• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.36 no.5
• /
• pp.507-513
• /
• 2008

In this paper, we present a development of an Avionics Hot Bench(AHB) used for the verification of operational flight programs and fault analysis using various simulation and stimulation software. We propose an application of the open system architecture to develop the AHB which can be used for the development of a real aircraft avionics system. In the design of the AHB, to reduce the development period and cost we use as many as commercial off-the-shelf hardware and software items. The developed AHB is compared with the existing proven AHB which was used for T-50 avionics system development. Thorough comparison between the test results using the developed AHB and those using the existing AHB is performed and the overall comparison results are very satisfactory.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.30 no.4
• /
• pp.114-122
• /
• 2002

The integration of the landing gear system is a complex relationship between the many conflicting parameters of shock absorption, minimum stow area, complexity, weight and cost. Especially ground impact load and dynamic behaviors greatly influence design load of landing gear components as well as load carrying structural attachment. This study investigates ground impact load and dynamic behaviors of the T-50 landing gear system using ADAMS. Taking into account for various operational/environmental conditions, an analysis of shock absorbing characteristics at ground impact is performed with experience derived from a wide range of proprietary designs. Analytical results are presented for discussing the effects of aircraft horizontal and vertical speed, landing attitudes, shock absorbing efficiency. This analysis leads us to the conclusion that the proposed program is shown to be a better quantitative one that apply to a new development and troubleshooting of the landing gear system.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.31 no.6
• /
• pp.110-117
• /
• 2003

The operational characteristics of the landing gear retraction/extension depend on the complexity of design variables operational/environmental conditions. In order to meet the requirements of minimum stow area and performance, the integration of the landing gear system requires operational kinematic and dynamic analysis considering an effect of its related system. This study investigates operational dynamic behaviors of the T-50 landing gear system using ADAMS. Taking into account for various operational/environmental conditions, an analysis of dynamic behavior on the landing gear operational characteristics is performed with experience derived from a wide range of proprietary designs. Analytical results are presented for discussing the effects of temperature, aerodynamic and maneuver load on normal/emergency operation of the landing gears and doors. This analysis leads us to the conclusion that the proposed program is shown to be a better quantitative one that apply to a new development and troubleshooting of the landing gear system.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
• /
• v.20 no.5
• /
• pp.460-470
• /
• 2009

In this paper, we described the implementation of the X-Band continuous-wave doppler radar for muzzle velocity measurement. The radar is consisted of microwave transceiver, signal processor, power board, and the measuring program was developed for the operating and field test. The operating frequency of doppler radar is able to set ${\pm}3\;MHz$ with 5 channel from the center frequency, and the output power is 25 dBm. The minimum receiving power is -117 dBm. The radar would obtain the doppler frequency from the artillery, and calculate accurate velocity point and then estimate muzzle velocity. The performance test for this radar was done with 155 mm at barrel and tripod mounted, and also compared the performance with the reference radar. As a result, the performance of the our new radar is equal with the reference one.

• Journal of the Korea Academia-Industrial cooperation Society
• /
• v.17 no.11
• /
• pp.363-367
• /
• 2016

A test section of a supersonic wind tunnel was designed for the analysis of flow characteristics over a backward-facing step with Mach 1.0 slot injection in a supersonic flow of Mach 2.5. The cavity flow of a high-speed vehicle is very complex at supersonic speed, so it is necessary to do experiments using supersonic wind tunnels to verify numerical analysis methods. The previous 2D symmetrical nozzle was replaced with an asymmetrical nozzle. The inviscid nozzle contour was designed using Method of Characteristics (MOC), and the boundary layer thickness correction was reflected by experimental data from the wind tunnel. The results were compared with a CFD analysis. The PID control system was changed to be based on the change of tank pressure. This improved the control efficiency, and the run times of supersonic flow increased by about 1 second. The flow characteristics over a backward facing step with slot injection were visualized by a Schlieren device. This equipment will be used for an experimental study of the film cooling effectiveness over a cavity with various velocities, mass flows, and temperatures.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.50 no.11
• /
• pp.791-800
• /
• 2022

