• Journal of the Korea Institute of Information and Communication Engineering
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• v.22 no.2
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• pp.354-361
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• 2018

This paper describe the Lateral Navigation algorithm design and verification that implementation on Mission Computer's OFP for Korean Utility Helicopter(KUH) instead of Auto Flight Control System(AFCS) Vehicle Management System. The LNAV function transmits Roll command into the AFCS System. The Roll command value will be calculated by control algorithms in MC. The Operational Flight Program(OFP) shall use for its calculations different measurements of the aircraft's attitude and place. Using these inputs, the OFP will translate a navigational demand(for example-to perform the selected flight plan) into Roll commands to the autopilot. By conducting integration test using SIL and ground test, flight test, it is confirmed that the introduced algorithm meets the requirements of the Mission Equipment Package(MEP) system. LNAV function is verified through the System Integration Laboratory(SIL) test, ground and flight test.

• Journal of Aerospace System Engineering
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• v.12 no.5
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• pp.48-53
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• 2018

In this study, Real-Time Operating System(RTOS) and 3-D collision avoidance algorithm are implemented to three different Miciro Controller Unit(MCU)s and their performances compared. We selected Microchip Technology's ATmega2560, STM's ARM Cortex-M3 and ARM Cortex-M4, because they are widely used. FreeRTOS, an open-source operating system, was also used. The 3D collision avoidance algorithm consists of the vertical and the horizontal avoidance algorithm, which is implemented using C++. The performances of the MCUs were compared with respect to used memory and calculation time. As a result, Cortex-M4's calculation time was the fastest and ATmega2560 used least memory.

• KSCE Journal of Civil and Environmental Engineering Research
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• v.26 no.3D
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• pp.511-517
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• 2006

In this paper, we studied the techniques to analyze the flying safety area focused on the air base rules for military that has been the criteria of the altitude restrictions around the airfield for both civilian and military purposes in Korea. We wanted to present the effective method to analyze the restricted area and to help solving problems that could result recently from the altitude restrictions around the airfield at the beginning of the development projects. To do this we proposed the methods to effectively generate the model of the flying safety area in accordance with the air base rules using 3D GIS techniques and to automatically identify the obstructions caused by the natural and man-made features in those areas. To apply the proposed methods actually to the airfield chosen for the study area, we presented the approaches to generate geospatial informations based on the commercial digital maps and satellite imagery and by generating the flying safety area model, identifying the obstructions, and visualizing the integrated model for the flying safety area analysis we showed the practical usability of the proposed techniques.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.5
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• pp.50-56
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• 2005

The objective of this study is to find the optimal thrust condition and wing loading of a vertical take-off and landing (VTOL) fixed-wing aircraft through a single engine failure analysis during landing approach and an analysis of transition flight. The aircraft analysis modules used in the study are based on the aircraft synthesis program. To achieve the computing infrastructure for aircraft design and analysis, the EMDIOS was employed as a design framework, which is a semi-completed application program and ready to customize. Simulation results reveal the most critical height at the event of single engine failure is approximately 40 ft. And, in order to avoid a significant loss in altitude during the transition, the thrust to weight ratio must be kept high, while both the engine tilt speed and the wing loading must be kept low, as confirmed by the analysis results.

• Journal of Advanced Navigation Technology
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• v.25 no.5
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• pp.336-343
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• 2021

Avionics corresponds to the brain, nerves and five senses of an aircraft, and consists of aircraft mounted electronic equipment of communication, identification, navigation, weapon, and display systems to perform flight and missions. It occupies about 50% of the aircraft system, and its importance is increasing as the technology based on the 4th industrial revolution is developed. As the development period of the aircraft is getting shorter, it is definitely necessary to develop a stable avionics SIL in a timely manner for the integration and verification of the avionics system. In this paper, we propose a method to replace the legacy SIL with the avionics simulation model framework based one and evaluate the framework based on the result of alternative application.

