• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.187-194
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• 2008

Because the types and severities of most engine faults are various and complex, it is not easy that the conventional model based fault detection approach like the GPA(Gas Path Analysis) method can monitor all engine fault conditions. Therefore this study proposed newly a diagnostic algorithm for isolating and diagnosing effectively the faulted components of the smart UAV propulsion system, which has been developed by KARI(Korea Aerospace Research Institute), using the fuzzy logic and the neural network algorithms. A precise performance model should be needed to perform the model-based diagnostics. The based engine performance model was developed using SIMULINK. For the work and mass flow matching between components of the steady-state simulation, the state-flow library was applied. The proposed steady-state performance model can simulate off-design point performance at various flight conditions and part loads, and in order to evaluate the steady-state performance model their simulation results were compared with manufacturer's performance deck data. According to comparison results, it was confirm that the steady-state model well agreed with the deck data within 3% in all flight envelop. The diagnosis procedure of the proposed diagnostic system has the following steps. Firstly after obtaining database of fault patterns through performance simulation, then secondly the diagnostic system was trained by the FFBP networks. Thirdly after analyzing the trend of the measuring parameters due to fault patterns, then fourthly faulted components were isolated using the fuzzy logic. Finally magnitudes of the detected faults were obtained by the trained neural networks. Because the detected faults have almost same as degradation values of the implanted fault pattern, it was confirmed that the proposed diagnostic system can detect well the engine faults.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.330-339
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• 2008

Ground-based interceptors(GBI) comprise a major element of the strategic defense against hostile targets like Intercontinental Ballistic Missiles(ICBM) and reentry vehicles(RV) dispersed from them. An optimum design of the subsystems is required to increase the performance and reliability of these GBI. Propulsion subsystem design and optimization is the motivation for this effort. This paper describes an effort in which an entire GBI missile system, including a multi-stage solid rocket booster, is considered simultaneously in a Genetic Algorithm(GA) performance optimization process. Single goal, constrained optimization is performed. For specified payload and miss distance, time of flight, the most important component in the optimization process is the booster, for its takeoff weight, time of flight, or a combination of the two. The GBI is assumed to be a multistage missile that uses target location data provided by two ground based RF radar sensors and two low earth orbit(LEO) IR sensors. 3Dimensional model is developed for a multistage target with a boost phase acceleration profile that depends on total mass, propellant mass and the specific impulse in the gravity field. The monostatic radar cross section (RCS) data of a three stage ICBM is used. For preliminary design, GBI is assumed to have a fixed initial position from the target launch point and zero launch delay. GBI carries the Kill Vehicle(KV) to an optimal position in space to allow it to complete the intercept. The objective is to design and optimize the propulsion system for the GBI that will fulfill mission requirements and objectives. The KV weight and volume requirements are specified in the problem definition before the optimization is computed. We have considered only continuous design variables, while considering discrete variables as input. Though the number of stages should also be one of the design variables, however, in this paper it is fixed as three. The elite solution from GA is passed on to(Sequential Quadratic Programming) SQP as near optimal guess. The SQP then performs local convergence to identify the minimum mass of the GBI. The performance of the three staged GBI is validated using a ballistic missile intercept scenario modeled in Matlab/SIMULINK.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.2
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• pp.138-151
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• 2018

In this study, development information and technologies for reusable launch vehicles were surveyed. We investigated the reusable launch vehicles developed in various countries and analyzed their recovery technologies. In particular, we focus on the technologies of the Falcon 9 of SpaceX and the New Shepard of Blue Origin, which have succeeded in several flight experiments. Moreover, we explain the control algorithms for each flight condition. Finally, we discuss the reusable technologies that can be applied to the Korean Space Launch Vehicle to reduce the launch cost.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.5
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• pp.107-114
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• 2018

Korea Space Launch Vehicle (KSLV)-I flight test data and the modified 1-dimensional steady state modeling data from the critical design results of the KSLV-II liquid oxygen filling system operation are compared to validate the reliability of critical design modeling. A comparison of major flow rates and pressure values between test data and calculation results are conducted. The relative errors relative to maximum total flow rate for each cooling, filling, and replenishment mode are determined within 6.7%. Calculated pressure values at the outlet of the pump and the inlet of flow control valves are within 5.1%. The pressure at the inlet of the launch vehicle for each operation mode are within the measured pressure range.

