• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.2335-2339
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• 2003

To prevent the critical situation due to the fault in the aircraft sensor system, the fault tolerant system with triple or quadruple redundancy can be made. However, if the faults are occurred in two or more than sensors simultaneously, the conventional fault detection process, such as cross-channel monitoring, may give the wrong fault alarm. For this case, we can detect the fault by estimating the state vector based on the system dynamics model, which is nonlinear for aircraft. In this paper, we propose the unscented Kalman filter to estimate the nonlinear state vector. This filter utilizes the so-called unscented transformation of sigma points featured the statistical characteristics of the random variable. For verification, we perform the simulations for F-16 aircraft with accelerometers, gyros, GPS and air data system.

• 한국통신학회논문지
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• 제17권4호
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• pp.361-370
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• 1992

수직 이착륙기와 같은 비행체의 정지비행 도중 비행체의 위치각, 각속도, 각가속도와 같은 상태량을 궤환 시킨 SRFIMF(State Rate Feedback Implicit Model-Following)이론을 이용하여 4개의 팬을 갖는 부상제어시스템을 구성하였다. 이 부상제어시스템의 yaw제어를 행하여, 각 상태궤환이득 및 전향경로 이득을 변화시켜 부상제어시스템의 특정을 해석하였으며, 부상시스템과 같은 제어계에 SRFIMF방식을 적용시켜 그 타당성을 조사하였다.

• Nuclear Engineering and Technology
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• 제52권2호
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• pp.417-428
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• 2020

Investigations of the commercial aircraft impact effect on nuclear island infrastructures have been drawing extensive attention, and this paper aims to perform the safety assessment of Generation III nuclear power plant (NPP) buildings subjected to typical commercial aircrafts crash. At present Part III, the local damage of the rigid components of aircraft, e.g., engine and landing gear, impacting the steel concrete (SC) structures of NPP containment is mainly discussed. Two typical SC target panels with the thicknesses of 40 mm and 100 mm, as well as the steel cylindrical projectile with a mass of 2.15 kg and a diameter of 80 mm are fabricated. By using a large-caliber air gas gun, both the projectile penetration and perforation test are conducted, in which the striking velocities were ranged from 96 m/s to 157 m/s. The bulging velocity and the maximal deflection of rear steel plate, as well as penetration depth of projectile are derived, and the local deformation and failure modes of SC panels are assessed experimentally. Then, the commercial finite element program LS-DYNA is utilized to perform the numerical simulations, by comparisons with the experimental and simulated projectile impact process and SC panel damage, the numerical algorithm, constitutive models and the corresponding parameters are verified. The present work can provide helpful references for the evaluation of the local impact resistance of NPP buildings against the aircraft engine.

• Nuclear Engineering and Technology
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• 제50권8호
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• pp.1387-1401
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• 2018

An aircraft impact (AI) on a nuclear power plant (NPP) is considered to be a beyond-design-basis event that draws considerable attention in the nuclear field. As some NPPs have already adopted the seismic isolation technology, and there are relevant standards to guide the application of this technology in future NPPs, a new challenge is that nuclear power engineers have to determine a reasonable method for performing AI analysis of base-isolated NPPs. Hence, dynamic influences of the seismic isolation on the vibration and structural damage characteristics of the base-isolated CPR1000 containment are studied under various aircraft loads. Unlike the seismic case, the impact energy of AI is directly impacting on the superstructure. Under the coupled influence of the seismic isolation and the various AI load, the flexible isolation layer weakens the constraint function of the foundation on the superstructure, the results show that the seismic isolation bearings will produce a large horizontal deformation if the AI load is large enough, the acceleration response at the base-mat will also be significantly affected by the different horizontal stiffness of the isolation bearing. These concerns require consideration during the design of the seismic isolation system.

• Advances in aircraft and spacecraft science
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• 제7권6호
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• pp.495-516
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• 2020

Nonlinear state estimation is a desirable and required technique for many situations in engineering (e.g., aircraft/spacecraft tracking, space situational awareness, collision warning, radar tracking, etc.). Due to high standards on performance in these applications, in the last few decades, there was an increasing demand for methods that are able to provide more accurate results. However, because of the mathematical complexity introduced by the nonlinearities of the models, the nonlinear state estimation uses techniques that, in practice, are not so well-established which, leads to sub-optimal results. It is important to take into account that each method will have advantages and limitations when facing specific environments. The main objective of this paper is to provide a comprehensive overview and interpretation of the most well-known methods for nonlinear state estimation with Gaussian priors. In particular, the Kalman filtering methods: EKF (Extended Kalman Filter), UKF (Unscented Kalman Filter), CKF (Cubature Kalman Filter) and EnKF (Ensemble Kalman Filter) with an aerospace perspective.

