• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.04a
• /
• pp.245-248
• /
• 2011

A multi pulse rocket motor(MPRM) has several advantages compared to the single one. The range and the terminal velocity of the guided missile can be remarkably increased by the application of the pulse separation device(PSD) to the solid rocket motor which resulted in appropriate thrust distribution. In this study, the full scale heavy type dual pulse rocket motor with the bulkhead type PSD was designed, manufactured, and fire-tested. The bursting time and pressure of PSD were analyzed by the pressure, thrust and vibration results of static fire tests. As a result, the design requirement was verified that bursting pressure is lower than 30% of 2nd pulse operating pressure.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.32 no.8
• /
• pp.64-71
• /
• 2004

A computational study on the supersonic flow around the lateral jet controlled missile has been performed. For this purpose a three dimensional Navier-Stokes computer code(AADL3D) has been developed and case studies have been performed by comparing the normal force coefficient and the moment coefficient of a missile body for different jet flow conditions including jet pressure and jet Mach number. The results show different behavior of normal force and moment variation according to jet pressure variation and jet Mach number variation. From the detailed flow field analyses, it is verified that most of the normal force loss and the pitching moment generation are taken place at the low-pressure region behind the jet nozzle. Furthermore, it is shown that the pitching moment can be efficiently reduced by obtaining the lateral thrust through higher jet Mach number rather than through high jet pressure.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.15 no.2
• /
• pp.23-28
• /
• 2011

The engine ground and altitude tests were carried out to investigate the effect of jet fuel alteration on the performance of a small turbojet engine. JP-S was supplied 8% higher than JP-8 by fuel metering system at the same command. The employment of JP-S showed the similar starting characteristic to that of JP-8, however, difference in the ignition time and acceleration rate of engine speed due to the difference of fuel flow rate by fuel metering system was observed. In spite of jet fuel alteration, the test results yield the similar steady-state engine performance in net thrust, air flow, exhaust gas temperature, etc. On the other hand, the fuel consumption of JP-S increased by 5 % compared with that of JP-8. In point of specific fuel consumption (SFC), SFC of JP-S was approximately 1.1~2.6 %, 5 % higher than that of JP-8 in ground and altitude tests respectively at the same thrust.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.11a
• /
• pp.410-415
• /
• 2010

The engine ground and altitude tests were carried out to investigate the effect of jet fuel alteration on the performance of a small turbojet engine. JP-S was supplied 8% higher than JP-8 by fuel metering system at the same command. The employment of JP-S showed the similar starting characteristic to that of JP-8, however, difference in the ignition time and acceleration rate of engine speed due to the difference of fuel flow rate by fuel metering system was observed. In spite of jet fuel alteration, the test results yield the similar Steady-State engine performance in Net thrust, Air flow, Exhaust Gas Temperature, etc. On the other hand, the Fuel consumption of JP-S increased by 5 % compared with that of JP-8. In point of Specific Fuel Consumption (SFC), SFC of JP-S was approximately 1.1~2.6 %, 5 % higher than that of JP-8 in ground and altitude tests respectively at the same thrust.

• Proceedings of the KSME Conference
• /
• 2007.05b
• /
• pp.3518-3523
• /
• 2007

An analysis program of specific impulse has been developed for a gas generator cycle rocket engine. The program has been verified by comparing the published performance data of the same cycle engine with RP-1 as fuel. A model for pressure drop of regenerative cooling and film cooling mass flow rate has been suggested to satisfy the necessary cooling condition with Jet-A1 as fuel. The engine mixture ratio is defined by the film cooling mass flow rate and the core mixture ratio. The optimal condition of the combustor pressure and engine mixture ratio has been found for maximum specific impulse.

• Proceedings of the KIEE Conference
• /
• 2011.07a
• /
• pp.979-980
• /
• 2011

영구자석 선형 동기 전동기(Permanent Magnet Linear Synchronous Motor)는 구조적으로 간단하며 고속화 고추력화 등의 많은 장점을 가지고 있지만 전기자 권선부의 슬롯-치 구조로 인한 코깅력과 단부효과에 의한 코깅력이 발생한다. 이는 추력 맥동의 원인이 되며, 소음과 진동을 발생시킨다. 따라서, 본 연구에서는 전기자를 분산배치할 경우 필연적으로 생기는 단부에 의한 코깅력을 저감하기 위해 기존의 전기자 끝단에 설치한 보조치를 응용하여 계단형 형상을 가진 보조치의 설치를 제안하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.254-257
• /
• 2011

Two types of thrusters(Descent Control Thruster (DCT) for reducing landing speed and Attitude Control Thruster (ACT) for attitude control) are mounted on the propulsion system of Ground test model lunar lander. In this paper, plume impingement effect and ground effect between DCT Modules are analyzed using numerical method when the impact occurred close to the ground.

• Proceedings of the KIEE Conference
• /
• 2006.07b
• /
• pp.879-880
• /
• 2006

횡자속의 기본원리는 릴럭턴스 전동기와 같다. 발생한 힘밀도는 공극과 극간격에 반비례하고 기자력의 자성에 비례한다. 이러한 횡자속 선형전동기를 적용할 경우 추력의 변화로 인해서 진동과 힘의 불평형이 발생하는 것이 일반적이다. 본 논문에서는 이러한 추력 불평형과 진동특성을 향상시킬 수 있는 방법이 다상형으로 구동하는 방법이 있으며 힘을 균일하게 할 수 있고 전동기의 체적을 줄이고 진동특성을 저감시킬 수 있다는 것이라고 판단된다.

• Tribology and Lubricants
• /
• v.13 no.3
• /
• pp.1-9
• /
• 1997

인류가 지구상에 존재하기 이전에도 바다 속에는 오징어와 같이 자신의 힘만으로 분사 추진을 하여 움직이는 생물이 존재하였음에도 불구하고 인류는 이러한 반작용 원리를 이용한 항공용 가스터빈 엔진을 고안하는데 1900년 이상의 세월을 보내야 하였으며, 이 긴 세월 동안 많은 장치들이 고안되었다. 그러나, 실제로 이러한 원리를 사용한 현재와 같은 가스터빈 엔진의 개발은 1940년대 중반에야 가능하게 되었다. 이후 소형이면서 높은 추력을 발생시키기 위하여 많은 노력이 이루어져 왔으며, 이를 위하여 가스터빈 엔진의 주축 베어링, gearbox, seal 및 윤활 시스템 등은 더욱 큰 부담을 가질 수 밖에 없었다. 따라서, 이러한 어려움을 해결하고 보다 높은 추력을 발생시키는 가스터빈을 개발하는데 트라이볼로지의 역할이 중요하다고 할 수 있다. 가스터빈에서의 트라이볼로지의 적용 분야는 main-shift bearing, lubrication system, gearbox 및 seal등을 들 수 있으나, bearing과 lubrication을 중심으로 기술하고자 한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.33 no.12
• /
• pp.48-53
• /
• 2005

In this paper, we present our recent progress in the LIPCA (Lightweight Piezo-Composite Actuator) application for actuation of a flapping wing device. The flapping device uses linkage system that can amplify the actuation displacement of LIPCA. The feathering mechanism is also designed and implemented such that the wing can rotate during flapping. The natural flapping-frequency of the device was about 9 Hz, where the maximum flapping angle was achieved. The flapping test under 4 Hz to 15 Hz flapping frequency was performed to investigate the flapping performance by measuring the produced lift and thrust. Maximum lift and thrust were produced when the flapping device was actuated at about the natural flapping-frequency.