• 소음진동
• /
• 제9권6호
• /
• pp.1157-1165
• /
• 1999

Dynamic stability of a flying structure undertaking constnat and pulsating thrust force is investigated in this paper. The equations of motion of the structure, which is idealized as a free-free beam, are derived by using the hybrid variable method and the assumed mode method. The structural system includes a directional control unit to obtain the directional stability. Unstable regions due to periodically pulsating thrust forces are obtained by using the Floquet's theory. Stability diagrams are presented to illustrate the influence of the constant force, the location of gimbal, and the frequency of pulsating force. The validity of the diagrams are confirmed by direct numerical simulations of the dynamic system.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
• /
• 한국우주과학회 2008년도 한국우주과학회보 제17권2호
• /
• pp.25.3-26
• /
• 2008

The direct way to the moon is to start from the parking orbit by using impulsive thruster In previous domestic research, the direct way has been studied by using a single impulsive shot. However, when a single impulsive shot occurs to go into a Translunar orbit, gravity losses occur because thruster is not impulsive shot but the finite burns and it causes the gravity losses. To make up for the weak point of a single impulsive shot, this paper divides TLI (Trans Lunar Injection) into several small burns. Therefore, departure loop trajectory and the Translunar trajectory. This method is useful not only to reduce the gravity losses but also to check the condition of satellite. By using this method, this paper demostrates the optimized trajectory from Earth parking orbit to lunar mission orbit which minimizes the fuel, and the SNOPT (Sparse Nonlinear OPTimizer software) is used to find optimal solution. Also, this paper provides lunar mission profile which includes the mission schedule when TLI, LOI (Lunar Orbit Insertion) maneuvers occur, a mount of fuel when thruster is used and other mission parameters.

• 대한전기학회:학술대회논문집
• /
• 대한전기학회 2004년도 하계학술대회 논문집 B
• /
• pp.1223-1225
• /
• 2004

In difference with the rotary type electrical machinery, the linear induction motor(LIM) that generates the direct thrust directly, is widely used for the operation system of electrified railroad, elevation system, conveyer system, and so on. The operational principle of linear induction motor is constructively similar to the general rotary induction motor. It is difficult to realize the complicate linear induction motor which is applied SVPWM system, but widely used in vector motor control system or servo control system because of its high performance in current control. In this paper, we presented the dynamic characteristic analyzing methode, and calculated efficiently the end effect by using equivalent circuit methode in the operating linear induction motor control system for Maltlab simulink modeling.

• 대한전기학회:학술대회논문집
• /
• 대한전기학회 2000년도 하계학술대회 논문집 B
• /
• pp.891-893
• /
• 2000

Because of linear operation by direct drive and compact system, and the free accumulation of position error, LPM is suitable for proportional control valves actuator. In this study, to develop electromagnetic proportional valves actuator we designed tooth shape of double sides LPM and suggested the driving principle based upon the excitation method, It's the magnetic structure is so complex by the cubic effect configuration that finite element analysis is required. By the 3D finite element analysis, we got the magnetic distribution of LPM and analyzed static thrust force characteristics. By this analyzation, we obtained basic data required for the practical use of driving system for the proportional control valves. Thus, considering electrical and mechanical constants we could design and manufacture double sides LPM for the proportional control valves.

• 한국항공우주학회지
• /
• 제47권10호
• /
• pp.738-746
• /
• 2019

한국형발사체 3단에 사용되는 7톤 짐벌엔진의 추력벡터제어에는 전기유압식 구동장치시스템 대신 중량, 비용 및 시험평가 등의 측면에서 더 효율적인 전기기계식 구동장치시스템을 사용한다. 전기기계식 구동기는 위치제어 서보 구동기로 고진공에서도 운용 가능한 BLDC 모터를 사용한다. 짐벌엔진을 갖는 발사체의 경우 구동기 자체 진동모드와 구동기를 지지하는 기체구조체의 벤딩모드, 짐벌엔진의 관성부하 등이 조합되어 합성공진 현상이 발생할 수 있다. 합성공진이 발생할 경우 발사체 자세제어는 불안정해진다. 이러한 관계로 짐벌엔진 및 기체구조체 지지부, 구동장치시스템의 고유 특성을 고려하여 강성에 대한 요구규격이 적용되어 왔다. 한국형발사체 3단 7톤 짐벌엔진의 경우 구동장치시스템의 강성요구규격은 $3.94{\times}10^7N/m$ 수준이며 이를 만족시키기 위한 직구동 방식전기기계식 구동기를 설계하였다. 본 논문에서는 강성요구규격을 기반으로 설계된 직구동 전기기계식 구동기의 등가강성 해석모델을 제안하고, 이를 실험결과로 검증하였다.

