• 한국정밀공학회지
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• 제33권10호
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• pp.781-787
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• 2016

We introduce FEST (Flight Environment Simulation Test) procedures for precise guided missiles to reliably improve systems. Flight vibration specification was established based on power spectral density curves calculated from flight test data of a high speed precise guided missile. A FEST pre-profile was developed according to flight vibration specification and delivered to a precise guided missile assembly. Vibration responses were measured by installing accelerometers on electronic components vulnerable to dynamic forces. The FEST profile was adjusted by comparing the vibration responses and the flight vibration specification. Subsequently, the FEST profile was repeatedly modified through trial and error, because the responses were similar to the flight environment. The modified FEST profile enabled performance testing of assembled precise guided missiles under simulated flight conditions on the ground, where unexpected errors could be corrected before the flight tests, leading to cost and risk reduction in the development of the precise guided missile system.

• 전기전자학회논문지
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• 제22권3호
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• pp.747-753
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• 2018

Currently, many companies have succeeded in logistics delivery experiments utilizing drone and report it. When a drone is used commercially, long-term flight is an important performance that a drone should have. However, unlike vehicles operated on the ground, drone is a vehicle that continues to consume energy when maintaining the current altitude or moving to the destination. Therefore, the drones can fly for a long time as the capacity of the battery is large, but the batteries with large capacity are restricted by heavy weight and it acts as a limiting factor in a commercial use. To address this issue, we attempt to compare how far we can fly than forward flight based on the flight pattern with the same energy consumption condition. In this paper, the comparison of energy consumption was performed in three flight pattern, forward flight without altitude change and forward flight with altitude change, by computer simulation and it shows the increasing of flight distances when the quadrotor fly with altitude change from high altitude to low altitude.

• 한국추진공학회지
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• 제24권6호
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• pp.16-27
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• 2020

넓은 비행영역에서 스크램제트 엔진의 운용을 위해, 비행 조건의 변화에도 안정적인 성능을 나타내는 흡입구의 설계가 중요하다. 본 연구에서는 마하수 4~6, 받음각 -6도~6도의 넓은 비행영역에서 안정적인 성능을 얻기 위한 2D 고정형 흡입구의 설계 방법에 대한 연구를 수행하였다. 설계 방법 및 설계 주안점에 대해 제시한 후, 넓은 비행영역에서 높은 전압력 회복율과 유량 포획율을 갖는 흡입구를 설계함에 있어 가장 중요한 설계요소인 초기 압축각도와 비행 마하수 설계점에 따른 성능예측 및 분석을 수행하였다. 분석 결과를 바탕으로 넓은 비행영역에서 안정적인 성능을 나타내기 위한 두 가지 주요 설계요소의 선정기준을 제시하였다.

• 유통과학연구
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• 제22권5호
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• pp.105-115
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• 2024

Purpose: The purpose of the current study is to highlight the drivers of corporate environmentally and socially sustainable performance among different players including airlines, caterers, suppliers and logistics companies in the flight catering supply chain. Research design, data and methodology: Based on a qualitative research approach this study employed in-depth semi-structured interviews exploring the drivers of corporate sustainable performance with management from major in-flight catering stakeholders (n=23) from the perspective of constructivism. Using the snowball sampling approach, interviewees were carefully chosen to represent a diverse range of supply chain contexts (airlines, catering, non-food suppliers, and logistics companies). Results: By focusing on the complex context of multiple supply chain partners, the study identified a range of complex relationships between the drivers of sustainable performance in the supply chain: firm-led drivers, factors influencing firm-led drivers, partial influencers, and additional factor, cost. Conclusions: This study emphasizes that some drivers do not play an absolute role and has highlighted that there is a need for companies to change the attitude, that is to pay more than 'lip service' to improving sustainable performance. This study develops a theoretical framework of the drivers of corporate sustainable performance, along with its practical industry implications.

• 한국군사과학기술학회지
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• 제4권2호
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• pp.30-41
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• 2001

In Underwater Flight Vehicle depth control system, the followings must be required. First, It needs a robust performance which can get over the nonlinear characteristics due to hull shape. Second, It needs an accurate performance which has the small overshoot phenomenon and steady state error to avoid colliding with ground surface and obstacles. Third, It needs a continuous control input to reduce the acoustic noise. Finally, It needs an effective interpolation method which can reduce the dependency of control parameters on speed. To solve these problems, we propose a Intelligence depth control method using Fuzzy Sliding Mode Controller and Neural Network Interpolator. Simulation results show the proposed control scheme has robust and accurate performance by continuous control input and has no speed dependency problem.