The number and locations of force generators and their force directions of Active Vibration Control System(AVCS) are important to maximize the airframe vibration reduction performance of helicopters. The present AVCS simulation using an exhaustive test method attempts to determine the best number and locations of force generators and their force directions for maximization of the airframe vibration reduction performance of UH-60A helicopter at 158 knots. The 4P hub vibratory loads of the UH-60A helicopter are calculated using DYMORE II, a nonlinear multibody dynamics analysis code, and MSC.NASTRAN is used to predict the vibration responses of the UH-60A airframe. The AVCS framework with an exhaustive test method is constructed using MATLAB Simulink. As a result, when applying AVCS with the optimal combination of the force generators, the 4P airframe vibration responses of UH-60A helicopter are reduced by from 19.35% to 98.07% compared to the baseline results without AVCS.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.35 no.11
• /
• pp.1028-1035
• /
• 2007

this study, forced vibration analysis was performed on the composite main wing structure of a small scale WIG craft which is equipped two-stroke pusher type reciprocating engine. The structural vibration analysis based on the finite element method was performed using a commercial FEM code, MSC/NASTRAN. Excitations for the frequency response analysis were assumed as the H-mode(horizontal mode), the V-mode(vertical mode) and the X-mode(twisted mode) which are typical main vibration modes of engine. And excitations for the transient response analysis were assumed as the L-mode(longitudinal mode) with the oscillating propeller thrust which occurs.

• Telecommunications review
• /
• v.24 no.4
• /
• pp.468-480
• /
• 2014

The current-generation avionics systems are based on a federated architecture, where an electronic device runs a single software module or application that collaborates with other devices through a network. This architecture makes the internal system architecture very complicate, and gives rise to issues of Size, Weight, and Power (SWaP). In this paper, we show that the partitioning defined by ARINC 653 can efficiently deal with the SWaP issues on small unmanned aerial vehicles, where the SWaP issues are extremely severe. We especially install the integrated mission system on real hexacopter and quadcopter and perform successful flight tests. The presented software technology for integrated mission system and software consolidation methodology can provide a valuable reference for other SWaP sensitive real-time systems.

• Proceedings of the Korea Water Resources Association Conference
• /
• 2020.06a
• /
• pp.52-52
• /
• 2020

영상을 이용하여 하천유속과 유량을 측정하는 방법은 신속하고 간결하게 유속을 측정할 수 있는 방법으로 주목을 받고 있다. 또한 새로운 기술인 드론을 활용하여 하천의 유속과 유량을 측정하는 방법도 다양하게 시도되고 있다. 본 연구는 드론을 정지영상과 동영상을 이용하여 별도의 측량이나 복잡한 과정없이도 하천의 유속분포를 추정할 수 있는 방안을 제시하였다. 이 때, 중소하천의 유속 측정에 보다 쉽게 활용할 수 있도록 카메라 보정을 통한 카메라 내부변수 획득과 정지영상에 수록된 드론의 위치와 자세에 대한 EXIF 자료를 이용하는 방안, 약간의 흔들림이 있는 영상에서도 유속을 추정하는 방안을 제안하였다. 먼저, 드론의 카메라 보정을 위한 프로그램을 작성하고, 카메라의 내부 변수를 추정하였다. 드론의 위치와 자세에 대한 정보는 정지영상(JPG 파일)에 수록된 EXIF 정보를 이용하여 드론의 위치(GPS)와 자세(자이로스코프)를 알아내었다. 이를 이용하여 현장의 참조점에 대한 위치 정보를 확인하고, 또 수면촬영을 위한 정지비행시의 카메라의 대략의 위치와 자세 정보를 확인하였다. 이 자료들은 실제 유속측정에 이용하는 동영상에서 나타나는 참조점의 위치 정보를 결정하기 위한 것이다. 그리고 연이어 촬영된 동영상에서 시공간영상분석법으로 측정 단면의 유속분포를 분석하였다. 이 때, 동영상 내에 있는 약간의 흔들림은 FFT 분석으로 적절히 보완할 수 있다. 개발된 방법을 밀양강의 단장천 대리 수위표 지점 인근에서 시험한 결과 기존의 유속계로 측정한 방법과 상당히 근사한 결과를 얻을 수 있었다.

• Journal of Aerospace System Engineering
• /
• v.13 no.6
• /
• pp.52-59
• /
• 2019

The rotor blade is a key component that generates the lift, thrust, and control forces required for helicopter flight by the torque transmitted through the hub and the blade pitch angle control, and should be designed to factor vibration characteristics so that there is no risk of resonance with structural safety. In this study, the structural design of the main rotor blade for MPUH(Multi-Purpose Unmanned Helicopter) was conducted and the sectional stiffness measurement of the fabricated blade was performed. The evaluation of the vibration characteristics of the main rotor system was then conducted factoring the measured stiffness distribution. The interior of the rotor blade comprised of the skin, spar, and torsion box, and carbon and glass fiber composites were applied. The Ksec2D program was applied to predict the stiffness of blade, and the results were compared to the measured data. CAMRADII, a comprehensive rotorcraft analysis program, was applied to investigate the natural frequency trends and resonance risks due to the rotor rotation.