• Title/Summary/Keyword: 비행시험 기법

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Flight Compatibility Certification of ALQ-X ECM Pod (ALQ-X ECM 포드 비행 적합성 인증)

  • Jun, Seung-Moon;Lim, Jae-Moon
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.33 no.4
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    • pp.91-99
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    • 2005
  • Flight compatibility certification is performed to substantiate the compatibility between ALQ-X ECM pod and KF-16D/RF-4C aircraft. A certification plan for the ALQ-X flight compatibility is established. Similarity analysis, mass/inertia analysis, structural analysis/test, and ground vibration test/flutter analysis are made to support the safety of MIL-HDBK-1763 Test 250 (Captive compatibility flight profile). Aircraft flew along flight envelope boundary with representative ALQ-X configurations. Handling qualities are evaluated by comparing flight characteristics of the aircraft with and without ALQ-X. Structural integrity and endurance is evaluated using measured flight test data. Results of these flight tests showed that ALQ-X is compatible with KF-16D/RF-4C without altering the flight envelope which has originally been certified for ALQ-88 and ALQ-119 ECM pods. ALQ-X certification program made following technical achievements: Type III certification for foreign designed fighter, flutter analysis program development using GVT results, and utilization of MIL-STD-1553B data bus in flight test.

Vision-based Small UAV Indoor Flight Test Environment Using Multi-Camera (멀티카메라를 이용한 영상정보 기반의 소형무인기 실내비행시험환경 연구)

  • Won, Dae-Yeon;Oh, Hyon-Dong;Huh, Sung-Sik;Park, Bong-Gyun;Ahn, Jong-Sun;Shim, Hyun-Chul;Tahk, Min-Jea
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.37 no.12
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    • pp.1209-1216
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    • 2009
  • This paper presents the pose estimation of a small UAV utilizing visual information from low cost cameras installed indoor. To overcome the limitation of the outside flight experiment, the indoor flight test environment based on multi-camera systems is proposed. Computer vision algorithms for the proposed system include camera calibration, color marker detection, and pose estimation. The well-known extended Kalman filter is used to obtain an accurate position and pose estimation for the small UAV. This paper finishes with several experiment results illustrating the performance and properties of the proposed vision-based indoor flight test environment.

Design and Experiment of Lab-scale Contrail Generator (Lab-scale 비행운 발생장치 설계 및 시험)

  • Choi, Jaewon;Ock, Gwonwoo;Kim, Sangki;Kim, Hyemin
    • Journal of the Korean Society of Propulsion Engineers
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    • v.23 no.4
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    • pp.35-41
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    • 2019
  • Contrail is a kind of cloud that is formed during the flight by vapor condensation of engine exhaust in a cold atmospheric condition. Owing to the negative effects of contrails on the environment and in military applications, several studies for contrail mitigation had been performed in developed countries. The goal of this research is to design a lab-scale contrail generator, and to validate the contrail mitigation technology suggested by previous studies. The contrail generator was made using superheated vapor and a low temperature wind tunnel. Using this generator, the ineffectiveness of ethanol and surfactant suggested in the previous paper on contrail mitigation was found experimentally.

Airborne Pulsed Doppler Radar Development (비행체 탑재 펄스 도플러 레이다 시험모델 개발)

  • Kwag, Young-Kil;Choi, Min-Su;Bae, Jae-Hoon;Jeon, In-Pyung;Yang, Ju-Yoel
    • Journal of Advanced Navigation Technology
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    • v.10 no.2
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    • pp.173-180
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    • 2006
  • An airborne radar is an essential aviation electronic system of the aircraft to perform various missions in all weather environments. This paper presents the design, development, and test results of the multi-mode pulsed Doppler radar system test model for helicopter-borne flight test. This radar system consists of 4 LRU units, which include ANTU(Antenna Unit), TRU(Tx Rx Unit), RSDU(Radar Signal & Data Processing Unit) and DISU(Display Unit). The developed technologies include the TACCAR processor, planar array antenna, TWTA transmitter, coherent I/Q detector, digital pulse compression, DSP based Doppler FFT filtering, adaptive CFAR, IMU, and tracking capability. The design performance of the developed radar system is verified through various helicopter-borne field tests including MTD (Moving Target Detector) capability for the Doppler compensation due to the moving platform motion.

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Autonomous Formation Flight Tests of Multiple UAVs (다수 무인항공기의 자동 편대비행 시험)

  • Song, Yong-Kyu;Heo, Chang-Hwan;Lee, Sang-Jun;Kim, Jung-Han
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.38 no.3
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    • pp.264-273
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    • 2010
  • In this work, autonomous formation flight tests of multiple UAVs are experimentally studied. After a guidance and control system for a UAV is designed and tested, PID formation controller for follower UAV is tested using longitudinal and lateral distance feedback. It is shown that more stable and efficient formation guidance system is obtained by using position and attitude of the leader aircraft, which is exploited to calculate virtual waypoint for follower. In order to improve transient response during turn, part of roll command of the leader is added to the guidance command. Finally, autonomous formation flight test results of 3 UAVs are shown by using the best guidance algorithm suggested.

