• Title/Summary/Keyword: 전기체 구조시험

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A Study on Calculation of Test Load for Full-Scale Airframe Structural Test of Composite Aircraft (복합재 항공기 전기체 구조시험 시험하중 산출 방법 연구)

  • Choi, Ik-Hyeon;Ahn, Seok-Min
    • Aerospace Engineering and Technology
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    • v.10 no.2
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    • pp.146-153
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    • 2011
  • Some methods of calculation of test load value from design load data were investigated which will be applied at strap installed full-scale airframe of composite aircraft. These methods were applied to left wing of KC-100 composite aircraft and the calculated test load values were compared with each others. Generally since test load values are differently calculated according to each aircraft type and position of straps, all calculation methods mentioned at this study need to be applied and compared to each aircraft. Finally the most appropriate method needs to be selected.

전기체 구조시험을 위한 고성능 과하중 방지 모듈 개발

  • Chae, Dong-Chul;Kim, Sung-Chan;Hwang, Gui-Chul;Sung, Kyung-Jin;Shim, Jae-Yeul;Hwang, In-Hee
    • Aerospace Engineering and Technology
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    • v.3 no.2
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    • pp.208-216
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    • 2004
  • Advanced overload protection module for full scale airframe structural test was developed by improving the existing overload protection module. When performing the full scale airframe structural test, overload can be applied to the test article due to unexpected situations such as system shutdown, test article failure, and deficiency of design strength. Therefore, the overload protection module is needed for protecting the test article in unexpected overload situations. In this paper, the function of the existing overload protection module was summarized for each component and the problems encountered when using it in structural test were analyzed in addition, the development of advanced overload protection module was described.

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과하중 방지기의 전기체 구조시험 적용에 관한 연구

  • Kim, Sung-Chan;Chae, Dong-Chul;Kim, Sung-Jun;Hwang, In-Hee
    • Aerospace Engineering and Technology
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    • v.2 no.2
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    • pp.11-17
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    • 2003
  • This paper present a method of meter-out flow control for overload protection valve in full-scale airframe test. Emergency stop, which results in dump state, can be happened during full-scale airframe test by several causes. Because servo valve can't control hydraulics actuator in the dump state, pressure in cylinder chamber may rise abruptly and overload can be acted to the test article. In this paper, the procedure and technology of orifice setting are investigated to protect the test article from unexpected loads by dump. The test results show that the presented methods decrease peak loads and improve unloading characteristics of hydraulic actuators in the dump state.

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전기체 구조시험 설비 감시 시스템

  • Chae, Dong-Chul;Hwang, Gui-Chul;Song, Jae-Chang;Shim, Jae-Yeul
    • Aerospace Engineering and Technology
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    • v.2 no.1
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    • pp.29-34
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    • 2003
  • Full-scale test facility is a huge system which is integrated by many subsystems. There are several critical elements in test facility system. Those elements may cause undesirably test article failure during testing. Therefore, test facility monitoring system which indicates the operating status of the critical elements is required for performing full-scale structural test. Selection of critical element and design of this monitoring system are explained in detail in this paper. The monitoring system developed are being applied to T-50 full-scale static test, will be expended for full-scale fatigue test in the near future.

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Setup Procedure of Dump Valve for Full-Scale Airframe Test (전기체 구조시험의 덤프밸브 조절절차 개발;)

  • Kim, Sung-Chan;Kim, Sung-Jun;Hwang, In-Hee
    • Proceedings of the KSME Conference
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    • pp.1252-1257
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    • 2003
  • This paper present a procedure of meter-out flow control method for dump valve in full-scale airframe test. Emergency stop, which results in dump state, can be happened during full-scale airframe test by several causes. Because servo valve can't control hydraulics actuator in the dump state, pressure in cylinder chamber may rise abruptly and overload can be acted to the test article. In this paper, the procedure and technology of orifice setting are investigated to protect the test article from unexpected loads by dump. The test results show that the presented methods decrease peak loads and improve unloading characteristics of hydraulic actuators in the dump state.

