• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.606-608
• /
• 2017

The computational fluid analysis was carried out to investigate structural stability of exhaust duct for turboprop engine. In order to calculate the thrust and shear force acting on the flight condition of the aircraft, the flow in the exhaust duct and the flow in the direction of the exhaust duct flange were analyzed by Fluent software to obtain thrust, shear force and bending moment. As a result of the analysis, it was confirmed that the allowable loads set idle engine manual were not exceeded.

• Journal of Aerospace System Engineering
• /
• v.13 no.4
• /
• pp.60-65
• /
• 2019

This study did a structural design of a fuel system of auxiliary fuel tank applied to aircraft then analyzed it. The safety of the structural design result was investigated. Aluminum alloy metal structure was applied to the fuel system structure. The structural analysis was conducted using commercial finite element software. The design requirement was maximum accelerate condition of the structure. Therefore, structural design was done considering the maximum accelerate condition.

• Journal of Aerospace System Engineering
• /
• v.8 no.2
• /
• pp.21-26
• /
• 2014

The aircraft manufacturers are constantly driving to reduce manufacturing lead times and cost at the same time as the product complexity increases and technology continues to change. Integrated Modular Avionics (IMA) is a solution that allows the aviation industry to manage their avionics complexity. IMA defines an integrated system architecture that preserves the fault containment and 'separation of concerns' properties of the federated architectures. In software side, the air transport industry has developed ARINC 653 specification as a standardized Real Time Operating System (RTOS) interface definition for IMA. It allows hosting multiple applications of different software levels on the same hardware in the context of IMA architecture. This paper describes a study that provided the avionics software design for separation of fault and backup of core function to reduce workload of pilot with cost efficiency.

• Journal of Aerospace System Engineering
• /
• v.16 no.1
• /
• pp.97-103
• /
• 2022

An aircraft component can only be mounted on an aircraft if it has been certified to have a structural robustness under flight load conditions. Among the major components of the aircraft, a pylon is a structure that connects external equipment such as an engine, and external attachments with the main wing of an aircraft and transmits the loads acting on it to the main structure of the aircraft. In civil aircraft, when there is an incident of fire in the engine area, the pylon prevents the fire from spreading to the wings. This study presents the results of structural static tests performed to verify the structural robustness of a fuel pylon used to mount external fuel tank in an aircraft. In the main text, we present the test set-up diagram consisting of test fixture, hydraulic pressure unit, load control system, and data acquisition equipment used in the structure static test of the fuel pylon. In addition, we introduce the software that controls the load actuator, and provide a test profile for each test load condition. As a result of the structural static test, it was found that the load actuator was properly controlled within the allowable error range in each test, and the reliability of the numerical analysis was verified by comparing the numerical analysis results and the strain obtained from the structural test at the main positions of the test specimen. In conclusion, it was proved that the fuel pylon covered in this study has sufficient structural strength for the required load conditions through structural static tests.

• Journal of the Society of Disaster Information
• /
• v.20 no.1
• /
• pp.232-243
• /
• 2024

Purpose: Recently, large-scale forest fires caused by climate change, natural disasters, and human factors have been increasing every year in the East Coast and Taebaek Mountains region. Although forest fire extinguishing using helicopters is currently increasing, the need to introduce air force transport aircraft has continued to be raised due to the importance of early fire extinguishment to respond to large forest fires and the difficulty of extinguishing forest fires between sheep. This study seeks to present a plan for developing a post-fire management system for several aspects - achieving operational objectives, overcoming the operating environment, selecting a staging area, and efficient operation measures - to efficiently perform forest fire extinguishing missions using Air Force transport aircraft. Method: Based on literature research on forest fire extinguishing, forest fire extinguishing experiments using fixed-wing aircraft, and the operation status and operation method of forest fire extinguishing helicopters, the pros and cons of helicopter operation and the effects of large forest fire extinguishing using a large transport aircraft (C-130) Analyze the effectiveness of operation through analysis. Results: When extinguishing a large forest fire, an effective CM (Consequence Management) application plan was derived, including effective operation, control, command system, dispatch request, and forest fire extinguishment when integrating helicopter and fixed-wing aircraft (C-130). Conclusion: The application of the concept of CM (Consequence Management) is partially applied to some areas of chemical, biological, and radiological (CBRNE) protection in Korea, but efficient operation, control, and command systems are established when integrated operation of helicopters and large aircraft (C-130) in forest fire extinguishment. the concept of CM (Consequence Management), which is operated in advanced countries, was applied for safety management, dispatch requests, and forest fire extinguishing, thereby contributing to the establishment of a more advanced disaster and post-disaster management system.

