• International Journal of Aeronautical and Space Sciences
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• 제18권1호
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• pp.99-107
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• 2017

In this work, the nutation control of rigid spacecraft with only two momentum wheels is addressed by applying the feedback linearization technique. In this strategy, the primary performance index is to regulate the nutational angle by the momentum control of wheels. The spacecraft attitude equations of motion are transformed to a general linearized form by feedback linearization technique, including a guaranteed control law promising the internal dynamics stability to accomplish the nutation angle small. It is proven that the configuration of inertia properties plays a key role in analyzing spacecraft energy level. The behavior of the momentum wheels is also studied analytically and numerically. Finally, the effectiveness of the proposed nonlinear control law for the momentum transfer is verified by conducting numerical simulations.

• 한국분무공학회지
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• 제27권4호
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• pp.181-187
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• 2022

For carbon neutrality, direct-injection hydrogen engines are attracting attention as a future power source. It is essential to estimate the transient injection rate of hydrogen for the optimization of hydrogen injection in direct injection engines. However, conventional injection rate measurement techniques for liquid fuels based on the injection-induced fuel pressure change in a test section are difficult to be applied to gaseous fuels due to the compressibility of the gas and the sealing issue of the components. In this study, a momentum flux measurement technique is introduced to obtain the transient injection rate of gaseous fuels using a force sensor. The injection rate calculation models associated with the momentum flux measurement technique are presented first. Then, the volumetric injection rates are estimated based on the momentum flux data and the calculation models and compared with those measured by a volumetric flow rate meter. The results showed that the momentum flux measurement can detect the injection start and end timings and the transient and steady regimes of the fuel injection. However, the estimated volumetric injection rates showed a large difference from the measured injection rates. An alternative method is suggested that corrects the estimated injection rate results based on the measured mean volumetric flow rates.

• 한국운동역학회지
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• 제18권4호
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• pp.201-207
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• 2008

본 연구는 2003년 대구 유니버시아드 대회의 도마 경기에서 Roche 기술 동작을 실시한 세 명의 남자체조선수를 대상으로 연구되어진 결과(2005, 여홍철)를 운동역학적 분석으로 재검토하여 경기력 향상에 기여하고자 하는데 목적이 있다. 각 단계별 각운동량 결과에서는 도마 접촉시 반시계 방향으로 각운동량이 클수록 제2비약 즉 peak시 회전력을 방해하는 요인으로 나타났다. 가장 큰 신체각을 나타낸 국면은 VTD이며 가장 작은 신체각은 BTO 국면으로 나타났으며 도마 접촉 국면과 이륙 국면에서 개인차가 가장 큰 것으로 나타났다. Roche 기술은 앞으로 체공 높이도 중요하지만 앞으로 회전력을 빠르게 증가시켜야 하므로 투사각이 쿠에르보 비틀기 기술보다 작게 나타났으며 각속도 결과에서는 제 2비약에서 앞공중돌기 2회전 동작을 진행하고 있는 peak가 가장 큰 각속도를 나타내고 있다. 이러한 결과에 영향을 미치는 국면은 BTO부터 VTO 국면으로 각속도의 결과로 인해 각운동량에 영향을 미치는 것으로 사료된다.

• International Journal of Aeronautical and Space Sciences
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• 제3권2호
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• pp.13-23
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• 2002

In this paper, we present a sliding mode control strategy for the re-orientation maneuver of rigid spacecraft containing rotating wheels. The wheels are considered as internal devices, and external inputs are employed for generation of control commands. The formulation is developed for a general case while particular example is applied to pitch bias momentum spacecraft with a single momentum wheel. The resultant control commands are used to take the gyroscopic effects into account which are caused by the rotating wheels. The controller designed demonstrates that the nutational motion of the pitch bias momentum spacecraft is effectively controlled. It is also assumed that the external control torque device is of on-off nature, and pulse width modulation technique is applied to construct proper control torque history.

• 한국항공우주학회지
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• 제33권9호
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• pp.81-88
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• 2005

본 논문은 단일 태양전지판으로 구성된 통신해양기상위성(COMS)에 대하여 모멘텀 덤핑에 소요되는 연료량을 분석하였다. 먼저 하루 중 일정한 시간에 모멘텀 덤핑을 수행할 경우를 가정하여 최적의 시간을 선정하는 작업을 수치해석적인 접근을 통하여 수행하였고 요구되는 연료량을 분석하였다. 또한 모멘텀 덤핑에 소요되는 연료량을 절감하기 위하여 남북위치유지 시점과 모멘텀 덤핑시점을 근사적으로 일치시키는 방안을 제안하였다. 마지막으로 제안된 기법의 유효성을 분석하기 위하여 궤도 시뮬레이션을 수행하였다.

