• 한국군사과학기술학회지
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• 제25권3호
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• pp.311-320
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• 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.

• 항공우주시스템공학회지
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• 제15권4호
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• pp.47-56
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• 2021

In the management of aged aircraft, used avionics equipment is replaced with new ones to improve the performance and extend the life cycle of the aircraft. In this case, considering airworthiness, it is necessary to check whether the aircraft has sufficient electricity in the electric generator or the electrical distribution system, in accordance with the maximum electricity consumption of the new avionics equipment. Accordingly, this paper reviews a few airworthiness standards and guidelines associated with the electrical load analysis when an avionics equipment is upgraded in an aged aircraft, and proposes an optimization method for the electrical load analysis. In addition, it verifies the validity of the proposed method via the QFD theory, and is currently available for upgrading the performance of aged aircraft.

• Journal of Positioning, Navigation, and Timing
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• 제1권1호
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• pp.45-49
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• 2012

The flight performance evaluation of navigation system is very significant because the reliability of navigation data directly affect the safety of aircraft. Especially, the high-level navigation system such as DGPS/INS, need more precise flight performance evaluation method. The performance analysis is evaluated by comparing between the navigation system in aircraft and reference trajectory which is more precise than navigation system in aircraft. In order to verify DGPS/INS performance of m-level, the GPS receiver, which is capable post-processed Carrier-phase Differential GPS(CDGPS) method of cm-level, have to be used as reference system. The DGPS/INS is estimated the Center of Gravity (CG) point of aircraft to offer precise performance while the reference system is output the position of GPS antenna which is mounted on the outside of aircraft. Therefore, in order to more precise performance evaluation, it needs to compensate the lever arm and coordinates transformation. This paper use quaternion and Direct Cosine Matrix(DCM) methods as coordinate transformation matrix in lever arm compensation of CDGPS reference trajectory. And it compares NED errors of DCM and quaternion transformation in lever arm of reference trajectory via DGPS/INS result.

• 한국인터넷방송통신학회논문지
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• 제18권5호
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• pp.89-95
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• 2018

본 논문에서는 항공기에서 사용되는 방향 탐지용 안테나가 항공기에 장착 될 경우, 항공기 구조, 회절과 반사에 의한 안테나 성능 변화를 분석하였다. 방향 탐지용 안테나는 항공기 전자전 체계(Electronic Warfare System)의 방향 탐지(DF : Direction Finding) 장치에서 레이더 위협 신호를 수신하는 안테나이다. 최근 항공기에 다양한 안테나가 장착되므로 탑재된 안테나 성능 해석 및 안테나 간섭 분석 등의 다양한 해석이 요구되고 있다. 본문에서는 모사된 항공기에 50% 대역폭을 가지는 광대역 방향 탐지용 안테나를 장착하여 전자파 해석을 진행하였고, 안테나의 단일 성능과 항공기에 탑재된 성능을 비교하여 방향 탐지 성능을 분석하였다. 분석된 방향 탐지 정확도는 $6.47^{\circ}$ RMS를 가지며 항공기 방향 탐지용 안테나로 적합함을 예측하였다.

• 한국추진공학회지
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• 제6권3호
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• pp.1-7
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• 2002

항공기 개발초기 단계에서 주어진 항공기 임무요구도를 만족하는 최적 설계에 도달하기 위해서는 많은 엔진/기체 조합형상에 대한 적합성평가가 이루어지게 되며, 이를 위해서는 정확한 엔진장착성능을 산정할 수 있는 기법의 확립이 매우 중요하다. 본 연구에서는 초음속 항공기 개발초기 단계에서 주어진 엔진/기체 형상에 대한 엔진장착성능을 산정할 수 있는 기법을 연구하였다. 이를 위해 추력 -항력 산정 시스템(Thrust minus drag accounting system)에 의거하여 엔진 장착 추력 구성요소를 설정하고 풍동시험결과를 기초로 한 데이터베이스를 활용하여 이들 요소를 산정하였으며, 산정된 엔진 장착성능 결과를 제시하였다.

