Shroud의 영향에 따른 제트 베인의 공기역학적 특성 연구

박순종(Soonjong Park),박종호(Jongho Park) 한국추진공학회 2012 한국추진공학회지 Vol.16 No.2

Thrust vector control system is a control device which is mounted on the exit of the nozzle to generate pitch, yaw and roll directional force by deflecting flow direction of the supersonic jet from the nozzle. Thermal and aerodynamic loads are acting on the surface of jet vane when it is exposed to the jet flow. Axial thrust loss and side thrust loss are affected by shock patterns and interactions between jet-vanes which varies with jet-vane geometry and turning angle. In this research, the performance estimation using the numerical simulation analysis of the nozzle is given and the investigation of the flow visualization and aerodynamic performance with the enforced power to the vane is taken.

제트베인을 이용한 시스템 모델링 및 자세제어기법 연구

문관영,전병을,김성준 한국항공우주학회 2012 한국항공우주학회 학술발표회 논문집 Vol.2012 No.4

스텔스 성능을 극대화하기 위해 최근 함정에 탑재되는 유도탄은 수직 발사관을 이용하는 경우가 많다. 아함에 접근하는 적 유도탄으로부터 아함을 방어하기 위해서는 이륙 직후 급속한 자세 변화가 요구되지만, 유도탄의 속도가 충분히 증가되지 않은 경우 공력 제어만을 통해 이러한 요구조건을 달성하기 어렵다. 본 연구에서는 이를 극복하기 위한 제트베인(Jet vane)을 이용한 자세제어기에 대해 고찰한다. 공력과 추력에 의한 시스템 특성을 살펴보고, 각각의 모델링을 통해 제트베인 시스템을 인식하고 3-Loop 알고리듬을 이용하여 제어기를 구성하였다. 구성된 자세제어시스템의 타당성을 검증하기 위해 수치 시뮬레이션을 수행하였다. To increase the stealth capability, currently developed missile carried by ship uses the vertical launcher. Therefore, the rapid attitude control scheme is required to cope with the threat to the friendly ship. However in the initial phase of missile, the velocity is not fully build up, so the aerodynamic force is not enough to achieve the goal. In this study, the attitude control loop using the jet-vane is considered. The system modeling includes the jet-vane system as well as the aerodynamic force. The Classical 3-loop algorithm is adopted to design the attitude loop. Numerical simulation is performed to check the validity of proposed algorithm.

Shroud로 둘러싸인 제트베인 삭마에 따른 유동 특성

박지용(Jee-Yong Park),윤웅섭(Woong-Sup Yoon) 한국추진공학회 2012 한국추진공학회 학술대회논문집 Vol.2012 No.11

It is very difficult to predict the characteristics of thrust vector control for jet vane wrapped with shroud due to shock wave and expansion wave generated by each vane. Therefore, the current study investigated how vane, vase, shroud and nozzle effects the characteristics of side force and thrust force. In addition, ablation tendency of vane was predicted for modeling and transition tendency of side force and thrust force was examined according to ablation rate increase. Fluid flow analysis program(Fluent) was used to interpret what effects shroud wrapped jet vane has on control characteristics.

Shroud를 포함한 제트베인의 공기역학적 특성 연구

박순종(Soon-Jong Park),김경련(Kyoung-Rean Kim),박종호(Jong-Ho Park) 대한기계학회 2007 대한기계학회 춘추학술대회 Vol.2007 No.5

The performance study shows the result using two different methods which are used to control missile or aircraft. One is the Thrust Vector Control(TVC) method for the aviation of next generation and the other is the present effective Shroud Jet-vane System(SJVS) method for the satellite effector development. The research was done through the performance estimation using the numerical simulation analysis, the modelling, the performance measuring using the model, the investigation of the flow visualization and aerodynamic performance with the enforced power to the vane and the result comparison.

Analysis of the Influence of Guide Vane Wrap Angle and Number of Blades on the Propulsion Performance of a Water-Jet Propeller

Wei Han,JianDong Mi,SiCong Zhang,Jun Xu,BinYu Qin 한국유체기계학회 2021 International journal of fluid machinery and syste Vol.14 No.4

For water-jet propellers, the geometry size of the guide vane change can effectively improve the performance of the pump. If other parameters remain unchanged, CFD numerical simulation of the guide vane number and wrap angle of the change can be used to effectively adjust the operation conditions of the pump. The relationship between the changes in pump head, pump efficiency, and water-jet propeller propulsive efficiency can be used, to find the best guide vane parameters to achieve the highest thrust efficiency. The calculation results show that an increase in the guide vane number coefficient and wrap angle coefficient will reduce size of the pump head. Meanwhile, an increase in the wrap angle coefficient and the guide vane number coefficient will reduce the propulsive efficiency of the whole water-jet propeller. In this experiment, it was found that the propulsion effect is best when the guide vane number coefficient remains unchanged and the wrap angle coefficient is 1.