• 한국광학회:학술대회논문집
• /
• 한국광학회 2000년도 제11회 정기총회 및 00년 동계학술발표회 논문집
• /
• pp.18-19
• /
• 2000

Recently, coherent control of exciton populations has been demonstrated through terahertz, reflection, and four-wave-mixing experiments. However, the most direct probe of exciton population control is the absorption, which has been lacking in previous studies. In this report, we probe the time evolution of exciton population directly through a transmission experiment. In particular, using upconversion technique with both narrow (spectrally broad) and long (spectrally narrow) pulses, we can obtain both the temporal and the spectral information. The main thrust of our report is that when phase controlled, the second pulse can be either greatly enhanced or completely destroyed by gaining energy from exciton (thus destroying the exciton population) or giving all of its energy to the system (thus greatly increasing the exciton population), respectively. (omitted)

• Journal of Mechanical Science and Technology
• /
• 제19권2호
• /
• pp.682-691
• /
• 2005

This paper describes the design, fabrication, and testing of a microturbine developed at Seoul National University. Here, the term 'microturbine' refers to a radial turbine with a diameter on the order of a centimeter. Such devices can be used to transmit power for various systems. The turbine is designed using a commercial CFD code, and it has a design flow coefficient of 0.238 and work coefficient of 0.542. It has 31 stator blades and 24 rotor blades. A hydrodynamic journal bearing and hydrostatic thrust bearings counteract radial and axial forces on the rotor. The test turbine consists of a stack of five wafers and is fabricated by MEMS technology, using photolithography, DRIE, and bonding processes. The first, second, fourth, and fifth layers contain plumbing, and hydrostatic axial thrust bearings for the turbine. The third wafer contains the turbine's stator, rotor, and hydrodynamic journal bearings. Furthermore, a turbine test facility containing a flow control system and instrumentation has been designed and constructed. In performance tests, a maximum rotation speed of 11,400 rpm and flow rate of 16,000 sccm have been achieved.

• 한국추진공학회지
• /
• 제20권4호
• /
• pp.87-93
• /
• 2016

직접 연결식(DC) 고도모의 엔진시험 수행 시, 공기 흡입 덕트와 항공용 엔진 사이에 래버린스 씰이 설치된다. 래버린스 씰은 이 둘을 기계적으로 격리시킴으로써 주추력 및 측추력을 보다 정확하게 측정할 수 있도록 돕는다. 하지만 덕트 내부 공급공기에 높은 수직 온도구배가 발생할 경우, 래버린스 씰의 격리가 파괴되어버린다. 본 논문에서는 이러한 접촉 문제를 해결하기 위한 노력의 일환으로 래버린스 씰 온도 제어장치를 제작/설치하였다. 본 장치를 실제 항공용 엔진시험에 적용한 결과, 높은 수직 온도구배가 생성되어도 래버린스 씰의 격리가 잘 유지되는 것을 확인할 수 있었다.

• KIEE International Transaction on Electrical Machinery and Energy Conversion Systems
• /
• 제5B권2호
• /
• pp.154-161
• /
• 2005

In the machine tool industry, direct drive linear motor technology is an interesting means to achieve high acceleration, and to increase reliability. This paper analyzes and compares the characteristics of a tubular linear motor with Halbach and radial magnet array, respectively. First, the governing equations are established analytically in terms of the magnetic vector potential and two dimensional cylindrical coordinate systems. Then, we derive magnetic field solutions due to the PMs and the currents. Motor thrust, flux linkage and back emf are also derived. The results are shown to be in good conformity with those obtained from the commonly used finite element method. Finally, control parameters are obtained from analytical solutions.

• 한국철도학회:학술대회논문집
• /
• 한국철도학회 2006년도 추계학술대회 논문집
• /
• pp.742-747
• /
• 2006

This paper describes online stator-resistance estimation of a linear induction motor(LIM) with cage-type secondary using direct thrust control(DTC), where the resistance value is derived from stator-winding temperature estimation using thermocouple. In this paper, corrected stator resistance has an error in actuality measurement resistance. So compensation coefficient $\kappa$ which is decided through comparison and verifying several times relation of calculated resistance and measured motor line-line resistance. The stator-winding temperature information can also be used for monitoring, protection, and fault-tolerant control of the machine. Also, this paper reports the LIM's responses of the flux measured by the proposed stator resistance compensation algorithm.