• Journal of Advanced Navigation Technology
• /
• v.20 no.4
• /
• pp.275-284
• /
• 2016

The potential impact of aircraft emissions on the current and projected climate of our planet is one of the more important environmental issues facing the aviation industry. Increasing concern over the potential negative effects of greenhouse gas emissions has motivated aircraft emission estimation and prediction as one of the ways to reduce aircraft emissions and mitigate the impact of aviation on climate. We obtained airline flight schedules for all the airports in Korea that are included in OAG data. Fuel burn and emission index of LTO flight which contains take off, climb and approach under 3000ft and Non LTO flight which contains climb, cruise and descent over 3000ft for all the airports in Korea in 2005 were estimated and analysed for each condition using AEIC software which has been developed by MIT Lab for Aviation and Environment.

• Transactions of the Korean Society of Mechanical Engineers A
• /
• v.41 no.2
• /
• pp.129-136
• /
• 2017

This study aims to assess the damage tolerance of the wing structure of aged aircraft with long-term service through the fatigue crack growth analysis and tests. For the fatigue-critical locations (FCL) W2 and W4 in the wing structure, the fatigue stress spectrum was derived based on a previous study. Thereafter, a crack propagation analysis for the FCLs was conducted using the commercial software $NASGRO^{TM}$. The algorithm for the fatigue stress spectrum was verified. Fatigue crack growth tests were then performed for two types of specimens: Type #1 was extracted from the wing structure of aged aircraft, and Type #2 was made of the same material as the wing structure. By comparing the experimental results of these specimens, we assessed the damage tolerance of the wing structure of aged aircraft with service time.

• International Journal of Aeronautical and Space Sciences
• /
• v.16 no.1
• /
• pp.1-7
• /
• 2015

In order to provide some references for suitability of carrier-based aircrafts, this paper studies the flow field of exhaust jets and its impact on the flight deck. The geometrical models of aircraft carrier and carrier-based aircrafts are firstly built, on which unstructured tetrahedral meshes are generated for numerical analysis. Then, this paper simulates the flow field of exhaust jets to evaluate its impact on the Jet Blast Deflector (JBD) and the flight deck, when four carrier-based aircrafts are ready to start off in the bow. The standard k-${\varepsilon}$ equations, three-dimension N-S equations and the Computational Fluid Dynamics (CFD) theory are used in the analysis process. To solve the equations, the thermal coupling of the wind and the jet flow are also considered. The velocity and temperature distributions are provided with the simulation of the CFD software, FLUENT. The results indicate that: (1) this analytical method can be used to simulate aerodynamic problems with complex geometrical models, and the results are of high reliability; (2) the safety working area, the installation scheme of the JBD and the arrangement of the take-off position can be optimized through analysis.

• Journal of the Korea Society of Computer and Information
• /
• v.24 no.10
• /
• pp.1-9
• /
• 2019

Fighter pilots are taking 'Advanced Pilot Training' courses to perform their missions perfectly even under adverse conditions. However, there are accidents that fall due to problems with the human body's equilibrium in the acceleration of flight, falling into the 'Vertigo, Spatial disorientation' phenomenon. As such, accidents that fighters fall due to spatial disorientation frequently occur not only in Korea but also abroad. In this study, we implemented the 'Vertigo' warning function in the fighter. First, we analyzed the aircraft's mission computer and the currently implemented warning functions. And we studied the coordinate system to utilize the aircraft attitude information. Based on this, we wanted to provide a visual warning to the HUD when the fighter flies over a certain time in the inverted flight position. Implementing this feature is expected to improve pilot flight safety. In addition, based on the results of this study, we propose a method to implement warning functions through linkage with other subsystems.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.49 no.6
• /
• pp.505-513
• /
• 2021

We propose an autonomous mission management software design and verification technique for unmanned aerial vehicles to autonomously mitigate dynamic situation changes occurred in the inside and outside of an aircraft in compliance with the mitigation priority order. The proposed autonomous mission management software is designed in a modular architecture that consists of concurrently executing multiple threads. To verify it, we suggest three verification steps: 1) software integration by checking the expected request/response messages between the threads for all possible dynamic situation changes; 2) integration test to verify the software functionality; 3) performance test to verify the quantitative software performance. Especially, the software integration test environment is built and utilized to carry out the integration and performance tests.