추력방향조종용 제트베인의 3차원 온도분포 해석

황기영(Ki-Young Hwang) 한국추진공학회 2011 한국추진공학회 학술대회논문집 Vol.2011 No.11

수직발사 추진기관의 추력방향조종(TVC)용으로 사용되는 제트베인 조립체의 열전달 특성을 고찰하기 위해 수치해석을 수행하였다. 본 연구에서 제트베인 주위의 대류열전달계수는 열경계층 방정식의 해와 반실험식을 사용하여 구하였다. 제트베인 조립체의 3차원 온도분포에 대한 해석은 PATRAN과 ABAQUS 소프트웨어를 사용하여 수행되었다. 본 수치해석 기법의 타당성은 제트베인 축 내부에서 측정한 온도와 열해석 결과의 비교를 통해 검증하였다. 제트베인의 3개 편향각(0o, 12.5o, 25o)에 대해 연소시간별 제트베인의 온도변화를 고찰하였다. A computational investigation has been carried out to study the heat transfer characteristics of jet vane assembly used for the thrust vector control(TVC) of a vertical launch motor. In this study, the coefficients of convective heat transfer on the jet vane are calculated using the solutions of thermal boundary-layer equation and several semi-empirical equations. The calculation of 3-dimensional temperature distribution for the jet vane assembly was performed using the softwares called PATRAN and ABAQUS. The accuracy of the present numerical method is verified by comparing with the measured and calculated temperatures within jet vane shaft. The temporal variation of jet vane temperatures for three deflection angles(0o, 12.5o, 25o) was discussed.

공력과 추력방향 동시 제어가 가능한 전기식 구동장치 설계

이하준(Ha Jun Lee),윤기원(Kiwon Yoon),송인성(In Seong Song),박창규(Chang Kyoo Park),이영철(Young Cheol Lee) 한국항공우주학회 2020 韓國航空宇宙學會誌 Vol.48 No.1

비행체용 전기식 구동장치는 일반적으로 공력비행 조종날개의 편향각 또는 추력방향을 제어하는 장치로 본 논문은 공력제어와 추력방향 제어가 모두 가능한 전기식 구동장치의 설계 및 개발을 다루고 있다. 본 논문에서는 하나의 작동기로 미익과 제트 베인을 동시에 제어할 수 있고, 비행체의 표적까지 비행동안 효율을 증가시키기 위하여 수직 발사 및 고속 선회 후 제트 베인을 분리할 수 있는 새로운 소형 전기식 구동장치를 제안하였다. 이를 위하여, 푸시-푸시 링크 구조를 사용한 전기식 구동장치를 설계하였고 수학적 모델을 유도하였다. 수학적 모델은 시뮬레이션 결과와 실험결과를 비교하여 모델의 타당성을 검증하였다. 개발된 구동장치의 성능 및 신뢰성은 성능시험, 환경시험, 지상연소시험을 통하여 검증하였다. 제안된 구동장치는 성능 및 신뢰성 뿐만 아니라 단순하고 콤팩트한 구조로 인해 비행체용 전기식 구동장치로 유용할 것으로 기대된다. Electromechanical Actuator(EMA) for flight vehicles generally serves to control the fin deflection angle or the thrust vector angle. This paper deals with design and development of EMA for both aerodynamic control and thrust vector control. In this paper, a novel compact EMA is proposed that can simultaneously control both the tail fin and the jet vane with one actuator and detach the jet vane after vertical launch and rapid turn of the flight vehicle so as to increase efficiency during flying to target. To do this, we designed the EMA using a push-push link mechanism and derived a mathematical model. The mathematical model is validated by comparing simulation result and experimental data. The performance and reliability of the proposed EMA have been verified through performance test, environmental test and ground test. The proposed EMA is expected to be useful as an EMA for flight vehicles because of its simple and compact structure, as well as its performance and reliability.

Numerical investigation of an add-on thrust vector control kit

AbuElkhier, Mohamed G.,Shaaban, Sameh,Ahmed, Mahmoud Y.M. Techno-Press 2022 Advances in aircraft and spacecraft science Vol.9 No.1

Instead of developing new guided missiles, converting unguided missile into guided ones by adding guidance and controlkits hasbecome aglobaltrend.Ofthemost efficient andwidelyused thrust vector control(TVC) techniquesin rocketry isthe jet vanes placed inside the nozzle divergentsection. Upon deflecting them, lift created on the vanesistransferred to the rocket generating the desired control moment. The presentstudy examinesthe concept of using an add-on jet vaneTVC kit to a plain nozzle.The impact of adding the kit with different vaneslocations and deflectionanglesisnumericallyinvestigatedbysimulatingtheflowthroughthenozzlewiththekit.Twohingelocations are examined namely, at 24% and 36% of nozzle exit diameter. For each location, angles of deflection namely 0°, 5°, 10°, and 15° are examined. Focus is made on variation of control force, thrust losses, lift and drag on vanes, jet inclination, and jetflow structure withTVCkit design parameters.

Numerical investigation of an add-on thrust vector control kit

AbuElkhier, Mohamed G.,Shaaban, Sameh,Ahmed, Mahmoud Y.M. Techno-Press 2022 Advances in aircraft and spacecraft science Vol.9 No.1

Instead of developing new guided missiles, converting unguided missile into guided ones by adding guidance and controlkits hasbecome aglobaltrend.Ofthemost efficient andwidelyused thrust vector control(TVC) techniquesin rocketry isthe jet vanes placed inside the nozzle divergentsection. Upon deflecting them, lift created on the vanesistransferred to the rocket generating the desired control moment. The presentstudy examinesthe concept of using an add-on jet vaneTVC kit to a plain nozzle.The impact of adding the kit with different vaneslocations and deflectionanglesisnumericallyinvestigatedbysimulatingtheflowthroughthenozzlewiththekit.Twohingelocations are examined namely, at 24% and 36% of nozzle exit diameter. For each location, angles of deflection namely 0°, 5°, 10°, and 15° are examined. Focus is made on variation of control force, thrust losses, lift and drag on vanes, jet inclination, and jetflow structure withTVCkit design parameters.

로켓노즐에 장착된 제트베인 표면의 열전달 특성

유만선(Man Sun Yu),조형희(Hyung Hee Cho),황기영(Ki Young Hwang),배주찬(Ju Chan Bae) 한국추진공학회 2005 한국추진공학회지 Vol.9 No.1