• 제어로봇시스템학회논문지
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• 제11권3호
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• pp.262-269
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• 2005

Automatic landing of UAVs receives increasing interest these days, with increasing number of the developed UAV systems. In this paper, a glidepath tracking algorithm of the subscale UAV was proposed and the performance was analyzed. Flight data analysis shows that the existing autolanding flight control algorithm has a classical type glidepath control. This paper presents an alternative glidepath tracking strategy based on embedded flight control law. The performance of the proposed strategy was investigated through the TDP(Touch Down Point) error analysis with regard to various flight environment: steady headwind, atmospheric disturbance, communication transfer delay. It was verified that the proposed glidepath tracking strategy can be successfully applied to the practical autolanding of UAV systems.

• 대한전기학회논문지:시스템및제어부문D
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• 제50권8호
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• pp.367-375
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• 2001

In Underwater Flight Vehicle depth control system, the followings must be required. First, it needs robust performance which can get over modeling error, parameter variation and disturbance. Second, it needs accurate performance which have small overshoot phenomenon and steady state error to avoid colliding with ground surface or obstacles. Third, it needs continuous control input to reduce the acoustic noise and propulsion energy consumption. Finally, it needs interpolation method which can sole the speed dependency problem of controller parameters. To solve these problems, we propose a depth control method using Fuzzy Sliding Mode Controller with feedforward control-plane bias term and Neural Network Interpolator. Simulation results show the proposed method has robust and accurate control performance by the continuous control input and has no speed dependency problem.

• 한국항공우주학회지
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• 제33권2호
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• pp.22-31
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• 2005

본 연구에서는 회전익 항공기의 수직 이/착륙 성능과 고정익 항공기의 고속/고효율 순항 비행 성능을 모두 가지는 Canard Rotor/Wing 항공기 최적 형상설계를 수행하였다. CRW 항공기의 특징인 로터/날개 가변 방식과 로터 회전 시 팁 제트를 통하여 회전력을 얻는 점 때문에 기존의 회전익 또는 고정익 사이징 프로그램만으로는 바로 적용이 어렵고 Reaction Driven 로터에 대한 해석 모듈의 추가와 회전익/고정익 비행 모드 해석이 혼합되어야 한다. 따라서 기존의 사이징 프로그램을 바탕으로 로터 성능, 덕트 유동, 엔진 유동 해석 코드를 연결하여 Reaction Driven 로터 성능 해석이 가능하게 하였으며, 비행체 외형상 특징과 임무별 비행특징이 반영되도록 사이징 프로그램을 개발하였다. 1500 lbs급 소형 무인기에 대하여 비행체 사이징을 수행하고 성능에 크게 영향을 미치는 설계변수를 파악하여 최적화 문제를 구성하였고 전역적 최적화 기법을 이용하여 최소 중량을 가지는 CRW 항공기의 최적형상을 도출하였다.

• 한국항공운항학회지
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• 제5권1호
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• pp.7-16
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• 1997

Airspeed and altimeter calibration of Twin Bee was conducted by the flight test. We have adopted system to system method. Flight test data is corrected for instrumented error and position error, and the resultin data was satisfied. Climb Performance flight test also was conducted. But we could not have all data because of limited flight time. The resulted data was satisfied compare with calculated data.

• 한국항공운항학회지
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• 제3권1호
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• pp.37-47
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• 1995

It is very important to determine the performance and operating envelope of engine for aircraft's flight. The basic performance is provided by manufacturer, but installed engine's operating envelop is only determined by flight test. First, this study was measured cylinder head temperature(CHT), exhaust gas temperature(EGT) and oil temperature. At pre-determined altitude and power rate, these temperatures were measured by change of mixture ratio and mixture ratio condition for economic operation and max. power were found. And secondly, with the measured temperatures, possible positions of mixture lever were determined by flight test for stable flight Chang-91 and Lycoming IO-360-A series four cylinders engine with 200 hp was used for this study.