• Title/Summary/Keyword: External Fuel Tank

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Vibration Mode Measurement Test of External Fuel Tank for Aircraft (항공기용 외부연료탱크 진동모드 측정시험)

  • Kim, Hyun-gi;Choi, Hyun Kyung;Kim, Sungchan;Park, Hyung Bae;An, Su Hong;Kim, Young Shin
    • Journal of Aerospace System Engineering
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    • v.16 no.4
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    • pp.88-94
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    • 2022
  • The vibration mode measurement test measures the natural vibration characteristics of the target specimen. The measured natural mode characteristics are compared with the numerical analysis result to verify the reliability of the numerical analysis. If necessary, it is used to supplement the numerical analysis model of the specimen used for the dynamic characteristic analysis. In this paper, the natural frequency and natural mode of the external fuel tank are respectively obtained through the vibration mode measurement test and the numerical analysis, using the finite element model. The results are compared to verify the reliability of the numerical analysis model of the external fuel tank to apply to the entire aircraft model. To measure the vibration mode of the test specimen, a bungee cord was used, to simulate the free boundary condition for the test specimen. And, 3-axis accelerometers were installed on the test specimen. The response characteristics of the test specimen were measured, by excitation with an impact hammer. As a result of the test, after performing the frequency response analysis on the response acceleration, the natural frequency of the test specimen and its vibration mode were confirmed. The reliability of the numerical analysis model was verified by comparing the frequency and vibration mode, obtained through the test and the numerical analysis.

Structural Static Test for Validation of Structural Integrity of Fuel Pylon under Flight Load Conditions (비행하중조건에서 연료 파일런의 구조 건전성 검증을 위한 구조 정적시험)

  • Kim, Hyun-gi;Kim, Sungchan;Choi, Hyun-kyung;Hong, Seung-ho;Kim, Sang-Hyuck
    • Journal of Aerospace System Engineering
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    • v.16 no.1
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    • pp.97-103
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    • 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.

Development of Fuel Economy Measurement Technology for Fuel Cell Electric Vehicle (수소연료전지차 연비 평가기술 개발)

  • Jung, Young-Woo;Park, Jeong-Kyu;Ye, Chang-Hwan;Park, Jong-Jin;Oh, Hyung-Seuk
    • 한국신재생에너지학회:학술대회논문집
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    • 2007.11a
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    • pp.152-155
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    • 2007
  • Fuel cell electric vehicles (FCEVs) using hydrogen gas are zero emission vehicles, thus emission measurement for combustion vehicles is not applicable. The hydrogen gas consumption for fuel economy will be measured by the stabilized pressure/temperature method, mass flow method and electrical current method, etc. In this research, weight method with a newly manufactured test equipment is applied to measure the hydrogen consumption because above 3-methods have a deviation. The hydrogen consumption is directly calculated by the weight differences of the external hydrogen tank before and after the chassis dynamometer test. Ultimately the fuel economy for FCEVs is obtained with a deviation less than 1% in all chassis dynamometer tests.

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A Study on the Sloshing Reduction of a Cargo Fuel Tank with Baffle (배플을 적용한 Cargo용 연료탱크 내부의 슬로싱 저감 연구)

  • Yoon, Bo-Hyun;Yoon, Jun-Kyu;Lim, Jong-Han
    • Journal of Advanced Marine Engineering and Technology
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    • v.34 no.8
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    • pp.1074-1083
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    • 2010
  • Recently sloshing that fluid in fuel tank is undulating by the external force during motion of automobile, ship and aircraft is greatly affecting by damaging the inside of structure. It's most important to precisely analyze the behavior of fluid by computational fluid dynamics for minimizing the effect of sloshing for the loaded fuel. This study characterized volume of fluid and pressure according to the length and number of vertical baffle and horizontal baffle in fuel tank for Kia Frontier cargo and analyzed for reduction of sloshing during driving on corner and hill by using ADINA-CFD. As a result of analysis, the optimum length for sloshing reduction shows 0.19 m for vertical baffle and 0.08 m for horizontal baffle. And it shows that vertical baffle is better for the reduction effect of sloshing during driving on corners, on the other hand, horizontal baffle is effective and stable during driving on hills.

