• 산업기술연구
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• 제24권B호
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• pp.163-170
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• 2004

In this study, First, the results of travel-time inversion (first arrival inversion using the travel-time of the first arrival) were compared with those of full-wave inversion for numerical data. Numerical experiments to find key parameters other than initial velocity model showed that the frequency of source has a great effect on the result of full-wave inversion. Finally, this research presented the corrected full-wave inversion applying the correction term to the final result of full-wave inversion. The corrected full-wave inversion depicted cavities inside concretes even when the inversion started with 20% error in an initial velocity model for cavities. However, full-wave inversion did not reveal cavities.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1996년도 한국자동제어학술회의논문집(국내학술편); 포항공과대학교, 포항; 24-26 Oct. 1996
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• pp.1500-1503
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• 1996

This paper combines the disturbance accommodating control(DAC) and nonlinear model inversion control for a skid-to-turn(STT) missile. The missile autopilot may be designed to be robust with respect to a variety of uncertainties. We proposes the two step control design method. Nonlinear model inversion control is used as the main design method. Due to the model uncertainties and external disturbances, the exact nonlinear model inversion can not be achieved. DAC is designed to detect, to identify, and to compensate these uncertainties. DAC's disturbance observer is linear. Thus it is easy to implement. It does not cause the convergence problem due to coexistence between the modeling uncertainties and external disturbances. 6 DOF simulation results show that the proposed method may improve the missile tracking performance.

• 한국군사과학기술학회지
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• 제10권2호
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• pp.53-60
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• 2007

This paper presents a robust nonlinear autopilot design method based on dynamic inversion and PI(Proportional-Integral) control law. The new controller structure which is different from previous work is composed of classical linear PI control law and nonlinear fast dynamic inversion. A pitch axis model of highly maneuverable missiles and a linearized model for designing Pl controller are presented. The performance of proposed method is illustrated via nonlinear simulations including aerodynamic uncertainties and actuator dynamics.

• 한국항공우주학회지
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• 제35권11호
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• pp.990-998
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• 2007

불확실한 비선형 다중입출력 시스템에 대해서 신경회로망을 이용한 적응출력피드백제어기법이 제안되었다. 역변환 기반의 제어입력으로부터 불확실한 비선형성을 분리하기 위해 변형된 운동 역변환 모델(Modified Dynamic Inversion Model, MDIM)이 도입되었다. MDIM은 근사된 운동 역변환 모델과 역변환 모델 오차로 구성되었고 한 개의 신경회로망이 MDIM을 보상하는데 적용되었다. 여기서 신경회로망의 출력은 필터링된 근사오차 기반의 제어기를 증대시킨다. 추적성능과 종국적 유계성(ultimate boundedness)을 보장하기 위해 리야프노프의 직접방법(Lyapunov's direct method)으로부터 유도된 온라인 가중치 적응법칙이 이용되었다. 수치적 시뮬레이션을 통해 본 논문의 타당성을 검증하였다.

• 한국정보처리학회논문지
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• 제6권11호
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• pp.3131-3139
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• 1999

Satisfying the rigid timing requirements of various real-time activities in real-time systems often requires some special methods to tune the systems run-time behaviors. Unbounded blocking can be caused when a high priority activity cannot preempt a low priority activity. In such situation, it is said that a priority inversion has occurred. The priority inversion is one of the problems which may prevent threads from meeting the deadlines in the real-time systems. It is difficult to remove such priority inversion problems in the kernel at the same time to bound the worst case blocking time for the threads. A thread is a piece of executable code which has access to data and stack. In this paper, a new real-time systems. It is difficult to remove such priority inversion problems in the kernel at the same time to bound the worst case blocking time for the threads. A threads is a piece of executable code which has access to data and stack. In this paper, a new real-time server model, which minimizes the duration of priority inversion, is proposed to reduce the priority inversion problem. The proposed server model provides a framework for building a better server structure, which can not only minimize the duration of the priority inversion, but also reduce the deadline miss ratio of higher priority threads.

• 제어로봇시스템학회논문지
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• 제7권7호
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• pp.574-581
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• 2001

In this paper we design and evaluate the longitudinal nonlinear N(aub)z-CSAS(Command and Stability Augmentation System) flight control law in \"DMI(Dynamic Model Inversion)-method\" and classical \"Gain Scheduling-method\", respectively, to meet the handling quality requirements associated with push-over pull-up maneuver. It is told that the flight control law designed in \"DM-method\" is adequate to the full flight regime without gain scheduling and is efficient to produce the time response shape desired to the handling quality requirements. On the contrary, the flight control law designed in \"Gain Scheduling-method\" is easy to be implemented in flight control computer and insensitive to variation of the actuator model characteristics.n of the actuator model characteristics.

