• 대한인간공학회지
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• 제31권6호
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• pp.733-740
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• 2012

Objective: The present study systematically analyzed the characteristics of ergonomic layout optimization methods by a comprehensive literature survey. Background: Although layout design methods for ergonomic placement of controls and displays on a console have been developed, understanding of their characteristics is lacking. Method: The present study analyzed layout optimization papers published past 20 years from the following four aspects: optimization model, optimization algorithm, design principle, and constraint/assumption. Results: The existing layout optimization methods based on various optimization techniques consider only a partial set of four layout principles(importance, frequency of use, sequence of use, and functional grouping) and two ergonomic criteria(visibility and reach). In addition, the existing methods oversimplify components in various sizes, shapes, and angles by assuming the equality of the components in size and shape. Conclusion: A more effective layout optimization method is needed which considers the layout principles and ergonomic criteria in a comprehensive manner and reflect the diversity of components in size and shape. Application: The identified characteristics on the existing layout optimization methods can be applicable to development of a better ergonomic console layout design method.

• 한국정보과학회논문지:소프트웨어및응용
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• 제31권10호
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• pp.1304-1319
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• 2004

프로그램 시험 비용은 테스트 데이타를 생성하는 과정을 자동화함으로써 상당히 줄일 수 있다. 테스트 데이타 생성은 보통 선택된 프로그램 경로를 실행하는 입력 값들을 식별하는 데 주안점을 둔다. 지금까지 많은 연구가 있어왔지만 여전히 해결해야할 문제가 있다 그러한 문제들 중에 모양 문제가 있다. 모양 문제는 주어진 프로그램 경로를 수행하기 위해 요구되는 입력 자료구조를 밝혀내는 문제이다. 이 논문에서 이 모양 문제에 대한 새로운 방법을 제시한다. 이 방법은 주어진 경로를 포인터 역 참조가 없는 정적단일 할당문 (Static Single Assignment, SSA) 형태로 변환한다. 이는 주어진 경로 상에 존재하는 각 프로그램 문장을 등식이나 부등식과 같은 제약식으로 간주할 수 있게 해준다. 이러한 제약식에 대한 해는 각 입력 변수에 대한 'points-to relation' 형태로 나타난다. 간단한 예들을 통하여 제안한 방법에 대해 설명한다.에 대해 설명한다.

• 대한전자공학회:학술대회논문집
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• 대한전자공학회 2003년도 신호처리소사이어티 추계학술대회 논문집
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• pp.401-404
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• 2003

이 논문에서는 이산형 상태공간 모델에 대한 $H_2$, $H_{\infty}$, 및 혼합 $H_{\infty}$ FIR 필터를 선형행렬부등식(LMI)를 이용하여 제안한다. 제안되는 필터는 FIR 구조로서 $H_2$ 및 $H_{\infty}$ 관점에서의 성능기준을 만족함과 더불어 선형성 및 불편향성의 특성을 지니고, 초기 상태에 관한 정보를 필요로 하지 않는다. 그리고 FIR 구조로 인해 기존의 FIR 형태의 필터에 비해 불확실성에 대해 보다 견실하며 빠른 수렴성을 갖는다. 모의 실험을 통해 이러한 장점을 예시한다.

• International Journal of Aeronautical and Space Sciences
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• 제8권1호
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• pp.10-20
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• 2007

For spacecraft attitude control, reaction wheel (RW) steering laws with more than three wheels for three-axis attitude control can be derived by using a control allocation (CA) approach.1-2 The CA technique deals with a problem of distributing a given control demand to available sets of actuators.3-4 There are many references for CA with applications to aerospace systems. For spacecraft, the control torque command for three body-fixed reference frames can be constructed by a combination of multiple wheels, usually four-wheel pyramid sets. Multi-wheel configurations can be exploited to satisfy a body-axis control torque requirement while satisfying objectives such as minimum control energy.1-2 In general, the reaction wheel steering laws determine required torque command for each wheel in the form of matrix pseudo-inverse. In general, the attitude control command is generated in the form of a feedback control. The spacecraft body angular rate measured by gyros is used to estimate angular displacement also.⁵ Combination of the body angular rate and attitude parameters such as quaternion and MRPs(Modified Rodrigues Parameters) is typically used in synthesizing the control command which should be produced by RWs.¹ The attitude sensor signals are usually corrupted by noise; gyros tend to contain errors such as drift and random noise. The attitude determination system can estimate such errors, and provide best true signals for feedback control.⁶ Even if the attitude determination system, for instance, sophisticated algorithm such as the EKF(Extended Kalman Filter) algorithm⁶, can eliminate the errors efficiently, it is quite probable that the control command still contains noise sources. The noise and/or other high frequency components in the control command would cause the wheel speed to change in an undesirable manner. The closed-loop system, governed by the feedback control law, is also directly affected by the noise due to imperfect sensor characteristics. The noise components in the sensor signal should be mitigated so that the control command is isolated from the noise effect. This can be done by adding a filter to the sensor output or preventing rapid change in the control command. Dynamic control allocation(DCA), recently studied by Härkegård, is to distribute the control command in the sense of dynamics⁴: the allocation is made over a certain time interval, not a fixed time instant. The dynamic behavior of the control command is taken into account in the course of distributing the control command. Not only the control command requirement, but also variation of the control command over a sampling interval is included in the performance criterion to be optimized. The result is a control command in the form of a finite difference equation over the given time interval.⁴ It results in a filter dynamics by taking the previous control command into account for the synthesis of current control command. Stability of the proposed dynamic control allocation (CA) approach was proved to ensure the control command is bounded at the steady-state. In this study, we extended the results presented in Ref. 4 by adding a two-step dynamic CA term in deriving the control allocation law. Also, the strict equality constraint, between the virtual and actual control inputs, is relaxed in order to construct control command with a smooth profile. The proposed DCA technique is applied to a spacecraft attitude control problem. The sensor noise and/or irregular signals, which are existent in most of spacecraft attitude sensors, can be handled effectively by the proposed approach.