• Transactions of the Korean Society of Mechanical Engineers B
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• v.28 no.10
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• pp.1264-1270
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• 2004

In this paper research on micro solid propellant thruster is reported. Micro solid propellant thruster has four basic components; micro combustion chamber, micro nozzle, solid propellant and micro igniter. In this research igniter, solid propellant and combustion chamber are focused. Micro igniter was fabricated through typical micromachining and the effect of geometry was evaluated. The characteristic of solid propellant was investigated to observe burning characteristic and to obtain burning velocity. Change of thrust force and the amount of energy loss following scale down at micro combustion chamber were estimated by numerical simulation based on empirical data and through the calculation normalized specific impulses were compared to figure out the efficiency of combustion chamber.

• Proceedings of the KSME Conference
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• 2004.04a
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• pp.1280-1285
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• 2004

Microsystem technology has been applied to space technology and became one of the enabling technology by which low cost and high efficiency are achievable. Micro propulsion system is a key technology in the miniature satellite because micro satellite requires very small and precise thrust force for maneuvering and attitude control. In this paper research on micro solid propellant thruster is reported. Micro solid propellant thruster has four basic components; micro combustion chamber, micro nozzle, solid propellant and micro igniter. In this research igniter, solid propellant and combustion chamber are focused. Micro igniter was fabricated through typical micromachining and evaluated. The characteristic of solid propellant was investigated to observe burning characteristic and to obtain burning velocity. Change of thrust force and the amount of energy loss following scale down at micro combustion chamber were estimated by numerical simulation based on empirical data and through the calculation normalized specific impulses were compared to figure out the efficiency of combustion chamber.

• Proceedings of the SAREK Conference
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• 2009.06a
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• pp.762-767
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• 2009

Some types of semi-Volatile organic compounds (SVOC) that are emitted from plastics used in building materials and household appliances have associated health risks, even at low concentrations. In this study, micro chamber method for measuring SVOC is introduced and SVOC such as di (2-ethylhexyl) phthalate and butylated hydroxyltoluene emitted a flooring material were measured using a micro chamber method. Airflow characteristics in a micro test chamber deeply depended on air exchange rate. From the evaluation using an index of air change efficiency, such as the air age and the coefficient of air change performance, a fixed air exchange rate of $1.5\;h^{-1}$ in the micro chamber is desirable.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.67-70
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• 2006

In this study micro-thrust measurement method in high vacuum chamber is introduced. This is important for the development of micro-thruster for micro-satellite applications. At Chungnam national University, high-vacuum experimental facility has been constructed to simulate space environment. And strain gauge besed micro-thrust measurement in vacuum chamber has been studied and discussed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.147-150
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• 2003

The purpose of this research was to develope components of micro solid propellant thruster. Micro solid propellant thruster had four basic components: combustion chamber, nozzle, solid propellant and micro heater for ignition. A performance of micro heater and characteristic of solid propellant was investigated. Micro heater was fabricated by conventional MEMS process and Platinum layer was used for heating element. Effect of geometry parameters on micro heater was tested. The temperature responses of heater with respect to each parameters was compared for a given electrical power. The characteristic of solid propellant(HTPB/AP) was investigated to obtain burning velocity in small chamber. Additionally, a capacity of filling propellant with high viscosity in small chamber was checked to guarantee for the micro fabrication.

• The Transactions of the Korean Institute of Electrical Engineers C
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• v.50 no.6
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• pp.307-313
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• 2001

A micro syringe which can be attached to the end of a micro intravascular endoscope for drug injection is fabricated and its characteristic is tested. The syringe consists of a drug chamber and an actuator chamber which are separated by a silicone rubber membrane. The drug chamber is filled with liquid drug by the membrance actuation caused by the vaporization and condensation of the working liquid in the actuator chamber. The liquid drug is ejected by the electrolysis of the working liquid. The membrane deflection by each actuation method has been measured. The liquid ejection image has been captured during the electrolysis of the electrolyte. Also, the successful operation of the micro syringe under the normal blood pressure was verified.

• Journal of the Korean Society of Manufacturing Technology Engineers
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• v.26 no.4
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• pp.387-394
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• 2017

This paper develops a pump system for patient with chronic pain or cancer. The pump module is consists of two micro-valve and membrane. The micro-valve is operated by a solenoid. With two solenoid valves which are connected via a drug transport line, the inlet and outlet are completely blocked. A silicon rubber membrane located between the two valves makes the flow-rate constant without any backflow. This pump module can control the flow-rate of drugs by controlling the time that the valves are opened and closed. The reservoir consists of a drug chamber and a gas chamber. As the gas chamber encloses the drug chamber, propellant gas which is injected into the gas chamber pressurizes the drug chamber regardless of volume of the drug chamber. To design the pump module, analysis a constant efficiency test, and accuracy test for the pump module were conducted.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.3 no.4
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• pp.233-239
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• 2002

The technology of joining BT (Biotechnology) with NT (Nanotechnology) must be rapidly arranged in 21c. Specially, the technical value is important more and more since the research about MEMS, which synthesizes BT and NT, is variously proceeding on the wide fields. This study by simulation shows the Fluid-Flow within micro Pump used in Bio-MEMS technology through Fluent Program. Namely, this experiment shows the most suitable external conditions and Pump Model within micro Pump by observing the flow of fluids as to the conditions of pressure, temperature and Model when the Fluid flows within micro Pump. We saw the variousness of pressure and temperature as to the existence of Chamber through examining by reference of Fluid-Flow. In the case of the existence of Chamber, the variousness of pressure and temperature is less than in the case of the non-existence of Chamber. By this simulation, we know that the Pump, which has a Chamber, affects the Fluid-Flow less than that. So we can say that it is necessary for us to design the Pump which has a Chamber.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.251-254
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• 2006

Micro thruster is a key technology in the micro/nano satellite. MSPT has been attracted attention as a one of possible solution for micro thruster MSPT as a systems four components. It is composed of nozzle, igniter, combustion chamber and propellant. This paper surveys varioud MSPTs which have been reported. The model of MSPT arrays for total impulse of 1 mNs is proposed. Combustion chamber is designed and fabricated.

• Advances in biomechanics and applications
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• v.1 no.1
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• pp.23-40
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• 2014

This paper examines the blood chamber of a left ventricular assist device (LVAD) under static loading conditions and standard operating temperatures. The LVAD's walls are made of a temperature-sensitive polymer (ChronoFlex C 55D) and are covered with a titanium nitride (TiN) nano-coating (deposited by laser ablation) to improve their haemocompatibility. A loss of cohesion may be observed near the coating-substrate boundary. Therefore, a micro-scale stress-strain analysis of the multilayered blood chamber was conducted with FE (finite element) code. The multi-scale model included a macro-model of the LVAD's blood chamber and a micro-model of the TiN coating. The theories of non-linear elasticity and elasto-plasticity were applied. The formulated problems were solved with a finite element method. The micro-scale problem was solved for a representative volume element (RVE). This micro-model accounted for the residual stress, a material model of the TiN coating, the stress results under loading pressures, the thickness of the TiN coating and the wave parameters of the TiN surface. The numerical results (displacements and strains) were experimentally validated using digital image correlation (DIC) during static blood pressure deformations. The maximum strain and stress were determined at static pressure steps in a macro-scale FE simulation. The strain and stress were also computed at the same loading conditions in a micro-scale FE simulation.