• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.6
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• pp.516-525
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• 2015

In this paper, the acoustic pressure of a helicopter rotor in hovering and low speed descent flight is predicted and compared with experimental data. Ffowcs Williams-Hawkings equation is used to predict the acoustic pressure. Two different wind tunnel test data are used to validate the predicted results. Boeing 360 model rotor test results are used for the low-frequency noise in hover, and HART II test results are employed for the mid-frequency noise, especially BVI noise, in low speed descent flight. A simple free-wake model as well as the state-of-the-art CFD/CSD coupling method are adopted to perform the analysis. Numerical results show good agreement against the measured data for both low-frequency and mid-frequency harmonic noise signal. The noise carpet results predicted using the FFT(Fast Fourier Transform) shows also reasonable correlation with the measured data.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.12
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• pp.1173-1183
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• 2009

In order to reduce the download around the Smart UAV(SUAV) at hovering, flow control using synthetic jet has been performed. Many of the complex tilt rotor flow features are captured including the leading and trailing edge separation, and the large region of separated flow beneath the wing. In order to control the leading edge and trailing edge separation, synthetic jet is located at 0.01c, $0.3c_{flap}$, $0.95c_{flap}$. As non-dimensional frequency, the flow pattern is altered and the rate of drag reduction is changed. The results show that synthetic jets shorten the vortex period and decrease the vortex size by changing local flow structure. By using leading edge jet and trailing edge jet, download is efficiently reduced compared to no control case at hovering mode.

• Bulletin of the Korean Space Science Society
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• 2004.04a
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• pp.79-79
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• 2004

액체추진로켓 엔진의 추진제 공급 배관은 비행 중 비상상황에 따른 엔진 정지 및 비행종료 후의 엔진 정지 시에 밸브의 급격한 차단에 따라 수격현상이 발생한다. 따라서 추진제 공급배관 및 밸브는 이러한 압력에 견딜 수 있게 설계되어야 한다. 또한 무게를 줄여야 하기 때문에 정확한 최대압력을 예측하여 설계하는 것이 필요하다. 일반적으로 배관의 수격현상은 밸브의 개폐 시간에 가장 큰 영향을 받는 것으로 알려져 있다. (중략)

• Journal of Space Technology and Applications
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• v.2 no.2
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• pp.67-80
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• 2022

The missile early-warning satellite systems have been developed and upgraded by some space-developed nations, under the inevitable trend that the space is more strongly considered as another battle field than before. As the key function of such a satellite-based early warning system, the prediction algorithm of the missile flight trajectory is studied in the paper. In particular, the evolution computation, receiving broad attention in the artificial intelligence area, is applied to the proposed prediction method so that the global optimum-like solution is found avoiding disadvantage of the previous non-linear optimization search tools. Moreover, using the prediction simulator of the launch vehicle flight trajectory which is newly developed in C# and Python, the paper verifies the performance and the feature of the proposed algorithm.

• 한국항공운항학회:학술대회논문집
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• 2007.12a
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• pp.1-4
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• 2007

• Aerospace Engineering and Technology
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• v.11 no.2
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• pp.158-163
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• 2012

Spherical Flying Machine, unlike conventional aircraft structure, is protected by circular frame. This battery-operated propeller machine, which can do vertical take-off and hovering, is under development for indoor and outdoor operation and dubbed as Flying Ball in KARI. In the future, autonomous air vehicle will be constructed for reconnaissance and surveillance application.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.5
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• pp.413-422
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• 2012

The ducted fan for a small UAV propulsion can reconnoiter and observe in a town and a small area, it has better thrust efficiency and a long endurance than propeller. Thrust characteristics of hover and for ward flight condition for the ducted fan UAV is important issue to improve a endurance. The unsteady 3-dimensional flow fields of the ducted fan UAV is essential to stable flight. In this paper, to verify the design results of the ducted fan and to investigate a stable aeronautical characteristic, the thrust performance and the unsteady 3-dimensional flow fields are measured. Thrust characteristics for the hovering and the forward flight conditions are measured by the 6-components balance system in the subsonic wind tunnel. The unsteady 3-dimensional flow fields are analyzed by using a stationary $45^{\circ}$ slanted hot-wire technique. The swirl velocity is almost removed behind the stator blades. Therefore, the thrust performance of the ducted fan is improved and the flight stability is maintained.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.3
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• pp.243-250
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• 2012

In this paper, a systematic consequence of evaluation method, procedure, and flight data analysis is investigated for application of ADS-33E-PRF to UAV. And it is applied to unmanned rotorcraft for evaluation. CNUHELI-020, which is developed in Chungnam National University, is used for assessment of handling quality: decoupled longitudinal and lateral/directional model were used to assess handling qualities. Evaluation flight maneuvers are categorized as hover/low-speed requirements, small-amplitude attitude change, and moderate-amplitude attitude change requirements.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.21 no.1
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• pp.90-96
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• 2020

In this era, intelligence is considered a major factor in the defense sector. As a result, securing technology for weapons systems for monitoring and reconnaissance of companies has become inevitable. As a result, UAVs (Unmanned Aerial Vehicles) have been developed and are actively operating around the world if the flight operation of manned aircraft is restricted, such as in environments that are too dangerous, messy or boring for the military to perform directly. The system of unmanned aerial vehicles, which has been researched and developed in Korea, includes Air Vehicle Test Equipment(AVTE). AVTE is equipment that is connected to an UAV to check its status and allows the operator to check its flightability by issuing an operational command to the UAV and verifying that it follows the command values. This study conducts fault finding on the phenomenon where the AVTE has stopped operating due to engine noise during these operations and analyzes the cause in terms of software, hardware and external environment. Present improvement measures according to the cause are analyzed and the results of verifying that the proposed measures can prevent failure are addressed.

• Proceedings of the Korean Information Science Society Conference
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• 2007.10b
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• pp.172-177
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• 2007

공중공간은 평면에 비해 넓고 많은 항공기들이 고속으로 비행하고 있다. 더불어 항공사고는 바로 대형사고로 이어지므로 공중상황 통제의 중요성은 항상 강조되고 있다. 그러나 항공기는 3차원 공간에서 복잡한 패턴으로 비행하기 때문에 통제하기가 매우 어렵다. 통제를 위한 공중상황 정보는 시각화 시스템을 통해 제공되고 있으나, 이를 운영하는 통제요원의 경험, 인지능력이 공중상황판단의 결정적 역할을 하고 있다. 그래서 정확한 상황판단을 위한 정보제공이 매우 중요하다. 본 논문에서는 공중상황에 대한 정확한 정보제공을 위해 비행경로를 이용한 시각화 기법을 제안한다. 대부분의 항공기는 정지하지 않고, 급격한 상태전이 없이 이동하므로 과거 비행자료를 통해 미래의 비행상태를 예측할 수 있다. 즉 과거 상태정보와 현재 상황정보를 통합하여 시각화하면 비행패턴을 예측할 수 있어 정확한 공중상황 판단이 가능하다. 이를 위해 실시간 자료를 분석하여 동적자료를 구분한다. 동적자료만으로 상태전이자료를 생성하고 비행경로 상에서 색상과 도형 및 기호화를 통해 시각화한다. 비행경로와 색상 및 기호화로 제공된 상태전이 시각화 정보는 항공기의 상승/하강, 가속/감속, 직진/선회, 기타 상태전이정보와 바람의 방향과 같은 공중 공간의 상황정보 둥을 제공할 것이다. 이를 통해 운용요원은 공중상황을 정확히 인식하고 신속하게 판다하여 통제함으로서 공중안전을 도모하고 통제업무를 효과적으로 수행할 수 있을 것이다.