• 제어로봇시스템학회:학술대회논문집
• /
• 제어로봇시스템학회 2000년도 제15차 학술회의논문집
• /
• pp.54-54
• /
• 2000

For its synergistic relationship, an integrated SDINS/GPS system has been adopted in many navigation areas. As an application of SDINS/GPS integration, the in-flight alignment process of a SDINS utilizing GPS carrier phase measurements is introduced and analyzed via an observability analysis using nul1 space method. A measurement model of double-differenced GPS carrier phase measurements is newly derived in order to be used with a SDINS error model. Also, conditions for determining the complete observability of a SDINS/GPS system are suggested and proved. Consequently, it is shown that the system is not completely observable in case of one basel me. With one baseline aligned with y-axis of body frame, pitch error and x-axis accelerometer bias are unobservable states. Also shown is that al1 states are completely observable when sequential maneuver is performed. Above results are confirmed by a covariance analysis.

• 제어로봇시스템학회논문지
• /
• 제7권8호
• /
• pp.703-710
• /
• 2001

The nonlinear observers are proposed for a nonlinear system. To improve the characteristics such as stability, convergence, and $H^{\infty}$ filter performance criterion, we utilize an $H^{\infty}$ filter Riccati equation or a modified $H^{\infty}$ filter Riccati equation with a freedom parameter. Using the Lyapunov function method, the characteristics of the observers are analyzed. Then the in-flight alignment for a strapdown inertial navigation system(SDINS) is designed using the proposed observer. And the additive quaternion error model is especially used to reduce the uncertainty of the SDINS error model. Simulation results show that the observer with the modified $H^{\infty}$ filter Riccati equation effectively improves the performance of the in-flight alignment.

• 천문학회보
• /
• 제44권2호
• /
• pp.57.1-57.1
• /
• 2019

NASA and Korea Astronomy and Space Science Institute (KASI) have been collaborated to develop the Space solar coronagraph instrument to detect the solar wind speed and corona temperature. As an intermediate stage, BITSE is the Balloon-Borne instrument to prove our proposed technical method which uses a polarized light in 4 different bandwidth wavelengths. In the presentation, the optical design based on the requirements, tests and alignment process for integrating the system are discussed.

• 정보처리학회논문지:소프트웨어 및 데이터공학
• /
• 제3권12호
• /
• pp.523-530
• /
• 2014

온톨로지 정렬의 목적은 지식을 공유 및 재사용 하는 데 있다. 기존 온톨로지 정렬 시스템은 온톨로지 개념의 모호성 때문에 여러 가지 다양한 측정 기법을 사용하고 전수조사를 수행하여 사용자가 만족하는 결과를 얻는다. 온톨로지 개념이 점차 많아짐에 따라 계산이 복잡해지고 걸리는 시간이 기하급수적으로 증가하여 처리 과정에서 오류가 발생한다. 이를 해결하기 위하여 메타 휴리스틱 알고리즘을 사용하는 메타 매칭이 연구되고 있다. 기존 메타 매칭 시스템에서는 사용하는 파라미터가 많기 때문에 온톨로지 정렬 처리에 계산이 복잡하고 특정 도메인의 다양한 데이터에 따라 조율이 요구되어 온톨로지 정렬 탐색에 좋은 성능을 보여주지 못했다. 이 논문에서는 온톨로지 정렬을 쉽고 간단한 계산을 통해 높은 성능을 목표로 하여 DCS(Discrete Cuckoo Search) 를 사용한 온톨로지 정렬 알고리즘을 제안한다. 제안한 알고리즘은 Levy Flight 분포에 따른 탐색으로 효율적인 전략을 보여준다. 제안된 알고리즘은 OAEI 2012(Ontology Alignment Evaluation Initiative)에서 제공하는 벤치마크 데이터와 제안 알고리즘을 사용하여 성능을 평가한다.

• International Journal of Aeronautical and Space Sciences
• /
• 제11권3호
• /
• pp.184-192
• /
• 2010

In this paper, an initial fine alignment algorithm, which is developed for the strap-down inertial navigation systems of satellite launch vehicles, is considered. For fast and accurate alignment, a simple closed-loop estimation algorithm using a proportional-integral controller is introduced. Through computer simulation for the sway condition in the launch pad, it is shown that a simple filter structure can guarantee fast computational speed that is adequate for real-time implementation as well as the required alignment accuracy and robustness. In addition, its implementation results are presented for the Naro-1 flight test.

• International Journal of Control, Automation, and Systems
• /
• 제1권4호
• /
• pp.520-526
• /
• 2003

In the case of a strapdown inertial navigation system (SDINS) with sizeable attitude errors, the uncertainty caused by linearization of the system degrades the performance of the filter. In this paper, a robust filter and various error models for the uncertainty are presented. The analytical characteristics of the proposed filter are also investigated. The results show that the filter does not require the statistical property of the system disturbance and that the region of the estimation error depends on a freedom parameter in the worst case. Then, the uncertainty of the SDINS is derived. Depending on the choice of the reference frame and the attitude error state, several error models are presented. Finally, various in-flight alignment methods are proposed by combining the robust filter with the error models. Simulation results demonstrate that the proposed filter effectively improves the performance.

• 정보통신설비학회논문지
• /
• 제4권1호
• /
• pp.1-6
• /
• 2005

As an application of the GPS/SDINS integration for its synergistic results, the alignments of the SDINS utilizing GPS carrier phase rate measurements is introduced. A measurement model of GPS carrier phase rate, which does not require integer ambiguity determination process, is newly derived in order to be adopted with the SDINS in-flight alignment process. For in-flight alignment, the performance of the GPS/SDINS integration method suggested in this paper is analyzed using the covariance analysis.

• 제어로봇시스템학회논문지
• /
• 제21권7호
• /
• pp.691-698
• /
• 2015

Inertial Navigation Systems (INS) are widely used as the main navigation device for aircraft. To get the initial attitude, the INS requires the initial alignment before navigation starts. An aircraft also needs an engine test procedure that causes some vibrations before flight. An INS can't be aligned in a vibration environment so the initial alignment is performed before the aircraft engine test. Therefore, the initial alignment time of an INS has been a major factor in limiting an aircraft's takeoff response time. In this paper, we designed an initial alignment algorithm that can be executed even in disturbances such as aircraft run-up. We demonstrated verification of the algorithm that is embedded on the real INS and testing methods to evaluate the alignment of the INS. We also analyzed the test results of the proposed initial alignment algorithm that is performed during a real aircraft run-up.

• 제어로봇시스템학회:학술대회논문집
• /
• 제어로봇시스템학회 2000년도 제15차 학술회의논문집
• /
• pp.27-27
• /
• 2000

The nonlinear observers are proposed for a nonlinear system. To improve the characteristics such as a stability, a convergence, and an H$\sub$$\infty$/ filter performance criterion, we utilize and H$\sub$$\infty$/ filter Riccati equation or a modified H$\sub$$\infty$/ filter Riccati equation with a freedom parameter. Using the Lyapunov, the characteristics of the observer are analyzed. Then the in-flight alignment for a strapdown inertial navigation system(SDINS) is designed using the observer proposed. Simulation results show that the observer with the modified H$\sub$$\infty$/ fitter Riccati equation effectively improve the performance of the in-flight alignment.

• 한국소음진동공학회:학술대회논문집
• /
• 한국소음진동공학회 2012년도 춘계학술대회 논문집
• /
• pp.229-230
• /
• 2012