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KC-100 Full-scale Airframe Static Test (KC-100 전기체 정적 구조시험)

  • Shim, Jae-Yeul;Jung, Keunwan;Lee, Hanyong;Lee, Sang Keun;Hwang, Gui-Chul;Ahn, Seokmin
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.42 no.1
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    • pp.67-75
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    • 2014
  • A full-scale static test for a composite structure small aircraft (KC-100) was conducted in the KARI. The test includes 15 full-scale test and 7 local test conditions. Test requirements with test schedule, test article with dummy structures, test load generation, test system, and equipment are introduced for the test. Test load data of the 1st test condition(U1) was analyzed to evaluate an accuracy of load control for the test. The analysis results show that load data obtained during test were within tolerance of Static Null Pacing Error(SNPE) and the error value of load control was 8.6N. The error of load controls for the full-scale static test using dozens of actuators was calculated by a method suggested by authors. Test data for all other test conditions is also shown in this paper. Finally, reactions measured from restraint system of the U1 test condition show that the reaction changes as load increment. The factors which may change the change of reactions for a full-scale static test are introduced in this study.

Analysis on Reactions of Full-Scale Airframe Static Structural Test (항공기 전기체 정적구조시험의 반력 분석)

  • Shim, Jae-yeul
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.48 no.3
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    • pp.195-205
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    • 2020
  • This study addresses analysis on reactions which are induced in restraint system for airframe full-scale static structural test. This system restraints 6 degrees of freedom of a test article. It is valuable to study evaluating test error through analysis on the reactions which include all errors in a test. It is required to calculate fistly right reactions for the evaluation. This study focuses on calculation of the right reactions. The reaction is represented by sum of nominal reaction(Rn) and testing error reactions(Rce, Rerr) and is analyzed by two steps (inital vs relative reaction) in this study. It would evaluate intrinsic error at 0%DLL and error induced from applying test load, separately. Based on analysis using test data of a full-scale static test(canard type aircraft), resultant force of Rces and Rce_rs are distributed within 82.8N while resultant force of Rerr_rs shows to increase upto max. 808N as load level increment. Such well distribution of the Rce within the small range is caused from TMF values characteristics which are well distributed within -30N~40N. Additionally, it is shown through qualitative analysis on three components(X0, Y0, Z0) of the relative reaction(Rerr_r) that the reactions must be calculated with considering deformation of test article to calculate correctly reactions. This study shows also that equations characterizing deformation of components of test article are required to calculate the correct reactions, the equations must include information which will be used to calculate movement of all loading points.

비행체 구조시험 장비의 교정 확인 방법 개발

  • Chae, Dong-Chul;Kim, Sung-Chan;Hwang, Gui-Chul;Shim, Jae-Yeul
    • Aerospace Engineering and Technology
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    • v.4 no.2
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    • pp.21-26
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    • 2005
  • In airframe structural tests, a control system which has many control channels and a data acquisition system which has many data acquisition channels are used. The more it is used many channels in airframe structural test, the more hardware resources are added in test system. Before test load is applied in test article, test engineer must check test system and components. Therefore, many problems which be likely to happen to system can be minimized. The checking method of test system and components is calibration verification. In this paper, it is described that calibration verification concept and method in relation to airframe structural test controller components.(MTS Aero90 Multifunction Input Output Processor and 497.22 Dual DC Conditioner)

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A Study on the Test Load Simulation Technique for T-50 Full Scale Durability Test (T-50 전기체 내구성시험 시험하중 설계기술 연구)

  • Jung, Jae-Kwon;Lee, Kee-Bhum;Yang, Myung-Seog;Shul, Chang-Won
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.32 no.3
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    • pp.82-87
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    • 2004
  • The general requirements to achieve the structural integrity of the airframe are described in the military specification, MIL-HDBK-1530. One of these requirements is the durability and damage tolerance of the airframe, which should be shown through the analysis and test based on the related specifications. This paper describes the full scale durability test load simulation to evaluate the structural safety and durability of the advanced trainer, T-50. The test load simulation was performed according to the procedure in the military specification and the KAF contract requirements. The durability test design technique which involve the floating test set-up, the optimal test load simulation method, and the 6-DOF test article balance method to secure the real flight conditions as many as possible. It was confirmed that this method will be available in a similar full-scale airframe structural test in future.