• Convergence Security Journal
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• v.21 no.4
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• pp.31-39
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• 2021

In the R&D of the Defense Weapon System, the evaluation of technical and operational aspects has been developed with the military's own test evaluation system, and organizations and procedures have been established and implemented. However, with the recent advancement of information and communication technology in the private sector, it is often necessary to test-apply it to the field by enhancing the operability and suitability of technologies required for defense before development is complete. This paper investigates and analyzes the process for conducing empirical tests on the latest AI vaccine system R&D prototype organized by the Ministry of Science and ICT which proposes an improved demonstration plan for the existing military information system test evaluation procedure. In addition, under the specificity and security of the defense environment, we would like to present a practical demonstration plan and the improvement of the process for demonstrating the security technology prototype.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.5
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• pp.98-103
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• 2015

A flow passage opening device utilizing an acceleration follow-up technique allows fuel to flow continuously through a pressurized fuel tank system. It is very difficult to test the device in a real flight situation because of severe test condition and a cost problem. In this paper, therefore, the results of a basic negative g test conducted by low-speed airplane are compared with RecurDyn simulation. Dynamic behavior of the device in total flight profile of a high-speed vehicle is also analyzed by using RecurDyn to predict its performance.

• International Journal of Aeronautical and Space Sciences
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• v.16 no.4
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• pp.529-536
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• 2015

Various R&D programs for rocket-based combined cycle (RBCC) engines have progressed worldwide for the space development and the defense applications. As a way toward indigenous domestic RBCC program, a preliminary design of flight test conditions was studied in this study for a sub-scale RBCC engine using a sounding rocket. Launch and flight profiles were calculated for several booster options and compared with that of HyShot II program. The result shows that the Korea Sounding Rocket-II (KSR-II) is a proper candidate to perform the flight test available in Korea. The recommend flight test conditions with KSR-II are Mach 6.0 with a test vehicle of 230 kg and Mach 7.4 with 50 kg. Present study will soon be followed by a design of sub-scale RBCC for a flight test using a sounding rocket.

• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.3
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• pp.18-24
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• 2017

Appropriate selection of the starter is essential for successful starting of the gas-turbine engine. Thus, aerodynamic drag during starting phase should be analyzed to assess the feasibility of the starter. In this paper, aerodynamic drag is modeled based on the speed profile from the engine coast down test, and it is scaled with respect to the target engine by comparing the compressor load. Afterward, the govern equation of the starting phase is developed with the torque model of the starter, and the design scheme to select the feasible starter will be finally suggested. The proposed model of starting phase will be useful to perform a preliminary design of the starting system of the gas-turbine engine.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.3
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• pp.51-57
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• 2019

Post curing effects are estimated by specimen tests. Propellant specimen accelerated aging tests are performed when post curing is estimated to be complete and the coefficients of Arrhenius aging equations are acquired. Simulated motors with cylindrical grain are designed and fabricated to confirm the application. Accelerated aging tests are conducted, and aged properties are measured and estimated for the inner bore, center and bond parts of the grain. The measured aging ratios of the modulus are compared with the ones predicted by the equations. As the results, the accelerated aging equations predict well the propellant aging trends; however, some differences are observed at the bond part. Therefore, the specimen extraction part must be carefully chosen to suit the test purpose when a rocket motor grain is used for the aging test.

• Journal of Aerospace System Engineering
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• v.10 no.1
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• pp.51-58
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• 2016

In this paper, we present some results on No-failure accelerated life test of aerial vehicle for reliability demonstration. The design of general accelerated life test consists of the three phases: 1) Estimating normal life test time of a single product from Weibull distribution model; 2) Determining the acceleration factor (AF) by utilizing the relation between the life of mechanical components and the applied torque; 3) Calculating the accelerated life test time, which comes from dividing the estimated normal life test time into AF. Then, we applied the calculated life test time to the real reliability test of the flap actuating system, while considering the requirement specification for mechanical components and operating environment of the actuation system. Real experimental processes and results are presented to validate the theory.

• Journal of Aerospace System Engineering
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• v.14 no.6
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• pp.85-90
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• 2020

The infrared signature that is associated with an aircraft is mainly caused by heat released from the engine and the exhaust plume. In this study, a test-system was designed to observe the overall infrared signature characteristics of a turbofan engine during operation under ground running conditions and the infrared reduction features that result from different exhaust nozzle configurations. A test stand was designed for the 1400 lbf class turbofan engine that included a bell-mouth type intake, fuel supply system, a measurement system, and a data acquisition/control system. The design and verification of the test system were conducted so that the basic nozzle and various 2D nozzles could be applied to study the infrared signature produced by a turbofan engine exhaust.

• Journal of the Korea Institute of Military Science and Technology
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• v.20 no.3
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• pp.352-361
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• 2017

This paper proposes a design and fabrication of the test equipment that is implemented as a part of the airborne tracking radar inspection under the environment of indoor simulation. This test equipment provides controlling the operation status of airborne tracking radar and replicating the velocity and range information of target by generating a variety of target signal. This is mainly composed of radar operation controller, target signal generator, horn antenna driving devices. Radar operation controller is able to perform the controlling of radar operation mode and monitoring in real time by serial communication. Target signal generator is generated doppler signal and range delayed signal using virtual target of RF-band. Horn antenna driving devices perform a role of target simulating exercise. In the end, the performance is demonstrated using experiment results of test equipment for airborne tracking radar.

• Proceedings of the KIEE Conference
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• 2002.07d
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• pp.2082-2085
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• 2002

This paper describes the development of a gas turbine engine simulator in detail. The simulator presented in this paper has a mathematical engine model based on a target gas turbine engine performance data and is developed for generating a gas turbine engine sensor signals between the hardwares and softwares of a gas turbine engine control system using Data Acquisition systems(DAS) and 1553B communication, a aeronautic standard communication specification. In addition, this paper proves the excellent performance of this simulator by showing the results of a gas turbine engine field test and simulation.

• Journal of the Korean Society of Propulsion Engineers
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• v.20 no.2
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• pp.75-85
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• 2016

A pyrotechnic system consisting of donor/acceptor pair separated by a gap relies on shock attenuation characteristics of the gap material and shock sensitivity of the donor and acceptor charges. Despite of its common use, numerical study of such pyrotechnic train configuration is seldom reported because proper modeling of the full process requires precise capturing of the shock wave attenuation in the gap prior to triggering a full detonation of high explosive and accurate description of the high strain rate dynamics of the explosively loaded inert confinements. We apply a Eulerian level-set based multimaterial hydrocode with reactive flow models for pentolite donor and heavily aluminized RDX as acceptor charge. The complex shock interaction, critical gap thickness, acoustic impedance, and go/no-go characteristics of the gap test are quantitatively investigated.