• Journal of Space Technology and Applications
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• v.2 no.1
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• pp.30-40
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• 2022

This paper illustrates the trajectory design of drift distance recovery after initial launch and proximity operation when verifying rendezvous/docking technology using nanosatellites. The rendezvous/docking is a technology that is the basis of on-orbit servicing technology and is a preemptive process essential for approaching a target object. In particular, since it is difficult to verify in space, nanosatellites have recently been used to reduce the risk and cost of the development stage. Therefore, this paper not only introduces the configuration and specifications of thrusters for nanosatellites but also designs relative trajectories that can take into account the thrust limitations which come from the small size and low power of nanosatellites. In addition, we intend to be helpful in later designing scenarios according to the improvement of available thruster performance through comparison of trajectories and thrust usage with cases without thrust limitations.

• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
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• 2004.07b
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• pp.757-760
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• 2004

Shaking beam을 이용한 초음파 선형모터는 모터 구동부에서 발생하는 타원궤적이 선형 slider 와 마찰이 되어 선형운동을 발생시킨다. 이러한 초음파 선형모터에서 설계변수는 모터의 효율과 추력(thrust force) 등 동특성을 결정한다. 특히 초음파 모터 동작부의 tip 과 선형 slider 의 contact point와 압착은 모터의 속도, 추력 동작 주파수, 효율에 직접적인 영향을 주는 중요한 parameter 로 작용된다. 본 연구에서는 모터와 선형 slider 의 압착과 contact point둥의 설계변수가 초음파 선형 모터의 성능에 주는 영향을 고찰하였다. 모터으구동부와 선형 slider 사이의 압착력 ($10N{\sim}50N$)과 4가지 곡률을 갖는 tip을 설계변수로 취하였다. Tip 의 형태에 따른 곡률과 모터 구동부와 선형 slider 사이의 압착력 변화에 따른 모터의 동작특성이 변화되는 것을 확인할 수 있었다.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.1
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• pp.35-44
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• 2011

Mathematical modelling for liquid rocket engine(LRE) main components were conducted to predict the dynamic characteristics when the LRE operates at the transient condition, which include engine start up, shut down, or thrust control. Propellant feeding system is composed of fuel and oxidizer feeding components except for regenerative cooling channel for the fuel circuit. Components modeling of pump, pipe, orifice, control valve, regenerative cooling channel and injector was serially made. Hydraulic tests of scale down component were made in order to validate modelling components. The mathematical models of engine components were integrated into LRE transient simulation program in concomitant with experimental validation.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.2
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• pp.10-16
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• 2012

A computational analysis of nozzle flow characteristics and plume structure is conducted to examine performance of the supersonic nozzle employed in a thruster for ground firing test. At first, flow simulations in two-dimensional converging-diverging nozzle are performed for the verification of computational capability as well as turbulence model validity. Axisymmetric converging-diverging nozzles for ground firing test are analyzed with the k-${\omega}$ SST model. A performance penalty caused by flow separation in a diverging section is observed in initially-designed nozzle. The performance could be enhanced by the modification of the diverging section of nozzle contour.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.213-217
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• 2011

Unsteady numerical simulations of pintle nozzles were implemented for solid rocket thrust vector control. The variation of pintle location was considered using unsteady numerical techniques, and dynamic characteristics of various pintle models were investigated. In order to consider the variation of the pintle location, a moving mesh method was applied. The effects of shape and location of the pintle nozzle have been analytically investigated. And the results were compared with numerical results. The chamber pressure, mass flow and thrust are analyzed to take account dynamic characteristics of pintle performance.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.100-100
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• 2003

다목적실용위성 1호의 자세제어는 추력기를 이용한 방법과 반작용 휠을 이용한 방법으로 나눌 수 있다. 추력기를 이용한 방법은 위성이 안전모드에 진입하거나 궤도조정시 이용되며, 정상 운영모드에서 촬영임무를 수행할 때는 반작용 휠을 이용하여 위성의 자세를 제어하고 있다. 자세제어는 제로 모멘텀 바이어스(Zero Momentum Bias)를 이용하여 3축 제어방식을 사용하고 있다. 지구센서(CES, Conical Earth Sensor)와 자이로(Gyro)를 통하여 얻은 자세정보를 이용하여 위성의 탑재컴퓨터에서 제어로직을 수행하면 MDE(Motor Drive Electronic)를 통해 모멘텀을 입력받아 반작용 휠의 회전속도를 변화 시켜 자세제어를 수행한다. 본 논문은 위성의 임무기간 동안 반작용 휠을 이용하여 자세제어를 수행한 결과를 바탕으로 위성의 제로 모멘텀 바이어스를 통한 자세제어계의 변화를 분석하여 향후 연장 임무기간 동안 발생할 수 있는 운영상의 문제점을 확인하고, 이에 대한 조치 방법과 자세제어계의 운영 방안을 제시하고 한다.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.15 no.6
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• pp.3821-3826
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• 2014

This paper proposes a methodology for developing the performance of a solenoid valve for vehicles based on the dynamic analysis model by an electromagnetic field. The high performance solenoid model with a low current and high thrust was induced through the shape optimal design of the yoke and plunger. To perform the dynamic analysis of the solenoid valve, the input current profile was analyzed. The speed and thrust information was analyzed by FEM with this current profile. The co-simulation method of the circuit model of control logic and electromagnetic model of the solenoid valve was also proposed to analyze the performance with several current patterns. Finally, the performance of the original model and optimal one was compared.

• Proceedings of the Korean Society of Tribologists and Lubrication Engineers Conference
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• 1999.06a
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• pp.111-118
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• 1999

In this paper, linearized dynamic characteristics of parallel line pivoted pad thrust bearing(hereinafter refer to PLP thrust bearing) was analyzed by perturbation method with inlet pressure. Inlet pressure and excitation frequency irfluence dynamic characteristics of PLP thrust bearing at all operating condition, such as angular pivot position, mass of pad. Therefore, the characteristics is have to analyzed with inlet pressure, excitation frequency, mass of pad and thickness of pad. Otherwise, the analysis is able to estimate the characteristics over or under.

• Proceedings of the Korean Society of Tribologists and Lubrication Engineers Conference
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• 1997.04a
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• pp.91-100
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• 1997

In this paper the linearzed stiffness and damping coefficients of tilting pad thrust bearing are calculated by the perturbation method. The coefficients are obtained for a wide range of pivot positions. The effects of exciting frequency and pad mass on stiffness and damping coefficients are investigated. Critical frequencies due to the tilting motions of the pad are presented and are shown to be strongly influenced by the pivot position and pad mass.

• Tribology and Lubricants
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• v.16 no.4
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• pp.274-281
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• 2000

In this paper, linearized dynamic characteristics of parallel line pivoted pad thrust bearing (here-inafter refer to PLP thrust bearing) was analyzed by perturbation method with inlet pressure. Inlet pressure and excitation frequency influence dynamic characteristics of PLP thrust bearing at all operating conditions, such as angular pivot position, mass of pad. Therefore, the characteristics have to be analyzed with inlet pressure, excitation frequency, mass of pad and thickness of pad. Otherwise, the analysis may be over or under estimate.