• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.827-829
• /
• 2011

Vacuum facility is required for high altitude space environment test to develop satellites or space launch vehicles. We, at Chungnam, National University, developed turbo molecular pump vacuum test facility up to $1.0{\times}10-6$ torr to simulate 200 km altitude environment. In this paper, we present some preliminary vacuum performance test results.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2007.04a
• /
• pp.49-52
• /
• 2007

Vacuum facility is required for high altitude space environment test to develop small thruster. We, at Chungnam National University, developed vacuum test facility up to $10^{-5}$ torr to simulate $100{\sim}120km$ altitude environment. Prior to operation, we predict vacuum pump performances and present preliminary calculation and experiments.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2007.11a
• /
• pp.45-48
• /
• 2007

Vacuum facility is required for high altitude space environment test to develop small thruster. We, at Chungnam National University, developed vacuum test facility up to $10^{-5}$ torr to simulate 100${\sim}$120 km altitude environment. In this paper, we present some preliminary performance test results.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.336-339
• /
• 2011

Hot-fire test facility is one of the most important infrastructure for thruster development and evaluation. During the past three years, Korea Aerospace Research Institute (KARI) and Hanwha Corporation have successfully performed the construction of hot-fire test facility for medium-scale monopellant thruster to the maximum 200N thrust level. In general, thruster hot-firing test should be performed in vacuum conditions to simulate space environment. The hot-fire test facility is divided into three subsystems, vacuum system, propellant supply system and data measurement & control system. The goal of this facility is to extend the capability from small thruster for satellite mission to medium-scale thruster for launch vehicle and lunar mission. In this paper, the progress and overview for thruster hot-fire test facility was introduced and test results were also presented.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.1160-1164
• /
• 2017

In this research, a high altitude simulating test facility is designed using vacuum pump system composed of roots pumps and screw pumps. Air flow rate and chamber pressure are 1 kg/s and 2500 Pa, respectively. To design the test facility, experimental tests using certain pump combinations are performed for air injection of the order of hundreds of g/s. From the tests, it is found that 11 roots pumps and 33 screw pumps are required for the considered test facility. Test results are compared with theoretically estimated values. However, intake capacity theoretically estimated is found to be 20 percent larger than test results. This is thought because of higher pressure difference of roots pump for test conditions. Therefore, if more screw pumps are added for the considered pump system, it would be possible to lower the vacuum level of test chamber.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.112-115
• /
• 2017

We analyzed the rocket engine flow to check whether the possibility of the ground test and the equipment safety problems in the high altitude engine test facility. The test condition is that the vacuum chamber is open and the coolant water is injected into the supersonic diffuser. The analysis uses two-dimensional axisymmetry with a mixture of plume, air, and cooling water. As a result, the ground test was possible up to the cooling water flow rate of 200 kg/sec. However, due to the back flow of the initial plume, the vacuum chamber is exposed to high temperature, and at the same time, the inside of the vacuum chamber is contaminated due to the reverse flow of the cooling water. Therefore, sufficient insulation measures and work for pollution avoidance should be preceded.

• Proceedings of the KSME Conference
• /
• 2001.06e
• /
• pp.619-624
• /
• 2001

A performance test facility for turbopump inducer cavitation was developed and the inducer cavitation performance tests were performed. Major components of the performance test facility are driving unit, test section, piping, water tank, and data acquisition and control system. The maximum of testing capability of this facility are as follows: flow rate - 30kg/s; pressure - 13 bar; rotational speed 10,000rpm. This cavitation test facility is characterized by the booster pump installed at the outlet of the pump that extends the flow rate range, and by the pressure control system that makes the line pressure down to vapor pressure. The vacuum pump is used for removing the dissolved air in the water as well as the line pressure. Performance tests were carried out and preliminary data of test model inducer were obtained. The cavitation performance test and cavitation bubble flow visualization were also made. This facility is originally designed for turbopump inducer performance test and cavitation test. However it can be applied to the pump impeller performance test in the future with little modification.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2008.11a
• /
• pp.383-387
• /
• 2008

To design a high altitude test facility for testing liquid rocket engine optimal technical solutions with general understanding about characteristics of engines and test stands, mission of a rocket and the financial aspects of tests are required. In this paper conditions and requirements needed at the stage of conceptual design of high altitude engine test facility were suggested, and preliminary calculations of the sizes of a supersonic diffuser and volume of cooling water were carried out.

• Proceedings of the Korean Vacuum Society Conference
• /
• 2004.08a
• /
• pp.216-216
• /
• 2004

• Proceedings of the KIEE Conference
• /
• 2000.07c
• /
• pp.2113-2115
• /
• 2000

It is necessary to install the arc generation facility in order to obtain the important technology for the design of breakers and switches, and for the improvement of their performance and reliability. With this facility, it is possible, to study the characteristics of Arc in air/gas/vacuum insulation environment. The facility briefly consists of capacitor bank which can charge enormous energy, an air-core reactor, experimental arc-chamber, and several measurement equipments. This facility can simulates the arc phenomena in breakers and switches by means of generating high currents. In order to study the arc phenomena in SF6 gas and vacuum and to test the quenching performance of the extinguishing chambers which are developing. we made experimental $SF_6$gas/vacuum chambers and measured several parameter's of chambers. And besides we visualized arc ignition and arc movement by means of high speed camera.