• 항공우주정책ㆍ법학회지
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• 제32권1호
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• pp.201-224
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• 2017

이 논문은 공해상 군용기(또는 군용항공기)의 법적 지위에 관한 것으로 군용기의 법적 지위, 상공비행의 자유, 추적권, 임검권, 방공식별구역(ADIZ) 등을 다루었다. 1982년 UN해양법협약 제86조에 의하면 공해는 영해와 내수는 물론이고 접속수역, 배타적 경제수역이 아닌 수역을 의미하므로 기존의 공해였던 부분이 상당히 연안국관할권 하에 놓이게 되었다. 이와 같은 공해의 상공비행과 관련된 군용기의 법적 지위에 관한 사항으로 다음과 같은 결론을 얻을 수 있다. 첫째, 1944년 시카고 협약은 군용기의 법적 지위를 명시하고 있지 않은데 제3조(a)에서 본 협약이 민간항공기에만 적용되고 국가항공기에는 적용되지 않는다고 명시하고, 제3조 (b)에서 군용기, 세관용 항공기, 경찰용 항공기 등이 국가기관에 소속된 국가항공기로 간주된다고만 명시되어 있다. 따라서 현재 군용기의 법적 지위는 1919년 파리협약 제32조에 명시되었던 면책특권과 국제관습법에 의존하는 수밖에 없다. 한편 UN해양법협약 제95조는 공해상 군함의 면제권에 관하여 공해에 있는 군함은 기국외의 어떠한 국가의 관할권으로부터도 완전히 면제된다고 규정하고 있는데, 군용기의 경우도 군함에 준하는 면책권을 향유한다고 해석할 수 있다. 둘째, UN해양법협약 제111조는 추적권에 관하여 규정하고 있는데 이러한 추적권은 군함이나 군용기 또는 기타 정부역무에 종사함이 명백히 표시되고 식별되며 이에 대한 권한이 부여된 선박이나 항공기에 의해서만 행사되어질 수 있음을 명시하고 있으므로 선박 뿐 아니라 군용기에 의해서도 추적권이 행사될 수 있음을 규정하고 있다. 그러나 외국항공기에 대한 연안국의 공해상공의 추적권(right of aerial hot pursuit)이 국가관행이나 법적 확신(opinio juris)에 의해서 국제관습법 상 존재하는지는 확실하지 않다. 공해상공의 추적권 사례가 매우 적으므로 영공 이원의 외국항공기에 대한 이 권리가 국제관습법을 증명하는 '법으로 인정된 일반관행(general practice accepted as law)으로 존재한다고 할 수는 없다. 셋째, UN해양법협약 제110조는 임검권(right of approach)에 관하여 설명하고 있는데, 외국선박을 공해에서 만난 군함은 일정 혐의를 가지고 있다는 합리적 근거가 있는 한 그 선박을 임검하는 것은 정당화되는데, 이 규정은 정부 업무에 사용 중인 것으로 명백히 표시되어 식별이 가능하며 정당하게 권한이 부여된 모든 선박이나 항공기에도 적용된다. 따라서 이러한 규정은 군용기에도 준용된다고 할 수 있다. 넷째, 방공식별구역(ADIZ)은 자국 영공을 방위하기 위해 영공 외곽 배타적 경제수역(EEZ) 또는 공해 상공에 설정하는 공중 구역으로 국제법상 '자위권'(또는 정당방위, self defense)에 근거하여 일방적으로 선포되므로, 엄밀히 말하면 ADIZ를 설치할 규범도, 이를 금지할 수 있는 규범도 없고, 이를 규제하는 국제기구도 없다고 할 수 있다. 그러나 ADIZ가 영공의 확장으로 해석되지는 않는다.

• International Journal of Aeronautical and Space Sciences
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• 제16권3호
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• pp.425-436
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• 2015

This paper presents the procedures used for estimating the stability and control derivatives of a general aviation canard aircraft from flight data. The maximum likelihood estimation method which accounts for both process and measurement noise was used for the flight data analysis of a four seat canard aircraft, the Firefly. Without relying on the parameter estimation method, several aerodynamic derivatives were obtained by analyzing the steady state flight data. A wind tunnel test, a flight test of a 1/4 scaled remotely controlled model aircraft, and the prediction of aerodynamic coefficients using the USAF Stability and Control Digital Data Compendium (DATCOM), Advanced Aircraft Analysis (AAA), and Computer Fluid Dynamics (CFD) were performed during the development phase of the Firefly and the results were compared with flight determined derivatives of a full scaled flight prototype. A correlation between the results from each method could be used for the design of the canard aircraft as well as for building the aerodynamic database.