• Proceedings of the Korean Information Science Society Conference
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• 2006.06c
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• pp.232-234
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• 2006

항공기, 핸드폰, 자동차 등 여러 분야에서 내장형 S/W가 사용되고 있다. 내장형 S/W는 일반 S/W와는 달리 운용 및 개발 환경이 특화되고 다양하여 개발비용이 많이 들고 관리에 어려움이 있다. 이러한 문제점들을 해결하기 위하여 미군에서는 공통운용환경(Common Operating System)을 도입하여 시스템들의 통합을 용이하게 하고 상호운용성을 증진하고 있다. 공통운용환경은 운영체계 및 시스템 S/W는 표준화하고 공통으로 재사용가능한 부분을 일종의 컴포넌트라 할 수 있는 세그먼트로 개발하여 재사용하는 개발 및 운용환경을 말한다. 본 논문에서는 공통운용환경의 컴포넌트 기반 개발 방법을 소개하였다. 그리고 내장형 S/W 개발 및 운용에 필요한 내장형 공통운용환경 구조를 정의하고 세그먼트를 설계하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.11
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• pp.969-973
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• 2018

Avionics OFP runs on the mission computer and can be operated by interacting with several avionics equipments. In order to verify OFP SW, SIL having real avionics equipments or models is absolutely necessary. Therefore in many cases SIL is implemented concurrently with OFP developing, and only one SIL is provided to developers. So developers sometimes need an alternative to SIL for verifying requirements in the middle of development process. In this paper, we propose a single PC based STE SW that simulates interworking equipments and verifies OFP in a single PC environment without actual interworking equipments or SIL HW interfaces.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.6
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• pp.540-547
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• 2015

This paper describes development contents and flight tests of an ACMI simulator based on LVC integrating architecture. ACMI is the system that provides air combat training and ground bombing training for improving fighting efficiency, that is the live simulation involving real people to operate real systems. ACMI simulator was developed for technic acquisition of LVC interoperability by using data link communication. ACMI simulator simulated maneuvering of a fighter by operating an UAV, a fighter can be distinguished from an UAV by maneuvering characteristics. This study proposes maneuvering simulation method by using flight data of the UAV, and performed its flight test for verifying similarity of fighter maneuvering.

• Journal of the Economic Geographical Society of Korea
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• v.18 no.3
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• pp.267-280
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• 2015

The European civil aviation industry, which had lower technical skills, capital strength and market scale than the U.S., adopted the production system of joint development and division labor between the nations of Europe. Each plant locations strengthened their specialization of the production branch in the past 40 years with a geographical accumulation of the specialized manufacturing facilities, suppliers, universities and laboratories by the logic of geographical proximity and learning effect. The cargo plane transportation system in the production of short- and medium-haul aircraft facilitated the geographical dispersion of manufacturing process and the logistical linkage among the various plant locations. But the production of long-haul large aircraft(A380) chosen the transportation system by the cargo ship because of the size and weight. Considering the transportation system by the cargo ship, the choice of Toulouse as a final assembly plant location was the irrational locational decision from a locational point of view. This locational choice is explained by the merging process of the European civil aviation industry, the logic of learning effect and geographical proximity, and the active attraction support policy.

• Journal of Platform Technology
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• v.10 no.4
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• pp.25-38
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• 2022

Recently, it is reported that the Korean Unmanned Aerial Vehicle (UAV) interface protocol (K-4586) based on STANAG-4586 is being developed to secure interoperability between UAVs. The core elements of the K-4586-based Unmanned Aircraft System (UAS) are the Core UAV Control System (CUCS), Vehicle Specific Module (VSM), Data Link Interface (DLI), and C4I systems. In UAS based on K-4586, the DLI function for transmitting and receiving messages to link UAVs is included in VSM and CUCS respectively. The Generator/Analyzer (G/A) tool is an apparatus that is developed for protocol conformance verification for VSM and CUCS, and G/A tools with DLI message transmitting and receiving should be developed separately. Core applications (VSM, CUCS, DLI) and G/A tools based on K-4586 may be developed independently depending on the developers. If the DLI message modules are different for each developer, the scope and results of protocol conformance verification will be dissimilar, and some problems may happen during system integration. In this study, common DLI message module based on the API was designed to provide the DLI message transmitting and receiving function necessary to the development of core applications and the protocol conformance verification tool of based on K-4586. When applying the proposed common DLI message module, it can be expected to shorten the UAS system development period and reduce costs, and ensure conformance of protocol. In this paper, the design and implementation method for the common DLI message module based on API was proposed and the results of functional test was described.