• Journal of the Institute of Electronics Engineers of Korea SP
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• v.48 no.6
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• pp.8-17
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• 2011

Recently, fusion camera systems that consist of depth sensors and color cameras have been widely developed with the advent of a new type of sensor, time-of-flight (TOF) depth sensor. The physical limitation of depth sensors usually generates low resolution images compared to corresponding color images. Therefore, the pre-processing module, such as camera calibration, three dimensional warping, and hole filling, is necessary to generate the high resolution depth map that is placed in the image plane of the color image. However, the result of the pre-processing step is usually inaccurate due to errors from the camera calibration and the depth measurement. Therefore, in this paper, we present a depth map upsampling method robust these errors. First, the confidence of the measured depth value is estimated by the interrelation between the color image and the pre-upsampled depth map. Then, the detailed depth map can be generated by the modified kernel regression method which exclude depth values having low confidence. Our proposed algorithm guarantees the high quality result in the presence of the camera calibration errors. Experimental comparison with other data fusion techniques shows the superiority of our proposed method.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.04a
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• pp.18-18
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• 2000

In the high lift devices specifications for surface smoothness requirements, as manufacturing tolerances, arise out of aerodynamic consideration to minimize drag. True optimization of tolerances is a multi-disciplinary problem involving fluid mechanics, device performance, manufacturing philosophy and life cycle costing. One of the reasons for degradation of wetted surface is discrete roughness as a consequence of manufacturing defects, collectively termed as one of the excrescences effect. Usually, excrescence drag arising out of discrete roughness is of considerable lower order of magnitude as compared to the total drag of the flight bodies. Nor was there adequate predicting tool to account for the extent of drag degradation. Estimation of excrescence drag remained as a state-of-the art based on experimental results.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.355-358
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• 2005

Advances in scramjet technology over the past 40 years odd have been remarkable, involving dramatic advances in hypersonic flight-demonstrated technologies. Especially, it is noticeable that since 1990s the international activity in scramjet development has increased considerably Strong scramjet development capabilities in developed countries are being created through many ongoing research programs for a new generation of industrial and military capability. In this paper the current status of scramjet technology is identified through the investigation of scramjet development programs of each developed country.

• Journal of Korean Institute of Industrial Engineers
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• v.10 no.2
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• pp.3-16
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• 1984

This study develops a scientific method in pilot selection by analysing a divided attention performance between the successful pilots and the failures in a flight training course. To measure the divided attention performance, Dual Task Method is used in which the primary task is a tracking task while the secondary tasks are, 1. short term memory task, 2. choice reaction task and 3. judgement task. Result shows that the performance of the pilots is significantly better (P < 0.1) than that of the failures in dual performance. In addition, the differences in the divided attention performance between the two groups are increased in proportion to the difficulty of the task and especially in the Short Term Memory, the increment is most dramatic.

• Proceedings of the Korean Society of Broadcast Engineers Conference
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• 2016.06a
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• pp.329-331
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• 2016

일반적으로, 비행 표적의 궤적을 예측하기 위해 회귀분석이 사용되어왔다. 그러나 이 방법은 표적이 매우 다이내믹한 움직임을 보일 경우에는 오차가 크다는 한계가 있다. 이러한 문제를 해결하기 위해 본 논문에서는 다양한 수식을 생산해 내는 유전자 알고리즘을 이용하여 비행 표적의 다음 궤적을 예측해 내는 방법을 제안한다. 유전자 알고리즘을 통해 생산된 예측식을 토대로 비행 표적의 궤적을 3D 형태로 시각화 하였으며, 실제 관측 데이터와 예측된 데이터의 오차를 통해 정확도를 검증하였다.

• Proceedings of the Korean Society of Broadcast Engineers Conference
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• 2016.06a
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• pp.12-15
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• 2016

요즘 들어, 3차원 콘텐츠의 수요는 지속적으로 증가하고 있다. 3차원 콘텐츠의 품질은 해당 장면의 깊이 정보에 큰 영향을 받기 때문에 정확한 깊이 정보를 얻는 방법이 매우 중요하다. 깊이 정보를 얻는 방법은 크게 수동형 방식과 능동형 방식으로 나뉘는데, 수동형 방식은 계산 과정이 복잡하고 깊이맵의 품질이 보장되지 않는 단점을 갖기 때문에 능동형 방식이 많이 사용되고 있다. 능동형 방식은 깊이 카메라를 이용하여 직접적인 깊이 정보를 얻는 방식으로, 대게 ToF(Time-of-flight) 기술이 사용된다. 이 논문에서는 ToF 깊이 카메라로 촬영된 실제 깊이맵의 특성을 분석하기 위해 여러 가지 촬영 환경과 객체에 대해서 SR4000 깊이 카메라와 키넥트 v2 센서를 이용하여 깊이맵 품질을 비교했다. 실험 결과, 적외선이 제대로 반사되기 어려운 방사성 물질이나 표면, 경계 영역, 어두운 영역, 머리 영역 등에서 정확한 깊이 정보를 얻기 어려웠으며, 실외 환경에서 정확한 깊이 정보가 획득되지 않는 것을 확인할 수 있었다.