• Proceedings of the Korean Society for Technology of Plasticity Conference
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• 1999.03b
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• pp.66-69
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• 1999

This study aims at the improvement on the process and die set required for forming of flanged two-piece thrust engine bearings form laminated sheet blanks. Several suggestions are made to reduce the number of forming or subsequent machining processes or to improve the dimensional precision of formed products. The results of finite element analysis show the design suggested in this study are useful and applicable to the forming process of flanged bearings.

• Journal of Astronomy and Space Sciences
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• v.28 no.3
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• pp.203-216
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• 2011

To prepare for a future Korean lunar orbiter mission, semi-optimal lunar capture orbits using finite thrust are designed and analyzed. Finite burn delta-V losses during lunar capture sequence are also analyzed by comparing those with values derived with impulsive thrusts in previous research. To design a hypothetical lunar capture sequence, two different intermediate capture orbits having orbital periods of about 12 hours and 3.5 hours are assumed, and final mission operation orbit around the Moon is assumed to be 100 km altitude with 90 degree of inclination. For the performance of the on-board thruster, three different performances (150 N with $I_{sp}$ of 200 seconds, 300 N with $I_{sp}$ of 250 seconds, 450 N with $I_{sp}$ of 300 seconds) are assumed, to provide a broad range of estimates of delta-V losses. As expected, it is found that the finite burn-arc sweeps almost symmetric orbital portions with respect to the perilune vector to minimize the delta-Vs required to achieve the final orbit. In addition, a difference of up to about 2% delta-V can occur during the lunar capture sequences with the use of assumed engine configurations, compared to scenarios with impulsive thrust. However, these delta-V losses will differ for every assumed lunar explorer's on-board thrust capability. Therefore, at the early stage of mission planning, careful consideration must be made while estimating mission budgets, particularly if the preliminary mission studies were assumed using impulsive thrust. The results provided in this paper are expected to lead to further progress in the design field of Korea's lunar orbiter mission, particularly the lunar capture sequences using finite thrust.

• The KSFM Journal of Fluid Machinery
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• v.19 no.1
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• pp.31-36
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• 2016

Hydraulic actuator is a primary component of the hydraulic valve systems. In this study, the thrust performance of hydraulic actuator was studied with different values of viscosity of hydraulic oil and rod diameter. Numerical analysis was performed using the commercial CFD code, ANSYS with 2-way FSI(Fluid-Structure Interaction) method and $k-{\varepsilon}$ turbulent model. Results show that increase in viscosity of hydraulic oil reduces the thrust of hydraulic actuator. In order to satisfy the output required of the actuator, it is necessary to compensate for the operating pressure. The results of pressure, velocity and thrust efficiency distributions in the hydraulic actuator were graphically depicted.

• Journal of Aerospace System Engineering
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• v.9 no.2
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• pp.13-18
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• 2015

Micro planar type liquid propellant thruster was fabricated by MEMS manufacturing process for micro/nano satellites applications. 90 wt.% hydrogen peroxide was used as propellant and for propellant decomposition, Pt/Al2O3 was used as catalyst. Micro thruster structure was made by 5 photosensitive glasses patterned with thruster component profiles. Objective thrust was 50 mN and required hydrogen peroxide mass flow was 2.1 ml/min, which was supplied by syringe pump and teflon tube in experimental test. Performance test said that average steady thrust was approximately 30 mN, around 60% of objective thrust, and transient time was about 5 sec. It is estimated that extended response time was due to high thermal energy loss of micro scale thruster and low enthalpy input by propellant mass flow.

• Transactions of Materials Processing
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• v.9 no.5
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• pp.478-485
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• 2000

This study aims to Improve the productivity in forming of flanged thrust engine bearings from two kinds of laminated sheet materials by integrating the forming processes or by reducing the number of the subsequent sizing and machining processes or by modifying the forming tools used. For steel-Al rolled blank, a design scheme for the one-step forming operation and the geometry of the tool set required is suggested and is verified its usefulness by the finite element simulation. And for steel-Cu sintered blank, the results of experiment and finite element analysis show that it is possible to improve the dimensional accuracy of formed products and to reduce the number of sizing processes just by modifying the shape and dimensions of initial blanks and flange forming dies, and by controlling the spring force.

• Journal of Mechanical Science and Technology
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• v.16 no.5
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• pp.639-646
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• 2002

In this paper, thrust equations for a rubber belt CVT are derived by considering the geometry and mechanism of the mechanical actuators. In order to solve the thrust equations, an algorithm to calculate the speed ratio is suggested for the given driver speed and load torque based on the actuator characteristic equations and existing formula for the belt thrust forces. Experiments are performed to investigate the driver speed-load torque-speed ratio characteristics at a steady state. The speed and torque efficiencies are measured and used to modify the actuator equations. It is found that the modified equations well predict the steady state characteristics. In addition, the shift dynamic model for a rubber belt CVT is derived experimentally. Simulation results of the CVT shift dynamics are in good accordance with the experiments and it is noted that different coefficients are required to describe the CVT shift dynamics for the upshift and the downshift.

• Journal of the Korean Society for Precision Engineering
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• v.24 no.8 s.197
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• pp.89-96
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• 2007

In this paper, a new air bearing stage with magnetic preload and a linear motor has been developed for the small precision machine systems. The new air bearing stage is unique in the sense that permanent magnets attached bottom of the iron core of table are used not only for preloading air bearings in vertical direction but also for generating thrust force by current of the coil at base. The characteristics of air bearings using porous pads were analyzed with numerical method, and the magnetic circuit model was derived for linear motor for calculating required preload force and thrust force. A prototype of single axis miniature stage with size of $120(W){\times}120(L){\times}50(H)\;mm^3$ was designed and fabricated and examined its performances, vertical stiffness, load capacity, thrust force and positioning resolution.

• Proceedings of the KIEE Conference
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• 1994.07a
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• pp.49-51
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• 1994

LIM has been developed for use in the industry, transportation, OA, FA because of the merits of direct drive and simple structure. The thrust control of LIM usually has been the average thrust control. However, vector control is required to control the instantaneous thrust force for an accurate positioning and speed control. To obtain dynamic vector control characteristics, it is important to make equivalent circuits which represent exactly LIM In this paper, asymmetrical d-q equivalent circuits is built [1] and vector control characteristics is calculated by simulation using these circuits.

• 유체기계공업학회:학술대회논문집
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• 2004.12a
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• pp.166-171
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• 2004

The Rate-of-Loading(ROL) effect of motor operated gate valves causes a decrease in the thrust delivered at a specific torque by the actuator under dynamic flow ${\Delta}$P conditions as compared to the no-flow, static conditions. This effect needs to be studied for the quantitative evaluation of motor operated gate valve operability. This study is performed to verify the validity for the application of ROL in the evaluation of operability of motor operated gate valves for the opening stroke. The ROL is assessed on the basis of in-situ test data for the opening and closing strokes. The results show that the distribution of the ROL for the operling sake has a tendency to the negative value when DP is higher than 150psid.

• Proceedings of the Computational Structural Engineering Institute Conference
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• 1999.10a
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• pp.113-118
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• 1999

The design program of fitting and thrust block including various shapes and sizes was developed for the GMR project (Great Man-made River Project in Lybia). It can automatically recalculated the minimum size of fitting required for the structural performance and can also determine the proper size of fitting for the safe and economic design by users. It was found that the results of this program was accurate and efficient when it was compared to other references. This program is also developed with GUI (Graphic User Interface) technology for the convenience of users.