• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.04a
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• pp.13-13
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• 2000

일반적으로 고체추진 로켓 모타의 개발단계 때 공통적으로 수행되는 주시험(main test)으로는 추력, 압력, 회전률 등의 성능측정을 하기 위한 정적연소시험(static firing test), 내부 정수압(hydrostatic pressure)에 의한 폭발 압력 시험, 연소중이나 연소 후 케이스에 대한 굽힘 강성 시험, 이외에 노화 시험, 환경시험 등이 요구된다. 그러나 신궁과 같은 휴대용 대공 시스템의 추진기관 개발의 경우에는 사수를 보호하기 위해 여러 가지 안전장치들이 설계되고, 이러한 장치들의 성능에 대한 요구 조건들을 확인하기 위한 특수시험(specific test)들이 필요하게 된다. 이러한 특수시험을 위한 각종 시험대들을, 위에서 언급한 주시험을 위해 사용되는 정적시험대(static test bench)들과 구분하기 위해 동적 시험대(DTB : Dynamic Test Bench)라고 한다. 본 연구에서는 신궁 추진기관의 사출모타 점화에서 비행모타 점화에 이르는 일련의 비행절차를 확인하기 위한 동적 시험대 설계 및 제작, 계측장치 구성 및 데이터 획득 방법 등에 관한 내용을 소개하며, 동적 시험대에서 수회에 걸쳐 수행된 동적 시험 결과를 분석/정리하였다.

• Transactions of the Korean Society of Mechanical Engineers
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• v.16 no.1
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• pp.175-179
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• 1992

Generally speaking, natural gas possesses several characteristics that make it desirable as an engine fuel : for example (1) lower production cost, (2) abundant commodity and (3) cleaner energy source than gasoline. Due to the physical characteristics of natural gas, the volumetric efficiency and flame speed of a natural gas engine are lower than those of a gasoline engine, which results in a power loss of 10-20% when compared to a convensional gasoline engine. This paper describes the results of a research to improve the performance of a natural gas engine through the modification and controls of air/fuel ratio, spark timing advance and supercharging effect by forced air supply method.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.43-46
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• 2004

This work is experimental study about a nozzle part in the aerodynamic igniter using only compressible gas. In study, constructions of the aerodynamic igniter using a supersonic nozzle and an aerospike nozzle have been introduced, and experimental results(mainly max. heating temperature characteristics) have been presented. Using of the supersonic nozzle leads to faster and higher temperature in same mass flow, and the aerospike nozzle works in wide variable range of pressure.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.3
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• pp.70-77
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• 2014

In this paper, the development of unique model of the 2.75 inch rocket propulsion system is described. Recently developed korean 2.75 inch rocket propulsion system shows the improvement of a flame stability resulted from a change in the configuration of propellant grain, and of an incidental ignition protection function using the EMI(electromagnetic interference) filter on ignition system. Moreover it is shown that a directional flight stability is improved by increasing the number of fins and changing the nozzle configuration. Static firing test and thermal shock test were conducted for the validation before flight, and flight test of 210 rounds of rockets was conducted to verify the trajectory uniformity. In addition, intellectual property issues can be overcome with the unique korean 2.75 inch rocket motor as well as the performance improvement.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.6
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• pp.69-78
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• 2010

As part of preliminary study for development of 1,200 N-class bipropellant rocket engine with the concentrated hydrogen peroxide, bipropellant engine elements were designed and experimentally tested. The catalysts of $MnO_2$ and $MnO_2$ added Pb as an additive were compared to achieve high decomposition performance and the catalytic reactor with $MnO_2$ added Pb was designed and its decomposition efficiency of 97.2% was achieved. The autoignition tests of kerosene by decomposed hydrogen peroxide were carried out under various equivalence ratios to ignite without additional ignition sources. Autoignition were achieved in all experimental conditions and $C^*$ efficiencies at each condition were at or above 90%. From the measured thrust results, the highest value was 830 N which is in corresponds with 1,035 N at vacuum level assuming $C^*$ efficiency equals $I_{sp}$ efficiency.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.156-164
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• 2010

As part of preliminary study for development of 1,200 N-class bipropellant rocket engine with the concentrated hydrogen peroxide, bipropellant engine elements were designed and experimentally tested. The catalysts of $MnO_2$ and $MnO_2$ added Pb as an addictive were compared to achieve high decomposition performance and the catalytic reactor with $MnO_2$ added Pb was designed and its decomposition efficiency of 97.2% was achieved. The autoignition tests of kerosene by decomposed hydrogen peroxide were carried out under various equivalence ratios to ignite without additional ignition sources. Autoignition were achieved in all experimental conditions and $C^*$ efficiencies at each condition were at or above 90%. From the measured thrust results, the highest value was 830 N which is in corresponds with 1,035 N at vacuum level using 94.1% theoretical $I_{sp}$.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.1
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• pp.58-67
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• 2021

This paper describes the development for the dual thrust rocket motor with two types of propellants with different combustion characteristics. We developed the composition of two kinds of propellant to be applied to a rocket motor, and improved a propellant charging process in a free grain type to improve the adhesion method and the problems of adhesion between different propellants. In addition, to meet the ignition phenomenon as a small rocket motor, the ignition delay was improved by applying a nozzle plug developed in a high density foam. The propulsion rocket motor reflecting this design and the improved manufacturing process was evaluated through a ground performance test.

• Proceedings of the KIEE Conference
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• 2000.11d
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• pp.624-628
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• 2000

이 논문에서는 이산형 상태 공간 모델에서의 새로운 FIR 필터를 제안한다. 선형성, 무진동성, FIR 구조, 초기 조건과의 무관성등을 디자인 과정에서 고려해서 성능 지표를 최소화 하는 필터를 구한다. 성능지표로는 구간에서 외란 에너지와 현재 추정 에러의 최대 이득으로 생각하며, 이 지표는 일반적인 성능지표와는 다르다. 제안된 필터는 배치 형태로 먼저 구하고, 점화식 형태로 바꿀 수 있음을 보인다. 제안한 필터는 확률론적 시스템의 이동 구간 무편향 FIR 필터(RHUFF)와 유사함을 보인다.

• Journal of Energy Engineering
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• v.23 no.1
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• pp.75-80
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• 2014

The past several years have seen a substantial growth in mathematical modeling activities whose interests are to describe the performance, efficiency and emissions characteristics of various types of internal combustion engines. The key element in these simulations of various aspects of engine operation is the model of the engine combustion process. Combustion models are then classified into three categories: zero-dimensional, quasi-dimensional and multidimensional models. zero-dimensional models are built around the first law of thermodynamics, and time is the only independent variable. This paper presents a introduction to the combustion characteristics of a spark ignition combustion modeling by zero-dimensional model.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.4
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• pp.77-84
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• 2006

With the development of micro/nano spacecraft, concepts of micro propulsion are introduced for orbit transfer and drag compensation as well as attitude control. Micro solid propellant thruster has been attention as one of possible solution for micro thruster. In this paper, micro solid propellant thruster is introduced and research on basic components of a micro solid propellant thruster is reported. Micro Pt igniter was fabricated through negative patterning and quantitative effect of geometry was estimated. The characteristic of HTPB/AP solid propellant was investigated to measure the homing velocity. A combustion chamber was fabricated by means of anisotropic etching of photosensitive glass. Finally, micro solid propellant thrusters having various geometries were fabricated and tested.