• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
• /
• 2007.11a
• /
• pp.92-96
• /
• 2007

Microphone array beamforming method has been recognized as an important aeroacoustic research field and become a standard technique in localizing sound sources. This method also used in flight acoustic measurement, and especially, it is very useful when measure sounds inside the wind tunnel. In measuring sound which is inside the wind tunnel by traditional beamforming method, there are some errors caused by airstream. The speed and the propagation path of the sound changes as it travel through the airstream. This makes the error which the position of sound is changed a little bit to the down stream direction. In this paper, validation test has made about the correction equation for this wind effects of previous researches. And beamforming including shear layer correction was performed about a sound source in the anechoic open-jet windtunnel.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.10 no.1
• /
• pp.5-13
• /
• 2007

The trajectory of an current artillery munition is subject to a variety of different error sources resulting in more or less big deviation from the nominal predicted flight path. The 1D CCM(Course Correction Munition) has appeared to solve this problem and the mechanism of 1D CCM is a simple and low cost one using the influence of drag to range behavior of an artillery munition. In the paper 1D CCM concept has been simulated using wind tunnel experiment results of the specified Korean munition with CCF(Course Correction Fuze) and calculated the performance of its rang error reduction. From the simulated results it can be numerically explained that the possibility of adaptation of 1D CCM concept to Korean artillery munitions.

• Proceedings of the Korea Information Processing Society Conference
• /
• 2017.04a
• /
• pp.904-906
• /
• 2017

무인항공기(Unmanned Aerial Vehicle, UAV)는 조종사 없이 비행이 가능하고 고성능 카메라를 장착 가능함으로써 최근에는 이용하여 감시 및 정찰 자율화에 다양하게 활용되고 있다. 재난상황과 같은 급박하게 진행되는 상황에서 UAV가 비행하기 위한 그래프 기반 비행경로에서 비행하기 위한 비행경로를 계획하는 방법이 필요하다. 이 논문에서는 그래프 기반 비행경로에서 UAV가 감시 및 정찰을 시작하는 지점으로부터 감시 및 정찰하는 지점을 경유하며 도착지점까지 비행하기 위한 비행경로를 계획하는 방법을 제안한다. 실험에서는 그래프 기반 비행경로에서 조종사가 선택한 감시 및 정찰을 위한 지점을 거쳐가기 위한 비행경로를 계획한 결과를 검증한다.

• ETRI Journal
• /
• v.27 no.2
• /
• pp.172-180
• /
• 2005

Image resampling according to epipolar geometry is an important prerequisite for a variety of photogrammetric tasks. Established procedures for resampling frame images according to epipolar geometry are not suitable for scenes captured by line cameras. In this paper, the mathematical model describing epipolar lines in scenes captured by line cameras moving with constant velocity and attitude is established and analyzed. The choice of this trajectory is motivated by the fact that many line cameras can be assumed to follow such a flight path during the short duration of a scene capture (especially when considering space-borne imaging platforms). Experimental results from synthetic along-track and across-track stereo-scenes are presented. For these scenes, the deviations of the resulting epipolar lines from straightness, as the camera's angular field of view decreases, are quantified and presented.

• 제어로봇시스템학회:학술대회논문집
• /
• 2001.10a
• /
• pp.50.6-50
• /
• 2001

This paper deals with a design of nonlinear glide slope capture logic using dynamic model inversion in singular perturbation, which is applicable to the autolanding in ILS. Aircraft dynamics are separated into the fast time-scale variables, related with the inner-loop design, and the slow time-scale variables, related with the outer-loop design. It is assumed that the aircraft starts landing at 1000ft of altitude, -2.5deg of flight path angle, and 250ft/sec of velocity. In the outer-loop design, commands of altitude and velocity are selected and thereby the pseudo-controls of power level and pitch rate are determined. Also the elevator input to the aircraft is determined in the inner-loop design. The final design is evaluated in 6 DOF simulation model of the associated aircraft, in which the actuator models are not included. The results show the satisfactory autolanding ...