• Advances in aircraft and spacecraft science
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• 제7권6호
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• pp.553-570
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• 2020

To address the problems caused by the strong coupling of an airbreathing hypersonic vehicle's airframe and propulsion to the integrated control system design, an integrated airframe-propulsion model is established, and the coupling characteristics between the aircraft and engine are analyzed. First, the airframe-propulsion integration model is established based on the typical nonlinear longitudinal dynamical model of an air-breathing hypersonic vehicle and the one-dimensional dual-mode scramjet model. Thrust, moment, angle of attack, altitude, and velocity are used as transfer variables between the aircraft model and the engine model. The one-dimensional scramjet model can accurately reflect the working state of the engine and provide data to support the coupling analysis. Second, owing to the static instability of the aircraft model, the linear quadratic regulator (LQR) controller of the aircraft is designed to ensure attitude stability and height tracking. Finally, the coupling relationship between the aircraft and the engine is revealed through simulation examples. The interaction between vehicle attitude and engine working condition is analyzed, and the influence of vehicle attitude on engine safety is considered. When the engine is in a critical working state, the attitude change of the aircraft will not affect the engine safety without considering coupling, whereas when coupling is considered, the attitude change of the aircraft may cause the engine unstart, which demonstrates the significance of considering coupling characteristics.

• Advances in aircraft and spacecraft science
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• 제4권3호
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• pp.297-316
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• 2017

With rapid growth in the complexity of large scale engineering systems, the application of multidisciplinary analysis and design optimization (MDO) in the engineering design process has garnered much attention. MDO addresses the challenge of integrating several different disciplines into the design process. Primary challenges of MDO include computational expense and poor scalability. The introduction of a distributed, collaborative computational environment results in better utilization of available computational resources, reducing the time to solution, and enhancing scalability. SORCER, a Java-based network-centric computing platform, enables analyses and design studies in a distributed collaborative computing environment. Two different optimization algorithms widely used in multidisciplinary engineering design-VTDIRECT95 and QNSTOP-are implemented on a SORCER grid. VTDIRECT95, a Fortran 95 implementation of D. R. Jones' algorithm DIRECT, is a highly parallelizable derivative-free deterministic global optimization algorithm. QNSTOP is a parallel quasi-Newton algorithm for stochastic optimization problems. The purpose of integrating VTDIRECT95 and QNSTOP into the SORCER framework is to provide load balancing among computational resources, resulting in a dynamically scalable process. Further, the federated computing paradigm implemented by SORCER manages distributed services in real time, thereby significantly speeding up the design process. Part 1 covers SORCER and the algorithms, Part 2 presents results for aircraft panel design with curvilinear stiffeners.

• Advances in aircraft and spacecraft science
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• 제4권3호
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• pp.317-334
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• 2017

With rapid growth in the complexity of large scale engineering systems, the application of multidisciplinary analysis and design optimization (MDO) in the engineering design process has garnered much attention. MDO addresses the challenge of integrating several different disciplines into the design process. Primary challenges of MDO include computational expense and poor scalability. The introduction of a distributed, collaborative computational environment results in better utilization of available computational resources, reducing the time to solution, and enhancing scalability. SORCER, a Java-based network-centric computing platform, enables analyses and design studies in a distributed collaborative computing environment. Two different optimization algorithms widely used in multidisciplinary engineering design-VTDIRECT95 and QNSTOP-are implemented on a SORCER grid. VTDIRECT95, a Fortran 95 implementation of D. R. Jones' algorithm DIRECT, is a highly parallelizable derivative-free deterministic global optimization algorithm. QNSTOP is a parallel quasi-Newton algorithm for stochastic optimization problems. The purpose of integrating VTDIRECT95 and QNSTOP into the SORCER framework is to provide load balancing among computational resources, resulting in a dynamically scalable process. Further, the federated computing paradigm implemented by SORCER manages distributed services in real time, thereby significantly speeding up the design process. Part 1 covers SORCER and the algorithms, Part 2 presents results for aircraft panel design with curvilinear stiffeners.