• Title/Summary/Keyword: Aircraft equipment

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Study on Practical Use of Air Vehicle Test Equipment(AVTE) for UAV Operation Support (무인항공기 운용 지원을 위한 비행체 점검장비 활용에 관한 연구)

  • Song, Yong-Ha;Go, Eun-kyoung;Kwon, Sang-Eun
    • Journal of the Korea Institute of Information and Communication Engineering
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    • v.25 no.2
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    • pp.320-326
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    • 2021
  • AVTE(Air Vehicle Test Equipment) is an equipment to inspect and check the status of on-board aircraft LRUs(Line Replacement Units) before and after flight for performing successful UAV(Unmanned Aerial Vehicle) missions. This paper suggests utilization of the AVTE as an operation support-equipment by implementing several critical functions for UAV-operation on the AVTE. The AVTE easily sets initialization(default) data and compensates for the installation and position errors of the LRUs which provide critical mission data and situation image with pilots without additional individual operation support-equipment. Major fault list and situation image data could be downloaded after flight using the AVTE in the event of UAV emergency situation or unusual occurrence on duty as well. We anticipate the suggested operational approach of the AVTE could dramatically reduce the cost and man power for design and manufacture of additional operation support equipment and effectively diminish workload of the operator.

A Software Update Technique for Aircraft Missiles based on MIL-STD-1760 (MIL-STD-1760 기반 항공기용 유도탄 소프트웨어 업데이트 기법)

  • Lee, Seungyoun;Kim, Sungkwon;Lee, Hyunah;Cho, Dongsik
    • Journal of the Korea Institute of Military Science and Technology
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    • v.21 no.5
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    • pp.649-657
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    • 2018
  • It is essential that weapons which are mounted on aircraft need to prove its reliability and safety during its developments. A guided missile should have high reliability and safety throughout various tests which are including ground tests, captive flight tests, detailed technical tests and operational tests. In these various tests, it is vital that software of each component in the guided missile should be easily updated in order to correct algorithms or errors. In this paper, we propose a software update technique based on MDTP(mass data transfer protocol) which are defined in MIL-STD-1760. The proposed techniques have the following advantages: First, software of each unit in a weapon can be updated through a test equipment without disassemble a guided missile. Second, development periods for a software update can be reduced by reusing MDTP. Third, we can easily maintenance of the software because it is based on standard. We proved its efficiency and validity through experiments. Therefore, the proposed technique should be effectively utilized for software update of a weapon mounted on an aircraft during development processes.

Investigation on Strength Recovery after Repairing Impact Damaged Aircraft Composite Laminate (항공기 복합재 라미네이트의 충격 손상 부위 유지 보수 후 강도 복원 평가)

  • Kong, Chang-Duk;Park, Hyun-Bum;Lee, Kyung-Sun;Shin, Sang-Jun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.38 no.9
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    • pp.862-868
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    • 2010
  • Development of a small scale aircraft has been carried out for the BASA(Bilateral Aviation Safety Agreement) program in Korea. This aircraft adopted all the composite structures for environmental friendly by low fuel consumption due to its lightness behavior. However the composite structure has s disadvantage which is very weak against impact due to foreign object damages. Therefore the aim of this study is focusing on the damage evaluation and repair techniques of the aircraft composite structure. The damages of composite laminates including the carbon/epoxy UD laminate and the carbon/epoxy fabric face sheets-honeycomb core sandwich laminate were simulated by a drop weight type impact test equipment and the damaged specimen were repaired using the external patch repair method after removing damaged area. The compressive strength test and analysis results after repairing the impact damaged specimens were compared with the compressive strength test and analysis results of undamaged specimens and impact damaged specimens. Finally, the strength recovery capability by repairing were investigated.

Technology Trends and Performance Evaluation for Unmanned Aircraft System Datalink (무인 항공 시스템 데이터링크 기술 동향 및 성능 분석)

  • Hwang, Hyunsu;Jung, Yongcheol;Jung, Yunho
    • Journal of Advanced Navigation Technology
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    • v.20 no.4
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    • pp.329-335
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    • 2016
  • Unmanned aircraft systems (UAS) are defined as the system whose components include the necessary equipment, network, and personnel to control an unmanned aircraft. In the past, UAS were predominately operated for military operations. However, nowadays, the applications of UAS to commercial area are explosively augmented and UAS are being expected to be integrated in national airspace. Therefore, the need for the standardized datalink systems rapidly and the development of control and non-payload communication (CNPC) system are being processed for integration in national airspace in United States and Europe. In this paper, the technology trends for UAS CNPC datalink are explained and presented the performance evaluation results for CNPC system, which is the modified version of IEEE 802.15.4 ZigBee system.

