• Aerospace Engineering and Technology
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• 제11권2호
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• pp.109-116
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• 2012

A vent-relief valve performs as a safety-valve assembly for liquid propellant feeding system of space launch vehicle, which relives pressurant propellant tanks during the filling and the flight. At vent mode, valve is opened and closed by driving pneumatic pressure, and at relief mode, valve is automatically operated to set relief pressure. In this study, we have analyzed a basic layout of vent-relief valve which is designed using foreign LVs(Saturn) to satisfy requirements of Korean Space Launch Vehicle. The simulation model of vent-relief valve is designed by using the AMESim code to verify design parameters and evaluate pneumatic behaviors of valve. In this study, we performed dynamic characteristic simulations on design parameters. And we could predict opening/closing time and pressures, operating performances on design parameters. Using this results, we could suggest detail design and boundary conditions of design.

• Composites Research
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• 제19권5호
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• pp.12-19
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• 2006

In this paper, conceptual structural design of the main wing for a small scale WIG(Wing in Ground Effect) among high speed ship projects, which will be a high speed maritime transportation system for the next generation in Rep. of Korea, was performed. The Carbon/Epoxy material was selected for the major structure, and the skin-spar with a foam sandwich structural type was adopted for improvement of lightness and structural stability. As a design procedure for the present study, firstly the design load was estimated through the critical flight load case study, and then flanges of the front and rear spars from major bending loads and the skin and the spar webs from shear loads were preliminarily sized using the netting rule and the rule of mixture. Stress analysis was performed by a commercial FEA code, NASTRAN. From the stress analysis results for the first designed wing structure, it was confirmed that the upper skin between the front spar and the rear spar was unstable fer the buckling. Therefore in order to solve this problem, a middle spar and the foam sandwich type structure at the skin and the web were added. After design modification, the structural safety and stability for the final design feature was confirmed. In addition to this, the insert bolt type structure with eight high strength bolts to fix the wing structure to the fuselage was adopted for easy assembly and removal as well as in consideration of more than 20 years fatigue life.

• The Journal of Bigdata
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• 제6권2호
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• pp.29-38
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• 2021

Deviation of route in aviation safety management is a dangerous factor that can lead to serious accidents. In this study, the anomaly score is calculated by classifying the tracks through clustering and calculating the distance from the cluster center. The study was conducted by extracting tracks within 100 km of the airport from the ADS-B track data received for one year. The wake was vectorized using linear interpolation. Latitude, longitude, and altitude 3D coordinates were used. Through PCA, the dimension was reduced to an axis representing more than 90% of the overall data distribution, and k-means clustering, hierarchical clustering, and PAM techniques were applied. The number of clusters was selected using the silhouette measure, and an abnormality score was calculated by calculating the distance from the cluster center. In this study, we compare the number of clusters for each cluster technique, and evaluate the clustering result through the silhouette measure.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• 제38권1호
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• pp.35-41
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• 2010

In developing modern aircraft, the reconfiguration control that can improve the safety and the survivability against the unexpected failure by partitioning control surfaces into several parts has been actively studied. This paper deals with the reconfiguration control using model predictive control method considering the saturation of control surfaces under the control surface failure. Linearized aircraft model at trim condition is used as the internal model of model predictive control. We propose the controller that performs optimization using LMI (linear matrix inequalities) based semi-definite programming in case that control surface saturation occurs, otherwise, uses analytic solution of the model predictive control. The performance of the proposed control method is evaluated by nonlinear simulation under the flight scenario of control surface failure.

