• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.4
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• pp.241-250
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• 2022

This paper addresses the Feasible Angular Momentum(FAM) chart that can be used as an indicator for maneuverability analysis of spacecraft installed with control moment gyros(CMGs). Recently, as the demands for high agility of spacecraft has been increasing in order to perform the space mission given to spacecraft more effectively, interest in CMGs, which is a high torque generator is increasing. However, since the CMG has a singularity problem that does not generate the control torque in the specific directions, in this paper, we consider the two pairs of parallel control moment gyros(TPCMGs) that follows the roof-type configuration. The Gimbal space was newly defined except for the space where singularity can be generated and the space where torque error is generated due to the hardware limits. The feasible angular momentum space is defined as a FAM chart, and it is very meaningful that it is possible to analyze the spacecraft's rotational maneuverability effectively by deriving the spacecraft's 3-axis parameters in the corresponding gimbal space mathematically.

• Journal of the Korean Institute of Illuminating and Electrical Installation Engineers
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• v.19 no.3
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• pp.105-110
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• 2005

Programmable Logic Controller(PLC) is the most widely utilized among many sorts of existing controller for the design of factory automation control system, and study about a PLC language is peformed actively. In this paper, we proposed the encoding module that we increase input points when increased of the input machine which is going to control it in the FA design that used PLC. Input point is going to be extended with 2-3 points in the state that cannot equip input unit in basic base any more. Then an extension base, a power supply, an extension cable and an output nit must be equipped particularly. Then a cost must be added very much. This paper proposed the encoding module which extended an input in a small quantity, and we confirmed a feasibility through a simulation.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2006.05a
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• pp.886-889
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• 2006

수치연산 보조프로세서로도 알려져 있는 부동 소수점 연산장치(FPU)는 컴퓨터가 사용하는 기본 마이크로프로세서보다 더 빠르게 숫자를 다를 수 있는 특별한 회로 설계 또는 마이크로프로세서를 말한다. FPU는 전적으로 대형 수학적 연산에만 초점을 맞춘 특별한 명령 셋을 가지고 있어서 그렇게 빠르게 계산을 수행할 수 있는 것이다. FPU는 오늘날의 거의 모든 PC에 장착되고 있지만, 실은 그것은 그래픽 이미지 처리나 표현 등과 같은 특별할 일을 수행할 때에 필요하다. 초창기 컴퓨터 회사들은 각기 다른 연산방식을 사용했다. 이에 따라 연산결과가 컴퓨터마다 다른 문제점을 해결하기 위해 IEEE에서는 부동 소수점에 대한 표준안을 제안하였다. 이 표준안은 IEEE Standard 754 이며, 오늘날 인텔 CPU 기반의 PC, 매킨토시 및 대부분의 유닉스 플랫폼에서 컴퓨터 상의 실수를 표현하기 위해 사용하는 가장 일반적인 표현 방식으로 발전하였다. 본 논문에서는 부동 소수점 표준안 중 32-bit 단일 정밀도 부동 소수점 가산기를 VHDL로 구현하여 FPGA칩으로 다운하고 PCI 인터페이스를 통해 Visual C++로 데이터의 입출력을 검증하였다.

• Journal of the Korean Institute of Intelligent Systems
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• v.18 no.5
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• pp.579-585
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• 2008

Recently, many researches on autonomous mobile system have been proposed, which are possible to recognize its surrounding environment and navigate to destination without supervisor's intervention. Various sensors are mounted on the autonomous systems in order for the systems to move to destination safely without any accident. In this paper, we design an ontology-based autonomous system mounted laser distance sensors and cameras, and propose a method to conceptualize sensing information. We show the validity of the proposed method through the experiments of the system's navigation.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.4
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• pp.81-88
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• 2013

It was designed and tested at the design point that an oxidizer rich preburner for a staged combustion liquid rocket engine propelled by kerosene and LOx. The oxidizer rich preburner was designed as some of LOx injected from the mixing head was burned with kerosene and the rest of LOx injected from injection holes in the regenerative cooling chamber was vaporized by combustion gas. The preburner is operated at OF ratio of 60 and combustion pressure of 20 MPa. The Preburner has a honey-comb type mixing head with simplex swirl injectors, a turbulence ring improving combustion stability and uniformity of product gas temperature distribution, and a nozzle simulating the duct. With the combustion test results at the design point, the oxidizer rich preburner showed high combustion stability and uniformity of product gas temperature distribution.

