• Korean Journal of Construction Engineering and Management
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• v.24 no.3
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• pp.31-41
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• 2023

This study is a study to develop a configuration management methodology for efficient and systematic management in the event of configuration changes such as deformation, explosion, and remodeling of launch vehicle development test facilities, which are emerging as important national facilities in the era of full-scale space competition. Through the analysis of international standards for configuration management, a configuration management process framework to be applied to launch vehicle development test facilities is extracted, a survey was conducted on experts who performed life cycle engineering of launch vehicle development test facilities, and a configuration management methodology optimized for operation/management of domestic launch vehicle development test facilities was proposed. Identify the configuration for launch vehicle development test facilities, the configuration management manager, configuration management organization, and configuration management board approve/process the configuration changes, and after construction is completed according to design requirements, launch vehicle development test facilities try to manage the configuration in a controlled state.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.25 no.2
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• pp.63-68
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• 2017

In the present study, a wind tunnel test for a rotor-blade configuration was conducted to investigate a basic aerodynamic performance and a effect of the cross wind. The diameter of the configuration was 1.46 m and the test was carried out for both a clean and a tripped configurations. The boundary layer for the trip configuration was simulated by zig-zag tape and the test performed on constant-velocity and constant-rotational modes. It was shown that the test result for the tripped configuration reduces the maximum power coefficient by 9.4% ~ 12.1% compared to the clean one. Within $5^{\circ}$ of the flow angle, there is no significant loss of power, however, the coefficient is reduced by 5.3% ~ 36.7% in the range of $10^{\circ}{\sim}30^{\circ}$.

• Aerospace Engineering and Technology
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• v.10 no.2
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• pp.128-132
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• 2011

We can acquire the criteria of configuration tolerance on the Kick Motor system, KSLV-I upper stage propulsion system from the analysis results of the initial controllability on the KSLV-I upper stage. Also we can assign configuration tolerances on each subsystem from the configuration tolerance on the Kick Motor system. This article deals with the Kick Motor system configuration tolerance criteria and the results of configuration management on the both ground test models and flight test ones.

• Journal of Aerospace System Engineering
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• v.9 no.2
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• pp.19-24
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• 2015

Export basic trainer was designed to add armed configuration required by customer. Design configuration of main wing was changed to satisfy changed internal load caused by armed configuration. It was verified that design changed main wing airframe of export basic trainer satisfy the requirement through the structural detail analysis, structural ground test and flight test. This paper presents the durability test procensure and test result for the main wing of export basic trainer.

• Proceedings of the KIEE Conference
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• 1997.07c
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• pp.829-831
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• 1997

We investigated configuration plan and future expectation of the power distribution test center. The example of foreign country's test center was analyzed, and the required test facilities, test line, and power source for the operation of our test center were proposed.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.30 no.10 s.253
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• pp.1012-1018
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• 2006

To evaluate the aerodynamic efficiency of TR-S4 configuration, wind tunnel tests of 40% scaled model were done in KARI LSWT. TR-S4 configuration has different nacelle shape, larger EO/IR camera and aftward wing location compared with TR-S2. Component build-up test after adding each element of model is performed. Also effects of horizontal tail incidences, Flaperon and Aileron deflection. on aerodynamic characteristics are measured. Test results showed that TR-S4 configuration has favorable stability characteristics in longitudinal, lateral and directional for the pitch and yaw motions.

• International Journal of Aeronautical and Space Sciences
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• v.14 no.1
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• pp.99-104
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• 2013

Configuration design, analysis, and wind tunnel test of a vane-type multi-function air data probe (MFP) was described. First, numerical analysis was conducted for the initial configuration of the MFP in order to investigate aerodynamic characteristics. Then, the design was modified to improve static and dynamic stability for better response characteristics. The modified configuration design was verified through wind tunnel tests. The test results are also used to verify the accuracy of the analytical method. The analytically estimated aerodynamic damping provided by the Navier-Stokes equation solver correlated well with the wind tunnel test results. According to the calculation, the damping coefficient estimated from ramp motion analysis yielded a better correlation with the wind tunnel test than pitch oscillation analysis.

• Journal of the Korea Concrete Institute
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• v.12 no.1
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• pp.53-60
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• 2000

The objective of this study is to investigate the flexural behavior of reinforced concrete columns confined by lateral ties. This test was carried on the twelve reinforced concrete columns subjected to lateral and constant axial loads. The main experimental variables are concrete strength, the configuration of lateral ties, and the amount of lateral ties. Test results indicated that the steel configuration in column sections plays an important role in column behavior, and a proper configuration of lateral ties can obtain more ductile by the reduction of the space of lateral ties. Also, this experiment show that the utlization of high-strength concrete in columns properly designed on ACI Code takes less ductile. Therefore, we can conclude that the design of high-strength concrete columns under high axial loads requires more lateral ties than ACI Code.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.9
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• pp.9-15
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• 2005

This paper describes the test carried out on an experimental study of fuselage drag and stability characteristics of a helicopter configuration and the test techniques developed for the testing and the lessons learned in the Agency for Defense Development Low Speed Wind Tunnel(ADD-LSWT). The main objective of this test is to determine the drag and stability characteristics of helicopter configurations according to the various configuration changes. The fuselage model with a highly modular structure is a representation of 1:8 scale of the external contour of the conceptual design helicopter configuration with rotating main rotor hub including blade stubs capable of rotating up to 500 rpm. The test results are compared with the available similar data and fair to good agreement is obtained.

• KIPS Transactions on Software and Data Engineering
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• v.3 no.7
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• pp.243-254
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• 2014

When building a testing environment with a testing platform, the configuration of test executor and its interface should be built to be appropriate for the system under test (SUT). That is, it is necessary to build the test executor and interface environment that can properly handle the input and output signals of SUT. If the testing platform is not extendable, it should be modified significantly whenever new SUTs and models are tested. It is a serious drawback that the test executor and interface configuration need to be modified depending on testing targets. To overcome the drawback, this paper proposes TEM(test Execution Machine), which allows for test executor to reconfigure its environment suitable to new SUTs by modifying the configuration file. The proposed TEM is verified through testing two real systems.