• 한국운동역학회지
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• 제26권1호
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• pp.51-69
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• 2016

Objective: The purpose of this study is to suggest new terminology for the ninety-five hand techniques based on the significance of their angular momentum, determined by analyzing each technique's influence or impact on the compartmentalized angular momentum of the trunk, upper arm, and forearm in the Taekwondo Poomsae. Method: An athlete who won the 2014 World Taekwondo Poomsae championship was selected and agreed to participate in the data collection phase of our investigation. The video data was collected using eight infrared cameras (Oqus 300, Qualysis, Sweden) and the Qualisys Track Manager software (Qualisys, Sweden). The angular momentum of each movement was then calculated using the Matlab R2009a software (The Mathworks, Inc., USA). Results: The classification of the ninety-five hand techniques in the Taekwondo Poomsae based on the significance of each segment's momentum is as follows. Makgi (blocking) is classified into fourteen categories, jireugi (punching) is classified into three categories, chigi (hitting) was classified into six categories, palgupchigi (elbow hitting) was classified into four categories, and jjireugi (thrusting) was classified two categories. Conclusion: This study offers a new approach, based on a biomechanical method, to the classification of the hand techniques that reflect kinesthetic motions in the Taekwondo Poomsae.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2008년도 학술대회
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• pp.27-32
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• 2008

In the present study, a conservative overset mesh technique has been developed on 2-D unstructured meshes. A new domain connection technique between independent mesh blocks was proposed to satisfy the conservation of mass, momentum, or energy in entire computational domain. The present technique was applied to several classical computational problems to validate the superiority of the conservative method to the non-conservative method.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2008년 추계학술대회논문집
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• pp.27-32
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• 2008

In the present study, a conservative overset mesh technique has been developed on 2-D unstructured meshes. A new domain connection technique between independent mesh blocks was proposed to satisfy the conservation of mass, momentum, or energy in entire computational domain. The present technique was applied to several classical computational problems to validate the superiority of the conservative method to the non-conservative method.

• 대한기계학회논문집B
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• 제28권6호
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• pp.619-627
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• 2004

In most industrial applications, the geometrical complexity is combined with the moving boundaries. These problems considerably increase the computational difficulties since they require, respectively, regeneration and deformation of the grid. As a result, engineering flow simulation is restricted. In order to solve this kind of problems the immersed boundary method was developed. In this study, the immersed boundary method is applied to the numerical simulation of stationary, rotating and oscillating cylinders in the 2-dimensional square cavity. No-slip velocity boundary conditions are given by imposing feedback forcing term to the momentum equation. Besides, this technique is used with a second-order accurate interpolation scheme in order to improve the accuracy of flow near the immersed boundaries. The governing equations for the mass and momentum using the immersed boundary method are discretized on the non-staggered grid by using the finite volume method. The results agree well with previous numerical and experimental results. This study presents the possibility of the immersed boundary method to apply to the complex flow experienced in the industrial applications. The usefulness of this method will be confirmed when we solve the complex geometries and moving bodies.

• 한국추진공학회지
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• 제10권1호
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• pp.54-63
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• 2006

이젝터는 고속의 주 유동으로 주변의 낮은 운동량을 가지는 유동을 운동량 교환을 통해 압축시켜 수송하는 장치로서 각종 초음속 시험설비의 마하 4, 고도 20 km 이상의 고고도 조건을 모사하기 위한 목적으로 사용될 수 있다. 항공우주연구원에서는 램제트 엔진 시험설비의 마하 $4\sim5$, 고도 $20\sim25km$의 작동조건을 모사하기 위한 이젝터를 설계하기 위하여 일본 항공우주연구소(JAXA)의 램제트/스크램 제트 엔진 시험설비(RJTF)의 공기 이젝터 성능해석 기법 및 설계 기법을 적용하여 기본 설계를 수행하였다. 또한 설계된 이젝터 형상을 토대로 FLUENT를 이용한 수치해석을 수행하여 이젝터 시스템 내부의 충격파 구조와 고고도 조건 모사를 위한 흡입 압력 값 및 시스템 내에서 냉각이 요구되는 영역을 파악하고 기본 설계 과정 결과의 타당성을 검증하였다.