Redundancy Management Design for Triplex Flight Control System (3중 비행제어시스템의 다중화 기법 설계)

  • Park, Sung-Han;Kim, Jae-Yong;Cho, In-Je;Hwang, Byung-Moon
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.38 no.2
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    • pp.169-179
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    • 2010
  • Satisfying the same probability of loss of control and essentially two fail operative performance with a triplex computer architecture requires a lot of modification of the conventional redundancy management design techniques, previously employed in quadruplex digital flight control computer. T-50 FCS for triplex redundancy management design applied an advanced digital flight control architecture with an I/O controller which is functionally independent of the digital computer to achieve the same reliability and special failure analysis and isolation schemes for fail operational goals with a triplex configuration. The analysis results indicated that the triplex flight control system is to satisfy the safety requirement utilizing the advanced flight control techniques and the system performance of the implemented flight control system was verified by failure mode effect test.

Lever Arm Compensation of Reference Trajectory for Flight Performance Evaluation of DGPS/INS installed on Aircraft (항공기에 탑재된 DGPS/INS 복합항법 장치의 비행 시험 성능 평가를 위한 기준궤적의 Lever Arm 보정)

  • Park, Ji-Hee;Lee, Seong-Woo;Park, Deok-Bae;Shin, Dong-Ho
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.40 no.12
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    • pp.1086-1092
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    • 2012
  • It has been studied for DGPS/INS(Differential Global Positioning System/Inertial Navigation System) to offer the more precise and reliable navigation data with the aviation industry development. 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, as DGPS/INS, need more precise flight performance evaluation method. The performance analysis is performed by comparing between the DGPS/INS navigation data and reference trajectory which is more precise than DGPS/INS. The GPS receiver, which is capable of post-processed CDGPS(Carrier-phase DGPS) method, can be used as reference system. Generally, the DGPS/INS is estimated the CG(Center of Gravity) point of aircraft while the reference system is output the position of GPS antenna which is mounted on the outside of aircraft. For this reason, estimated error between DGPS/INS and reference system will include the error due to lever arm. In order to more precise performance evaluation, it is needed to compensate the lever arm. This paper presents procedure and result of flight test which includes lever arm compensation in order to verify reliability and performance of DGPS/INS more precisely.

The implementation of the firing control system considering a flight sequence control technique (비행시퀀스제어기법을 적용한 점화통제시스템 구현)

  • Lee, Seung-Jae
    • Journal of the Korean Society of Propulsion Engineers
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    • v.12 no.3
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    • pp.41-48
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    • 2008
  • One of main functions of the firing control system applied to a rocket propulsion test has been to provide electric current for ignition of a solid rocket motor. This paper describes the design and implementation of an enhanced firing control system for ground propulsion test that can also control and verify various types of squib events and flight sequences.

Study on On-Sight Image-Based Simulation Method for Predicting and Analyzing Flight Test Results of a Missile (유도무기의 비행시험 결과 예측 및 분석을 위한 현장 영상 기반 시뮬레이션 기법 연구)

  • Jeong, Dong-Gil;Park, Jin-Seo;Lee, Jong-Hee;Son, Sung-Han
    • Journal of the Korea Society for Simulation
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    • v.28 no.3
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    • pp.41-48
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    • 2019
  • In modern-war campaign, precision-guided missiles are dominantly used to minimize the collateral damage. Imaging infrared seekers are widely applied for the precise guidance. Due to the high cost of the infrared detector, the cost for the one-shot weapon's test is a burden for the development. To reduce the test cost, a simulation method including imagery tracking is required, which is so-called integrated-flight simulation(IFS). The synthetic image generation(SIG)-based simulation method is typically used, which however cannot represent various environmental and target conditions. In this paper, a new IFS method is proposed using on-sight measured image to overcome the limitations of the SIG-based IFS(SIIFS). The target image acquired at the launching sight has been used only for checking the performance criteria of the image tracker and has not been tried for IFS since it has low resolution and little information. The study described in this paper, however, shows that the on-sight image-based IFS can predict the pre- and mid-course flight performance quite similarly and is very useful for the flight test analysis.

A Case Study on the Unmanned Modification Process of 500MD Helicopter (500MD 헬리콥터의 무인화 개발과정 사례 연구)

  • Kim, Won-Jin;Son, Taek-Joon;Kim, Hong-Dae;Gong, Byung-Ho
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.49 no.4
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    • pp.329-334
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    • 2021
  • Korean Air has set the goal of the first stage of the development of unmanned helicopters to perform in hovering flight by remote control. In order to achieve the development goal, Korean Air carried out system integration, ground test, and safety wire test in sequence after carrying out programmed depot maintenance and aircraft modification of manned aircraft, and verified the controllability and flight safety of the unmanned helicopter system step by step. In particular, it was confirmed that the safety wire test technique used in the final stage of verification was an effective method to verify flight safety and controllability for a fully unmanned helicopter system.