• Journal of the Korea Institute of Military Science and Technology
• /
• v.25 no.3
• /
• pp.311-320
• /
• 2022

In this paper, we studied the optimal method of improving performance for aircraft having various variants within the same type. The study defined configuration of an entire fleet of aircraft being subject to a performance improvement program. And selected the most complicated aircraft configuration among them as a Standard Aircraft for modification by according to the proposed Aircraft Selection Process for developing an optimal Aircraft Performance Improvement Process. Based on the selected the Standard Aircraft, drew a system integration design result and carried out Evaluation Test and obtained Airworthiness Certification. Created the database with the design data of the Standard Aircraft, Evaluation Test, and Airworthiness Certification results, and applied it to variants of aircraft to complete the performance improvement program with optimized schedules and costs. By applying the proposed method to IFF performance improvement program, drew optimal system integration design and completed the program with minimized schedule.

• Journal of IKEEE
• /
• v.28 no.3
• /
• pp.243-252
• /
• 2024

In this paper, we proposed a performance improvement to replace the aged intercom of military aircraft with a new intercom ICS, and briefly designed and presented a interface block diagram and electrical wiring path for the connection between the new intercom ICS and the other avionics equipment. However, due to the absence of a guide necessary for the proposed design, this paper derived 15 main design elements by using the QFD technique based on the military aircraft airworthiness certification criteria and military aircraft work instructions. As a result, it is meaningful that the interface block diagram, wiring path diagram, and the 15 main design elements proposed in this paper can be applied as an electrical system design guide for the performance improvement of the aged military intercom in the future.

• Journal of Aerospace System Engineering
• /
• v.17 no.4
• /
• pp.87-94
• /
• 2023

This paper addresses the installation and modification design of airframe structures for new and modified equipment installations that are essential for aircraft performance improvement. Typical performance improvement equipment mounted on the exterior of the aircraft include antenna, radar, electro-optical/infrared (EO/IR), and self-protection system equipment, which require structural reinforcement, modification, and mounting design of the green aircraft for operation. In the interior of the aircraft, console and rack structures are modified or added according to user operation requirements. In addition, this is accompanied by the installation design of equipment to be replaced and added for performance improvement, and the according modification of environmental control system components for internal cooling. The engineering process and cases in which airworthiness was verified through the detailed design of airframe structures with structural integrity, operability, and maintainability of performance-improved aircraft are presented.

• Journal of the Korean Society for Aviation and Aeronautics
• /
• v.31 no.2
• /
• pp.81-88
• /
• 2023

SHM (Structural Health Monitoring) technique for monitoring aircraft structural health and damage, EHM (Engine Health Monitoring) for monitoring aircraft engine performance, and APM (Application Performance Management) is used for each function. APMS (Airplane Performance Monitoring System) is a program that comprehensively applies these techniques to identify the difference between the performance manual provided by the manufacturer and the actual fuel mileage of the aircraft and reflect it in the flight plan. The main purpose of using APMS is to understand the performance of each aircraft, to plan and execute flights in an optimal way, and consequently to reduce fuel consumption. First, it is to check the fuel efficiency trend of each aircraft, check the correlation between the maintenance work performed and the fuel mileage, find the cause of the fuel mileage increase/decrease, and take appropriate measures in response. Second, it is to find the cause of fuel mileage degradation in detail by checking the trends by engine performance and fuselage drag effect. Third, the APMS is to be used in making maintenance work decisions. Through APMS, aircraft with below average fuel mileage are identified, the cause of fuel mileage degradation is identified, and appropriate corrective actions are determined. Fourth, APMS data is used to analyze the economic analysis of equipment installation investment. The cost can be easily calculated as the equipment installation cost, but the benefit is fuel efficiency improvement, and the only way to check this is the manufacturer's theory. Therefore, verifying the effect after installation and verifying the economic analysis is to secure the appropriateness of the investment. Through this, proper investment in fuel efficiency improvement equipment will be made, and fuel efficiency will be improved.