A Study on The Possibility of Flash Fire of Combat System by Kinetic Energy Ammunitions (운동에너지탄에 의한 전투시스템의 순간화재 발생가능성에 대한 연구)

  • Park, Young Ju;Lee, Eun Min;Lee, Hae Pyeong;Hwang, Me Jung;Lee, Chang Hyun
    • Journal of the Korean Society of Safety
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    • v.29 no.2
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    • pp.89-97
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    • 2014
  • This study analyzed various possibilities of flash fire which could occur in a variety of combats, in order to predict that of flash fire of combat system armor using Autodyn program. The possibility was judged by the temperature distribution of fuels, which was caused by the impact of parts of fuel systems through an armor, in the event of getting shot by external ammunition. Diverse variables could affect the possibility of flash fire: external ammunition(Type A: penetration 570 mm, Type B: penetration 410 mm), fuels(Gasoline, Diesel, Kerosene), the thickness of an armor(100, 200, 300, 400, 500 mm), the gap of a fuel tank and an armor(45, 95, 145, 195, 245, 295 mm). As a result, when an armor was 20 mm think, the temperature of 3 fuels ranged like this: Gasoline 372~387 K, Diesel 442~408 K, Kerosene 384~395 K. Although they made a little difference among them, they all didn't reach their ignition points. When an armor was 200 mm think, each fuel reached the maximum temperature, not reaching its ignition points as well. The thicker an armor was, the lower the temperature got. When Type B ammunition was used, the temperature of fuels went up 19~59 K higher than Type A was used. In the case that the gap of fuel tank and an armor was 20 mm thick, the temperature distribution of Gasoline showed 389~450 K, the maximum temperature appeared in the gap of 145 mm, and the minimum temperature 295 mm. For Type B, the temperature distribution of fuels ranged 386~401 K, the maximum temperature appeared in the gap of 245 mm, and the minimum temperature 45 mm. There was no significant difference between two cases, and neither of them reached its ignition point. Accordingly, as the tested fuels of combat systems didn't reach their ignition points, it is thought that the possibility of flash point of an armor is low.

The Analysis of Emergency Response Guide for Hydrogen Fuel Cell Vehicle (수소연료전지 자동차의 긴급대응 가이드 분석)

  • Lee, Kwang-Ju;Lee, Jong-Tai;Yong, Gee-Joong
    • Transactions of the Korean hydrogen and new energy society
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    • v.23 no.2
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    • pp.156-161
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    • 2012
  • In case of commercializing of the hydrogen fuel cell vehicle, the suitable emergency response guide is necessary to prepare an accident. In order to suggest the suitable guide for the domestic affairs, the existing external guide about GM, Ford, Honda, and Hyundai was reviewed. The emergency response guides in CAFCP and main FC vehicle makers were included in the analysis. As the results, it was found that the design and make of vehicle for the domestic user are demanded in the emergency response and the guide is made with the shut-down manual picked out for the rescuer and repair man as well as user.

Study on Verification Methodology of Airworthiness Requirements for Bird Strike on Civilian Helicopter based on Numerical Analysis (수치해석을 통한 민수용 헬리콥터의 조류충돌 인증 요구도 검증기법에 대한 연구)

  • Kim, Dong-Hyeop;Kim, Sang-Woo;Kim, Hyun-Gi;Kim, Sungchan;Shin, Bok Kyun
    • Journal of Aerospace System Engineering
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    • v.13 no.6
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    • pp.70-79
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    • 2019
  • The increase of bird strike requires to be amended more safely current airworthiness requirements for bird strike. The USA and Europe are considering the methodology to verify the bird strike requirements based on the finite element analysis (FEA). Meanwhile, the aircraft airworthiness standards in Korea enacted by the Ministry of Land, Infrastructure and Transport were based on those enacted by the Federal Aviation Administration (FAA). This means that the verification methods using the FEA for the bird strike requirements should be reflected in the airworthiness standards in Korea. Our study proposes the methodology for bird strike simulation based on the FEA for the external auxiliary fuel tank assembly on the Surion helicopters and confirmed that the numerical outputs corresponded to the test results. The authors suggest that the methodology and procedure based on the FEA are adopted not only in the bird strike requirements but in various aircraft certifications of civilian rotorcraft.

