• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.57-60
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• 2003

An axisymmetric compressible flow solver accounting for chemical equilibrium has been developed as an analysis tool exclusively suitable for performance prediction and optimum contour design of LRE thrust chamber. By virtue of several features focusing on user-friendliness and effectiveness including automatical grid generation and iterative calculations with changes in design parameters prescribed through only one keyword-type input file, a design engineer can evaluate very fast and easily the influences of various design inputs such as geometrical parameters and operating conditions on propulsive performance. Validations have been carried out for various aspects by detailed comparisons with the result of CEA code, experimental data of JPL nozzle, actual data for two historical engines, and ReTF data for KSR-III.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.14 no.4
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• pp.17-23
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• 2006

This paper describes the preliminary design procedure for the hybrid propulsion system. For a given mission defined by velocity increment, the design of a polyethylene/LOX hybrid rocket was implemented. In addition, Seven-cluster multi-port fuel-grain was considered. After determining the system size including the combustion chamber, the performance parameters such as specific impulse, thrust, characteristic velocity, and thrust coefficient can be predicted by using empirical regression rate correlation, though most of preliminary design code assume constant regression rate. The results of the performance prediction indicated that besides the widely used HTPB/LOX, polyethylene/LOX hybrid motor can be a viable alternative to the more widely used SRMs.

• Proceedings of the KIEE Conference
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• 1997.07a
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• pp.211-214
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• 1997

This paper describes the position accuracy performance improvement of hybrid type LPM. The harmonics are included in the thrust force component of LPM, those are generated from the the nonlinearity of intrinsic magnetic saturation characteristic and mechanical construction, and so on. In this paper, the performance improvable methode is proposed for the better thrust force by the corrected exciting current injection, and precise position control is achieved.

• Computers and Concrete
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• v.22 no.2
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• pp.239-248
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• 2018

TBM penetration rate is a function of intact rock properties, rock mass conditions and TBM operational parameters. Machine rate of penetrationcan be predicted by knowledge of the ground conditions and its effects on machine performance. The variation of TBM operational parameters such as penetration rate and thrust plays an important role in its performance. This study presents the results of the analysis on the TBM penetration rates in schistose rock types present along the alignment of Golab tunnel based on the analysis of a TBM performance database established for every stroke through different schistose rock types. The results of the analysis are compared to the results of some empirical and theoretical predictive models such as NTH and QTBM. Additional analysis was performed to find the optimum thrust and revolution per minute values for different schistose rock types.

• Journal of Aerospace System Engineering
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• v.5 no.2
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• pp.27-32
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• 2011

The purpose of this study was to suggest 10 kinds of case and perform Mixed-flow pump optimum design and performance analysis depending on the shape of the impeller for suitable to water jet propulsion system. H20 was applied to the material properties, to analysis conditions for water jet axial impeller 1000 rpm given analysis was performed. Interpretation for each case as a result of speed, pressure, flow rate, calculate the thrust at the Inlet Angle $30^{\circ}$ and Outlet Angle $30^{\circ}$ could see a persistence of optimal performance.

• Journal of the Korean Society of Manufacturing Process Engineers
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• v.21 no.5
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• pp.53-60
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• 2022

In this study, the conceptual design and performance evaluation of a personal air vehicle (PAV) is presented, which is a potential futuristic individual transportation. The blade element theory (BET) is employed to compute a rotational velocity. A computational fluid dynamics (CFD) simulation is performed to investigate the difference in the thrust performance in the rotor axis distance of a quad-copter PAV in hovering. Modal analysis is performed to create a Campbell diagram to investigate critical speed. Consequently, a quad-copter PAV changes the aerodynamics thrust and critical velocity according to the rotor axis distance.

• Advances in aircraft and spacecraft science
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• v.10 no.4
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• pp.369-391
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• 2023

In our research we have offered a solid solution for aeronautical analysis. which can guarantee the asymptotic stability of coupled nonlinear facilities. According to the theoretical solutions and methods presented, the engine of this aircraft is a small high-bypass turbofan engine. using the non-linear aero-motor control approach and this paper focuses on the power management function of the aero-motor control system. These include static controls and transient controls. A mathematical model of the high-bypass-ratio two-spool unmixed-flow aeroengine was developed through a set of nonlinear dynamic equations verified by experimental data. A single actuator using the displacement method is designed to maintain a certain level of thrust under steady-state conditions. and maintains repeatable performance during transient operation from the requested thrust phase to the next. A single controller can compensate for the effects of noise and harmonic noise at many performance points. And the dynamic performance of a single controller is satisfactory during the transient. for fairness Numerical and computer experiments are described in the perfection of the methods we offer in research.

• Proceedings of the KIEE Conference
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• 2011.07a
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• pp.1103-1104
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• 2011

This paper presents 1kW BLDC motor drive system and magnetic coupler for water thrust in ROV. In order to get a high performance and reliability, some design flow is proposed in this paper. The proposed system is verified by the experimental tests.

• Proceedings of the KIEE Conference
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• 1992.07b
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• pp.637-641
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• 1992

This paper presents a fundanental method to analyze and design a Single-sided Linear Induction Motor(SLIM) as a propulsion system for magnetic levitation vehicles of DAEJEON EXPO'93 in Korea. The performance characteristics of the designed SLIM are examinated by the thrust force, the normal force, the efficiency and the power factor according to the change of input frequency. The dimension of the SLIM is 1792mm long ${\times}$ 200mm width ${\times}$ 58mm high and the rated thrust is 1300 Newtons at the operating speed of 40 Km/h.

• 한국전산유체공학회:학술대회논문집
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• 1997.10a
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• pp.66-72
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• 1997

Circular-to-rectangular transition ducts are used as exhaust components of high performance fighter aircraft with vectored thrust nozzles. Three-dimensional incompressible Navier-Stokes solver is used to analyze the transition duct. Cross sections of transition duct are defined by superelliptic equation. The grid system is generated by Non-Uniform Rational B-Spline, after generating surface grid by blending the cross sections. Good agreement between the results of the computational simulation and the experimental data is observed.