• Journal of IKEEE
• /
• v.26 no.4
• /
• pp.560-567
• /
• 2022

This paper proposed an application of agile management method to resolve the electrical system issues identified during the mass production phase of aged aircraft performance improvement. The proposed method was applied from issue analysis to on-site verification and testing stage, before the formal configuration control process. At this time, the project was carried out by setting a sprint period to complete the verification according to requirements through daily scrum and sprint review. As a result, It was verified that the wiring installation of the aircraft, which was the output of the sprint, met requirements within the defined sprint period.

• Journal of the Korean Society for Aviation and Aeronautics
• /
• v.29 no.3
• /
• pp.44-51
• /
• 2021

PIP is an abbreviation of 'Performance Improvement Package', which is a package that can improve performance by applying some design changes to existing aircraft. Boeing provides PIP applicable to B777-200, and Airbus provides PIP applicable to A350-900 as standard. PIP provided by Boeing and Airbus is a separate task, but it is expected to reduce fuel consumption by reducing drag through aerodynamic improvements. The PIP applied to the A350-900 includes work such as increasing Winglet Height and re-twisting Outboard Wing. This study is to verify the effect of PIP application of the A350-900 aircraft and use it as basic data for economic analysis. The aerodynamic improvement studies and expected effects of the PIP application were examined, and the actual flight data of the PIP-applied and the non-applied aircraft were compared to confirm the PIP application effect. This paper provides empirical results for the aviation industry on the PIP application efficiency as a method of improving fuel efficiency and reducing carbon emission.

• Transactions of the Korean Society for Noise and Vibration Engineering
• /
• v.14 no.3
• /
• pp.214-223
• /
• 2004

This study aim to find an appropriate window for classrooms to provide proper sound insulation against aircraft noise and to achieve this goal, measurements were taken of the sound insulation performance of windows with various thicknesses of inner air space and sound absorption materials in the inner air spaces. As a result of this study the improvement of the sound insulation performance of windows(single, double and triple window) was shown through the analysis and the measuring of windows with these characteristics. These results may be applied to the manufacture of window frames and provide basic data for the improvement of the sound insulation performance of windows.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
• /
• 2003.11a
• /
• pp.710-717
• /
• 2003

This study aim to find an appropriate window for class rooms to provide proper sound insulation against aircraft noise and to achieve this, measurements were taken of the sound insulation performance of windows with varying thicknesses of inner air space and sound absorption materials in the inner air spaces. As a result of (his study the improvement of the sound insulation performance of windows(single , double and triple window) has been shown through the analysis and the measuring of windows with these characteristics. These results may be applied to the manufacture of window frames and provide data lot the improvement of the sound insulation performance of windows.

• Journal of Internet Computing and Services
• /
• v.23 no.1
• /
• pp.113-124
• /
• 2022

In wartime conditions, the communication system of military aircraft is exposed to jamming, and it is necessary to mount communication equipment with high anti-jamming performance in order to perform air operations smoothly even in an environment where jamming attempts are made. In this paper, we check in detail the jamming and anti-jamming technology that can be applied to wireless communication, and the data disclosed on the difference in specifications of the next-generation anti-jamming radio with frequency hopping method and the improvement of anti-jamming performance according to these changes. It was briefly analyzed within the scope. In addition, the points to be considered when designing a new domestic aircraft and the possibility of installing the next-generation anti-jamming communication equipment on the currently operating aircraft were confirmed, and the tactical usefulness of improving the anti-jamming capability of the next-generation anti-jamming communication equipment was confirmed.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.25 no.3
• /
• pp.292-299
• /
• 2022

In this paper, we proposed an automatic TOD synchronization and verification method for improving the performance of air-to-ground radio(hereafter SATURN) of legacy aircraft. In order to automatically synchronize TOD with SATURN radio, it is proposed to modify the GPS antenna installed in the existing aircraft according to the minimum operating performance standard. In addition, test methods and results are presented to verify the TOD information generation capability before and after the GPS antenna modifying. It is expected that the automatic TOD synchronization method proposed in this paper can be applied to the SATURN performance improvement design.