Analysis of Crash Load in Crash Impact Test for Fuel Tank of Rotorcraft (항공기용 연료탱크 Phase I 충돌충격시험 충격하중 분석)

  • Kim, Hyun-gi;Kim, Sung Chan
    • Journal of the Korea Academia-Industrial cooperation Society
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    • v.16 no.6
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    • pp.3736-3741
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    • 2015
  • Crash impact test is conducted to verify the crashworthiness of fuel tank. Success of the crash impact test means the improvement of survivability of crews by preventing post-crash fire. But, there is a big risk of failure due to huge external load in the crash impact test. The failure of crash impact test can result in serious delay of a entire rotorcraft development because of the design complement and re-production of the test specimens requiring a long-term preparation. Thus, the numerical simulations of the crash impact test has been required at the early design stage to minimize the possibility of trial-and-error in the real test. Present study conducts on the numerical simulation of phase I crash impact test using SPH supported by crash simulation software, LS-DYNA. Test condition of MIL-DTL-27422 is reflected on analysis and material data is acquired by specimen test of fuel cell material. As a result, the crash load on the skin material, overlap area and metal fitting is estimated to confirm the possibility of acquisition of the design load for the determination of the overlap area and adhesive strength.

Structural Static Test of Pylon for External Attachment Separation Load (외부장착물 분리하중에 대한 파일런 구조 정적시험)

  • Kim, Hyun-gi;Kim, Sungchan;Hong, Seung-ho;Choi, Hyun-kyung;Cho, Sang-hwan;Park, Hyung-bae
    • Journal of Aerospace System Engineering
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    • v.16 no.1
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    • pp.104-109
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    • 2022
  • The bomb rack unit (BRU) installed inside the pylon serves to fix external attachments such as external fuel tank or external weapon, and also serves to separate external attachments in case of emergency. In particular, the load generated when the external attachment is separated from the BRU is called the punching load. In this study, we present the results of a structural static test performed to verify the structural integrity of the pylon under the BRU punching condition acting on it. In the structural static test report, we present the implementation method for the separation load of the external attachment and the test profile for the BRU punching load condition, and compared the error between the load input signal and the feed-back signal to determine the appropriateness of load control in each test. Furthermore, we compared the strain results obtained in the numerical analysis and structural test at the main positions of the specimen. As a result, it was shown that the load of the actuators were properly controlled within the allowable error range in each test, and the numerical analysis effectively predicted the test result. Finally, through structural static tests conducted by design limit load and design ultimate load, we verified that the aircraft pylon dealt with in this study has sufficient structural strength for external attachment separation condition.

Test and Evaluation of Onboard Equipments for Guided Missile via Captive Flight Test (탑재비행시험을 이용한 유도무기 탑재장비의 시험평가)

  • Lee, Sung-Mhan;Oh, Hyun-Shik;Sung, Duck-Yong;Lee, Su-Chang
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.35 no.1
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    • pp.73-78
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    • 2007
  • The process and results of Captive Flight Test(CFT), conducted by Agency for Defense Development(ADD) using the Korean KTX-1 trainer and external fuel tank, are presented. Through over 150 sorties of CFT, the guided weapon system's critical subsystems like Seeker, Navigation Device and Technology, Inertial Sensor, and Radio Altimeter are tested and evaluated. Using the CFT, time and cost are saved in weapon system research and development procedure.