• Journal of the Korea Convergence Society
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• v.10 no.10
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• pp.123-128
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• 2019

The structural analysis for light weight on the brake pedal of the racing spec installed with the balance bars of the four models were performed in this study. By utilizing two materials of steels and aluminum alloys, four shapes were analyzed. It is generally assumed that the magnitude of force a person may incur when riding in a car is 1000 N. The fixed points are designated as the parts at which the bolts and pedals are fixed and the mounting part of the balance bar applied by the stress transmitted through the rod when the pressure of the master cylinder rises and the operation stops. Through this analysis study, it is thought that the vulnerability of each brake pedal model can be investigated and the transmission efficiency of the brake pedal can be increased by light weight. As the design data with the durability of brake pedal obtained on the basis of this study result are utilized, the esthetic sense can be shown by being grafted onto the part of car at real life.

• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.2
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• pp.10-17
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• 2004

The results of the combustion performance tests of gas generator which supplies hot gas into the turbine of turbo-pump for liquid rocket engine and uses LOx and kerosene as propellant are described. The gas generator consists of a injector head with F-O-F impinging injector, a water cooled combustion chamber, a gas torch igniter, a turbulence ring and an instrument ring. The effect of turbulence ring and combustion chamber length on performance of gas generator are investigated. The ignition and combustion at design point are stable and the pressure and gas temperature at gas generator exit meets the target. The turbulence ring installed at middle of chamber effectively mixes hot gas with cold gas and the effect of residence time of hot gas in gas generator on combustion efficiency is small. Test results show that the main parameter controlling the gas temperature at gas generator exit is overall O/F ratio.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.397-400
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• 2011

MDO Optimization for a low pressure axial compressor rotor has been carried out to improve aerodynamic performance and structural stability. Global optimized solution was obtained from an artificial neural network model with genetic algorithm. Optimized rotor model has a high blade loading near hub and near zero incidence flow angle near tip region to reduce the incidence loss and flow separation at trailing edge region. Also the rotor shape is converged to a trapezoid shape to reduce the maximum stress occurred at the root of the blade. Numerical simulation results show that rotor has 87.6% rotor efficiency and safety factor over than 3.

• Aerospace Engineering and Technology
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• v.12 no.2
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• pp.193-201
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• 2013

Propeller is an important component of Human Powered Aircraft (HPA) propulsion system. HPA uses large diameter low rotational speed propeller to get high propeller efficiency. The propeller was designed by HPA propeller designing program. The propeller pitch is adjustable by rotating the blade axis angle at ground. Performance of the propeller for various parameters are analysed by the same program used for design. Off-design condition performance was also checked including pilot power change and flight speed change. The propeller was manufactured in ultra-light structure using carbon composite material down to 950g. The propeller was ground tested on ironbird and installed on KARI HPA. Finally the HPA flew 291m with this propeller.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.17 no.9 s.112
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• pp.900-912
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• 2006

A GPS receiving antenna installed in the missile's warhead is designed and fabricated at a center frequency 1.575 GHz. The circular shaped antenna is installed in the middle of the warhead where the antenna's patch and the ground plane are connected with a hollow cylindrical shaped short pin. Using the dual feeding and phase difference method, an omni-directional radiation pattern which direction is normal to the missile's axis(H-plane) is obtained. The optimized diameters of the circular patch and the cylindrical ring typed shorting pin of the GPS receiving antenna which use the FR4.material(dielectric constant $\varepsilon_r=4.6$) are 59.5 mm and 14 mm, respectively. The cylindrical body with diameter 100 mm and height 500 mm is attached to the lower part of the warhead in order to complete the missile figure. The radiation patterns are measured by changing the angle and phase between the dual feeding points. When the phase difference of dual feeding is $100^{\circ}$ and the angle between the dual feeding points is $100^{\circ}$, the nearly omni-directional radiation pattern in the H-plane is obtained. In this case, the antenna gain is -5.55 dBd and the relative level difference between the maximum and the minimum radiation intensity is 3.98 dB.