• 한국항공운항학회지
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• 제19권4호
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• pp.1-5
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• 2011

The free-wing tilt-body aircraft is researched in the flight performance characteristics for center of gravity (CG) change. All of speed, body tilt angle and center of gravity change are simulated to determine the flight envelope by a non-linear 3-DOF mathematical model. In flight, this aircraft configuration changes by the tiltable empennage. Then, flight dynamics distinguishes from those of a conventional fixed-wing aircraft. Though flight performance and trimmability are studied by CG change, the flight model of free-wing tilt-body aircraft is to reduce the hidden risk and to achieve the successful flight test. It is analyzed the flight characteristics by CG change that distinguishes free-wing tilt-body aircraft from the conventional aircraft.

• International Journal of Aerospace System Engineering
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• 제3권2호
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• pp.1-8
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• 2016

The improvements in high performance and agility of modern fighter aircraft have led to improvements in survivability as well. Related to these performance increases are rapid response and adequate deflection of the control surfaces. Most control surface failures result from the failure of the actuator. Therefore, the failure and behavior of the actuators are essential to both combat aircraft survivability and maneuverability. In this study, we investigate the effects of flaperon actuator failure on flight maneuvers of a supersonic aircraft. The flight maneuvers were analyzed using six degrees of freedom (6DOF) simulations. This research will contribute to improvements in the reconfiguration of control surfaces and control allocation in flight control algorithms. This paper compares the results of these 6DOF simulations with the horizontal tail actuator failures analyzed previously.

• 한국항공운항학회지
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• 제19권1호
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• pp.1-6
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• 2011

The free-wing tilt-body aircraft is researched in the flight performance characteristics such as short take-off and landing capability, and reduced sensitivity to gust and center of gravity (CG) change. Due to the main wing separating from the fuselage, the high tiltable empennage, and the stub-wing strongly influencing from the propeller wake, the resulting vehicle aerodynamics and flight dynamics are quite different from those of a conventional fixed-wing aircraft. Using the governing flight dynamics model was studied previously, all of speed and body tilt angle is simulated to determine the flight envelope by a non-linear 3-DOF flight simulation analysis. Though flight performance and trimmability are studied, the flight model of free-wing tilt-body aircraft is to reduce the hidden risk and to achieve the successful flight test. It is analyzed the flight characteristics that distinguishes free-wing tilt-body aircraft from the conventional aircraft.

• 한국항공운항학회지
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• 제28권1호
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• pp.115-121
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• 2020

Recently avionics equipment and its integration are most important part for implementing high performance aircraft system. This trends are emphasized in the military or special purpose aircraft development program. Flight Test Bed Aircraft (hereafter FTB A/C) - by modified commercial aircraft - was key solution to verify function and performance of avionics system for complex aircraft development program for a while, but there are no experience to use it in domestic airspace of ROK. This paper would like to address what act and regulation is necessary to perform flight operation of FTB A/C with keeping a airworthiness and airspace control policy. and then willing to propose what do we do for improving aviation industry.

• 한국항행학회논문지
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• 제28권1호
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• pp.95-101
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• 2024

본 논문에서는 다양한 eVTOL (electric vertical take-off and landing) 항공기의 안전성 평가 수행을 위한 가변형 시뮬레이션 환경을 구축하고자 한다. eVTOL 항공기마다 적용되는 Inceptor, 항공기 동역학 모델, 제어기가 상이하므로, 이를 가변형으로 구성하여 eVTOL 항공기마다 안전성 시험 평가 시뮬레이션을 수행할 수 있도록 구성하였다. eVTOL 항공기의 안전성 평가 수행을 위한 시험 항목 및 성능 지표를 설정하였으며, 시험 항목별 시험절차에 따라 안전성 시험 평가 시 필요한 지상보조설비를 구상하여 시뮬레이션 환경에 구현하였다. 또한, 시뮬레이션 내 eVTOL 항공기의 데이터를 활용한 안전성 성능 분석을 위해 MATLAB/Simulink 기반의 시뮬레이션 비행데이터 수집 환경을 구축하고, 안전성 성능 분석을 위한 툴을 구현하였다. 최종적으로 본 논문에서 구현한 가변형 시뮬레이션 환경에서의 안전성 시험 비행 수행 및 성능 분석을 수행하였으며, 정상적으로 수행되는 것을 확인함으로써 시뮬레이션 환경을 검증하였다.