• 대한원격탐사학회지
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• 제24권5호
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• pp.427-436
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• 2008

This paper presents radar remote sensing of soil moisture and surface roughness for vegetated surfaces. A precise volume scattering model for a vegetated surface is derived based on the first-order radiative transfer technique. At first, the scattering mechanisms of the scattering model are analyzed for various conditions of the vegetation canopies. Then, the scattering model is simplified step by step for developing an appropriate inversion algorithm. For verifying the scattering model and the inversion algorithm, the polarimetric backscattering coefficients at 1.85 GHz, as well as the ground truth data, of a tall-grass field are measured for various soil moisture conditions. The genetic algorithm is employed in the inversion algorithm for retrieving soil moisture and surface roughness from the radar measurements. It is found that the scattering model agrees quite well with the measurements. It is also found that the retrieved soil moisture and surface roughness parameters agree well with the field-measured ground truth data.

• 지구물리와물리탐사
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• 제21권1호
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• pp.15-25
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• 2018

탄성파 역산은 유가스 집적이 가능한 구조의 탐지에 고해상도의 분해능을 가지는 반면, 인공송신원을 이용한 해양전자탐사 역산은 유가스의 직접적인 탐지가 가능하다. 이런 이종의 물리탐사자료를 함께 이용한 복합역산은 단일 역산의 불확실성을 줄일 수 있고, 각각의 탐사자료가 가지는 장점 또한 함께 이용할 수 있다. 이 연구에서는 암석물리모델을 이용하여 탄성파탐사자료와 전자탐사자료가 동시에 최적화 될 때의 저류층의 물성값을 추출할 수 있는 동시복합역산 알고리듬을 개발하였다. 상호구배(cross-gradient) 방법을 적용하여 구조적인 해상도를 향상시켰으며, 최대우도추정법을 이용한 상대 가중치를 적용하여 자료간의 균형을 조절하였다. 개발된 알고리듬을 단순한 고립 가스층 모델에 적용한 결과, 동시복합역산으로 고해상도의 저류층 물성 추출이 가능함을 확인하였다. 하지만 오일 저류층을 모사한 배사구조의 모델에서는 적용된 모델 가중 행렬에 따라 전혀 다른 결과를 획득할 수 있었다. 따라서, 기존의 알고리듬을 각각의 모델 변수에 적합한 모델 가중 행렬을 사용하도록 수정하여, 평활화 기법과 감쇠항 기법을 수포화율과 공극률에 각각 적용하였다. 개선된 알고리듬을 오일 저류층 모델에 다시 적용한 결과, 저류층의 공극률과 수포화율을 성공적으로 추출할 수 있었다. 개발한 복합역산 알고리듬을 이용하여 획득한 결과는 유가스전 저류층의 매장량 계산에 직접적인 정보로 사용될 수 있을 것이다.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2006년도 Proceedings of ISRS 2006 PORSEC Volume I
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• pp.224-227
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• 2006

For estimation of three inherent optical properties (IOPs), the absorption coefficients for phytoplankton ($a_{ph}$) and suspended solid particle ($a_{ss}$) and dissolved organic matter ($a_{dom}$), from ocean reflectance, we used inversion of remote sensing reflectance model (Ahn et al., 2001) at this study. The IOP inversion model assumes that (1) the relationship between remote sensing reflectance ($R_{rs}$) and absorption (a) and backscattering ($b_{b}$) is well known, (2) the optical coefficients for pure water ($a_{w}$, $b_{bw}$) are known, (3) the spectral shapes of the specific absorption coefficients for phytoplankton ($a^*_{ph}$) and suspended solid particle ($a^*_{ss}$) and the specific backscattering coefficients for phytoplankton ($b_b^*_{ph}$) and suspended solid particle ($b_b^*_{ss}$) are known. The input data of IOP inversion model is used in-situ ocean optical data at the seawater around the Korea Peninsula for 5 years (2001-2005). We compared the output data of the IOP inversion model and the in-situ observation for seawater around the Korea Peninsula.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1996년도 한국자동제어학술회의논문집(국내학술편); 포항공과대학교, 포항; 24-26 Oct. 1996
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• pp.1492-1495
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• 1996

In this paper, an approach to autopilot design based on the robust nonlinear dynamic inversion method is proposed. Both unknown parameters and uncertainty bounds are estimated and parameter estimates are used in the fast inversion. Furthermore, to get more robustness slow inversion is incorporated with MRAC(Model Reference Adaptive Control) and sliding mode control where the estimates of uncertainty bounds are used. The proposed method is applied to the pitch autopilot design of a missile system and excellent performance is shown via computer simulation.