• Transactions of the Korean Society for Noise and Vibration Engineering
• /
• v.18 no.6
• /
• pp.612-618
• /
• 2008

Microphone array beamforming method has been recognized as an important aeroacoustic research field and become a standard technique in localizing sound sources. This method also used in flight acoustic measurement, and especially, it is very useful when measure sounds inside the wind tunnel. In measuring sound which is inside the wind tunnel by traditional beamforming method, there are some errors caused by airstream. The speed and the propagation path of the sound changes as it travel through the airstream. This makes the error which the position of sound is changed a little bit to the down stream direction. In this paper, validation test has made about the correction equation for this wind effects of previous researches. And beamforming including shear layer correction was performed about a sound source in the anechoic open-jet wind tunnel.

• Smart Structures and Systems
• /
• v.11 no.2
• /
• pp.185-197
• /
• 2013

We developed a simultaneous strain measurement and damage detection technique using a pair of surface-mounted piezoelectric transducers and a fiber connecting them. This is a novel sensor configuration of the fiber acoustic wave (FAW) piezoelectric transducer. In this study, lead-zirconate-titanate (PZT) transducers are installed conventionally on a plate's surface, which is a technique used in many structural health monitoring studies. However, our PZTs are also connected with an optical fiber. A FAW and Lamb wave are simultaneously guided in the optical fiber and the structure, respectively. The dependency of the time-of-flight of the FAW on the applied strain is quantified for strain sensing. In our experimental results, the FAW exhibited excellent linear behavior and no hysteresis with respect to the change in strain. On the other hand, the well-known damage detection function of the surface-mounted PZT transducers was still available by monitoring the waveform change in the conventional Lamb wave ultrasonic path.

• Proceedings of the Korean Society of Computer Information Conference
• /
• 2011.01a
• /
• pp.179-180
• /
• 2011

항공기의 비행경로 시각화는 저고도 임무나 지형고도에 대한 위협을 해소하기 위하여 널리 사용되는 시스템이다. 하지만, 시스템을 구성하기 위하여 GPS와 방대한 지리정보를 구축해야하는 제약으로 인하여 게임 등의 저가형 시스템에 사용되기에는 불가능하다. 본 논문에서는 비행경로를 경제적으로 시각화하기 위한 오픈소스 기반의 DMM(Digital Moving Map) 시스템을 제한한다. 먼저 X-Plane에서 UDP를 통하여 비행정보를 전달받아 구글어스에서 시연 및 지형고도 정보를 DMM 시스템에 전달한다. DMM 시스템에서는 비행체의 고도와 현 위치의 지형고도를 매핑하여 ArcGIS의 MapServer를 통해 가져온 지도 정보상에 비행경로를 시각화한다. 시간간격에 다른 지형고도와 비행체의 고도 비교를 위하여 별도의 모니터링 화면을 제공한다. 본 논문의 결과물은 게임 및 연구 등의 목적으로 비행경로를 시각화하는 분야에 경제적인 도구로 사용될 수 있을 것이다.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
• /
• 2000.06a
• /
• pp.65-70
• /
• 2000

Flying an aircraft is not like driving a train along a railway track. There are many factors that may affect an aircraft's course, including the wind speed and direction relative to the aircraft's intended flight path. This paper investigates noise exposed area by using INM. Especially, effect on aircraft route to minimise the number of people overflown by departing aircraft is evaluate. The result shows that track keeping scheme is effective to reduce the noise area. On the other track at 4000ft is negligible to the noise contour.

• Journal of Institute of Control, Robotics and Systems
• /
• v.20 no.4
• /
• pp.414-421
• /
• 2014

This paper presents a method of ballistic missile launch point estimation using phase division least squares. The proposed algorithm employs smoothing to enhance estimation accuracy and generates functions of time for total velocity, flight path angle and heading angle, allowing extrapolation to estimate the launch point. Performance of the proposed algorithm is tested in conjunction with the extended Kalman filter and the Kalman filter.