• Journal of Aerospace System Engineering
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• 제10권4호
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• pp.105-114
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• 2016

The world is currently confronted with regional conflicts among nations that seek to protect their territory. The associated counter-terrorism activities and international business flows can be increased through airworthiness-recognition tasks that are related to aircraft exports, dispatch troops, and overseas bases. It is important to establish airworthiness-recognition processes between foreign military authorities to minimize the potential for sovereign national positions and responsibilities. For this study, the military airworthiness recognition between recognition partners was surveyed to secure flight safety for the development and operation of aircrafts. The analysis of the U.S. and European Military Authority Recognition Questionsets (MARQs) in this paper introduces the rules, inspection capabilities, production process, and certification of the airworthiness authority. The regulatory activities, which are required by the Korea Military Airworthiness Authority (MAA) with respect to foreign MAAs, can be reduced by the implementation of the MARQ.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 한국항해항만학회 2009년도 공동학술대회
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• pp.19-20
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• 2009

International Maritime Organization(IMO) recommends the installation of an Automatic Identification System(AIS) according to requirements by SOLAS Chapter 5 to avoid maritime collision. AIS provides traffic information of other ships that may be used for maritime traffic control, SAR(Search and Rescue) and collision avoidance to apply safety management. In this paper, preliminary results to implement an aeronautical surveillance transceiver using AIS transceiver based on ADS-B concepts are described. Although altitude information is not required for AIS since the AIS is operated at MSL(Mean Sea Level), altitude information can be extracted by a GPS chip-set in the ALS transceiver. ADS-B transceiver is implemented by defining a surveillance message format including the altitude information and modifying SOTDMA protocol. Ground tests and flight tests are performed to validate the implementation results.

• Journal of the Korea Institute of Military Science and Technology
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• 제25권6호
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• pp.628-636
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• 2022

This paper describes the design of the avionics architecture for military unmanned aerial vehicles considering the airworthiness requirements for the first time. This design considers the redundancy in the system data bus and the power system and the data link system to meet the system safety requirements of the airworthiness requirements of military UAVs. This avionics architecture design has been verified through the system integration test and the flight test after manufacturing the UAV.

• Journal of Navigation and Port Research
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• 제33권10호
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• pp.685-690
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• 2009

International Maritime Organization (IMO) recommends the installation of an Automatic Identification System (AIS) according to requirements by SOLAS to avoid maritime collision. AIS provides traffic information of other ships that may be used for maritime traffic control, SAR (Search and Rescue) and collision avoidance to apply safety management. In this paper, preliminary results to implement an aeronautical surveillance transceiver using AIS transceiver based on ADS-B concepts are described. Although altitude information is not required for AIS since the AIS is operated at MSL (Mean Sea Level), altitude information can be extracted by a GPS (Global Positioning System) chip-set in the AIS transceiver. ADS-B transceiver is implemented by defining a surveillance message format including the altitude information and modifying SOTDMA (Self-Organizing Time Division Multiple Access) protocol. Ground tests and flight tests are performed to validate the implementation results.

• Journal of Advanced Navigation Technology
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• 제27권6호
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• pp.699-709
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• 2023

As the global air traffic volume has shown a rapid increase, doubling every 15 years since 1977, domestic and international air traffic control services and air navigation safety facility operation management system and status review It is necessary to present the feasibility of establishing an air traffic control agency with integrated functions and establish an operating system for an independent dedicated agency to provide advanced air traffic control services in preparation for the future air transport environment. In particular, in 2021, the national ATM reformation and enhancement (NARAE) a customized comprehensive plan for operations, facilities, and systems to handle air traffic safely and efficiently by actively reflecting changes in the navigation environment such as international policies and standards as this is established, the role of the air traffic control agency becomes more important, and an improved action plan for the control and navigation operating system must be promoted.

• Journal of Advanced Navigation Technology
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• 제28권4호
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• pp.393-399
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• 2024

The digital map computer for advanced air vehicles (AAV) must be high-performance, lightweight, portable, and modular. It should receive data on terrain, weather, and obstacles from external modules to display digital maps accurately. This necessitates robust communication capabilities with external devices via an Ethernet interface and the ability to output digital map visuals clearly through an high-defintion multimedia Interface (HDMI) or digital visual interface (DVI) interface. This paper presents the design of both hardware and software architecture that fulfills these critical requirements for an AAV digital map system. Additionally, it establishes the minimum specifications needed and verifies the suitability of the designed digital map computer through rigorous performance measurements and testing. By ensuring these standards, the digital map computer can reliably support the complex navigational needs of AAV, enhancing operational efficiency and safety.