level 1 flying qualities and assures safety of flight.