Accelerated Life Analysis and Endurance Verification of Electro-Mechanical Actuator (항공기용 전기식 날개 구동장치의 가속 수명 분석 및 시험을 통한 내구성 검증)

  • Huh, Seok Haeng;Lee, Byung Ho;Seol, Jin Woon;Baek, Joo Hyun;Yang, Myung Seok;Kwon, Jun Young
    • Journal of the Korean Society for Precision Engineering
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    • v.33 no.10
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    • pp.829-835
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    • 2016
  • Electro-Mechanical Actuator installed on the aircraft plays a key role in an aircraft's flight control through flight control computer. Reliable prediction of the actuator is important for the aircraft. To estimate the lifetime of a product, it is necessary to test full target life. However, it is very difficult to perform it due to the long life time of actuator but short period of development time with increasing cost. Therefore, accelerated life test has been used to reduce the test time for various reasons such as reducing product's development cycle and cost. In this paper, to predict the lifetime of the actuator, we analyzed the flight profile of aircraft and adapted the method of accelerated life test in order to accelerate failure modes that might occur under user conditions. We also set up an endurance test equipment for validating the demanded lifetime of an actuator and performed accelerated life test.

Fatigue Life Evaluation in Frequency Domain of aircraft Equipment Exposed to Random Vibration (무작위 진동에 노출된 항공기 탑재 장비의 주파수영역 피로수명 평가)

  • Jung, Hyun Su;Kim, Ki Seung;Kim, Jun Su;Lee, Seong Woo
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.45 no.8
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    • pp.627-638
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    • 2017
  • Expecting fatigue life of mounted radar in aircraft is very important when designing, because the mounted radar in aircraft is exposed to long-term external random vibration. Among the methods of predicting the fatigue life, Fatigue analysis method in frequency domain has continuously been proposed in this field. In this paper, four fatigue analysis methods in frequency domain, which are widely used, have been selected and compared with the results for Specimen fatigue test. As a result, Dirlik and Benascicutti-Tovo methods have been matched better with fatigue analysis in time domain than the method in frequency method through the comparison between the fatigue analysis method in time domain and the method in frequency domain by conducting the specimen fatigue test with strain gage. Based on the results of the specimen fatigue test, We have conducted fatigue analysis of mounted radar in aircraft with Dirlik and Benasciutti-Tovo methods in the finite element model, and confirmed that the required life was satisfying.

GBAS Flight Testing and Performance Assessment using Flight Inspection Aircraft at Gimpo International Airport (비행검사용 항공기를 이용한 김포국제공항 GBAS 비행시험 및 성능평가)

  • Jeong, Myeong-Sook;Bae, Joongwon;Jun, Hyang-Sig;Lee, Young Jae
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.43 no.1
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    • pp.49-61
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    • 2015
  • Ground Based Augmentation System(GBAS) is a system that offers an aircraft within 23 NM radius from the airport precision positioning service and precision approach service using the concept of Differential Global Positioning System(DGPS). After GBAS ground equipment installing at the airport, functionalities and performances of GBAS should be verified through the GBAS ground and flight testing. This paper describes the methods and results for GBAS flight test using the flight inspection aircraft at Gimpo International Airport. From the test results, we confirmed that the VDB data was received without misleading within the VDB coverage of Gimpo International Airport, and VDB field strength, protection level, and course alignment accuracy met the evaluation's criteria.

Heat Dissipation Design for KW Class Power Control Unit Mounted on Aircraft Store (항공기 장착물에 탑재되는 KW급 전력변환장치의 방열설계)

  • Choi, Seok-min;Kim, Hyung-jae;Jung, Jae-won;Lee, Chul
    • Journal of Advanced Navigation Technology
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    • v.24 no.4
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    • pp.261-266
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    • 2020
  • When a KW-class power control unit is installed in an aircraft installation, a heat dissipation design for a large amount of heat generated during power conversion should be considered. Failure to provide adequate heat dissipation can lead to equipment malfunction and fire, which can be a fatal factor in aviation operations. This paper describes the heat dissipation design of a KW-class power control unit installed in aircraft installation. The design and manufacturing test were conducted through computerized analysis, and the analysis model was corrected by confirming the rapid heat generation phenomenon of the heating element due to high power control. After the model revision, the design was improved, and the high-temperature operation test of the US military standard MIL-STD-810G was performed to confirm the feasibility of the improved design.

The Applicability of Avionics Simulation Model Framework by Analyzing the Performance (항공용 시뮬레이션 모델 프레임워크 성능 분석을 통한 적용성 평가)

  • Seo, Min-gi;Cho, Yeon-je;Shin, Ju-chul;Baek, Gyong-hoon;Kim, Seong-woo
    • 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.

Development of Feedback Data Automated Verification Program for Mission S/W (임무 S/W 시험을 위한 피드백 데이터의 기댓값 검증 자동화 도구 개발)

  • Kwon, GI-Bong;Lee, Ha-Yoeun;Ha, Seok-Wun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.49 no.10
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    • pp.871-877
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    • 2021
  • Aircraft defects are important matters directly related to the operation of the aircraft and the life of the pilot. The defects in the mission software that occur during aircraft control seriously affect the pilot's mission performance and safety. Therefore, the organization in charge of aircraft development or software defects are reinforced in the process to identify and eliminate defects in the early stages of development, and a lot of labor and time are spent, but due to the nature of the mission software, strong functional coupling with other avionics and high complexity, so there are restrictions on the identification and removal of software defects through the existing test method. This study analyzes the effect of securing mission software integrity and reducing test cost through data integrity verification by developing a tool that automates the verification of expected value of feedback data among communication data of mission computer interlocking equipment.