• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.3
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• pp.41-48
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• 2008

One of main functions of the firing control system applied to a rocket propulsion test has been to provide electric current for ignition of a solid rocket motor. This paper describes the design and implementation of an enhanced firing control system for ground propulsion test that can also control and verify various types of squib events and flight sequences.

• Journal of the Korean Institute of Intelligent Systems
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• v.18 no.4
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• pp.482-487
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• 2008

In case of flooding, the underwater flight vehicle (UFV) executes the blowing by blowing ballast tanks off using high pressure air (HPA), while it also uses control planes and a propulsion unit to reduce the overshoot depth caused by a flooding and blowing sequence. However, the conventional whole HPA blow-off method lets the body on the surface after blowing despite slight flooding. This results in the unnecessary mission failure or body exposure. Therefore, it is necessary to keep the body at the near surface by the blowing control while reducing the overshoot depth. To solve this problem, an adaptive blowing control algorithm, which is based on the decomposition method expanding the expert knowledge in depth control and the adaptive method using fuzzy basis function expansion (FBFE), is proposed. To verify the performance of the proposed algorithm, the blowing control of UFV is performed. Simulation results show that the proposed algorithm effectively solves the problems in the UFV blowing control system online.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.9 no.3
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• pp.632-637
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• 2008

On board Weapon Control Unit for a military aircraft, as a core equipment of the Weapon Management System, generates signals for selective jettison, emergency jettison and rocket fire and controls the external stores according to a pilot's weapon selection, aircraft's flight status and external store's installation status. This paper describes about detail design process and performance evaluation for Weapon Control Unit developed by a sequence control circuit design methodology.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.4
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• pp.329-334
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• 2021

Korean Air has set the goal of the first stage of the development of unmanned helicopters to perform in hovering flight by remote control. In order to achieve the development goal, Korean Air carried out system integration, ground test, and safety wire test in sequence after carrying out programmed depot maintenance and aircraft modification of manned aircraft, and verified the controllability and flight safety of the unmanned helicopter system step by step. In particular, it was confirmed that the safety wire test technique used in the final stage of verification was an effective method to verify flight safety and controllability for a fully unmanned helicopter system.

• Journal of the Korean Home Economics Association
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• v.23 no.4
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• pp.61-68
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• 1985

This study was conducted in a Korean airline catering operation where about 8, 000~10, 000 in flight meals per day were served. Time ad temperature observations were made in an actual airline catering operation to determine critical control points in mushroom and cheese omelet production, and to provide guidelines for the effective quality control programs of the airline catering operation. All data collection was replicated three times. Time and temperature data were collected by using standard instruments throughout the process sequence. Most phases of the food prodct flow were identified as critical control points. Holding phases of after cooking, and before and after reheating need a special attention, since foods were held at room temperature. Several guidelines were suggested for the effective quality control programs for the airline catering operation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.109-114
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• 2008

This paper presents the development status of a subscale precooled turbojet engine "S-engine" for the hypersonic cruiser and space place. S-engine employs the precooled-cycle using liquid hydrogen as fuel and coolant. It has $23cm{\times}23cm$ of rectangular cross section, 2.6 m of the overall length and about 100 kg of the target weight employing composite materials for a variable-geometry rectangular air-intake and nozzle. The design thrust and specific impulse at sea-level-static(SLS) are 1.2 kN and 2,000 sec respectively. After the system design and component tests, a prototype engine made of metal was manufactured and provided for the system firing test using gaseous hydrogen in March 2007. The core engine performance could be verified in this test. The second firing test using liquid hydrogen was conducted in October 2007. The engine, fuel supplying system and control system for the next flight test were used in this test. We verified the engine start-up sequence, compressor-turbine matching and performance of system and components. A flight test of S-engine is to be conducted by the Balloon-based Operation Vehicle(BOV) at Taiki town in Hokkaido in October 2008. The vehicle is about 5 m in length, 0.55 m in diameter and 500 kg in weight. The vehicle is dropped from an altitude of 40 km by a high-altitude observation balloon. After 40 second free-fall, the vehicle pulls up and S-engine operates for 60 seconds up to Mach 2. High altitude tests of the engine components corresponding to the BOV flight condition are also conducted.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.7
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• pp.83-90
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• 2004

This paper describes on-board decentralized data acquisition system that acquires and encodes the numerous sensor data distributed on the big flight vehicles efficiently. The system's sub-units which have one encoder unit and several remote units were designed and simulated according to the communication protocols and the control, sequence logics based on the FPGA chip. And we have made the functional verification of the acquisition, collection and formatting of remote analog and digital data for the manufactured hardwares.

• Aerospace Engineering and Technology
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• v.2 no.1
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• pp.140-152
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• 2003

Scenario is a guiding principle of launch operation and control for rocket and ground support system. Therefore, developing a scenario is the first step to prepare for rocket launch, which is a critical task for success of KSR-III flight test. The launch scenario for KSR-III flight test is a procedural sequence of command and control signals to be given to rocket and ground support systems. In this paper, the UML object modeling method is applied to development of a launch scenario. First, the subsystems of the launch system are modeled by objects, and then the interfaces between each two subsystems are modeled by association links. The finally obtained object diagram of KSR-III launch system is used to analyzing flow of data and commands and control signals, and interactions. The scenario includes the sequences of pre-launch/launch operations and emergency operations.

• Journal of Microbiology and Biotechnology
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• v.25 no.11
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• pp.1954-1959
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• 2015

Bacillus subtilis HM1 was isolated from the rhizosphere region of halophytes for its antifungal activity against Colletotrichum acutatum, the causative agent of anthracnose. Treatment of postharvest apples with the cell culture or with a cell-free culture supernatant reduced disease severity 80.7% and 69.4%, respectively. Both treatments also exhibited antifungal activity against various phytopathogenic fungi in vitro. The antifungal substances were purified and analyzed by acid precipitation, gel filtration, high-performance liquid chromatography, and matrix-assisted laser desorption ionization-time of flight mass spectrometry (MALDI-TOF MS). Three compounds were identified as fengycin, iturin, and surfactin. The MALDI-TOF/TOF mass spectrum revealed the presence of cyclized fengycin homologs A and B, which were distinguishable on the basis of the presence of either alanine or valine, respectively, at position 6 of the peptide sequence. In addition, the cyclized structure of fengycin was shown to play a critical role in antifungal activity.

• Journal of Advanced Navigation Technology
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• v.19 no.2
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• pp.108-115
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• 2015

Multilateration systems are used to provide the position of aircraft in flight or on airport runways. In the multilateration systems, the interrogator is an important transmitter that used to interrogate the airplanes with appropriately scenario in surveillance airspace. Whisper-Shout interrogation sequence, which is one of the key functions of the interrogator, can control airport traffic density when intruder airplanes are coming into the surveillance airspace. Therefore collision chance between airplanes could be reduced and also get highly accurate location of incoming airplane in multilateration systems. In this paper, we developed the interrogator that allows it to transmit Mode A/C and Mode S interrogations which is similar to existing secondary surveillance radar. With appropriately controlled Whisper-Shout sequence in the interrogator, the multilateration systems can avoid synchronous garbling and FRUIT phenomenons caused by receiving multiple responses from a number of airplanes.