• 지구물리와물리탐사
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• 제23권2호
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• pp.89-96
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• 2020

물리탐사에서 유용한 3차원 좌표계 회전 문제를 일관성있게 정리하였다. 일관성을 유지하기 위한 기준으로 오른손 좌표계의 정의에서 출발하였다. 또한 능동 회전과 수동 회전의 개념을 설명하고, 서로 다른 좌표계 간의 회전 및 역회전은 전치행렬의 관계로서 기준 좌표계와 센서 좌표계 사이의 회전 관계를 명확히 하였다. 3차원 회전에서는 항법 등에서 사용하는 요-피치-롤(yaw-pitch-roll) 회전과 물리검층에서 쉽게 이해할 수 있는 방위각-편차-센서회전 회전 방식의 회전 행렬을 설명하였다. 또한, 이 둘과 Rodrigues 회전 공식에 의한 회전 행렬 각각의 각도를 구하는 수식을 정리하였다. 요-피치-롤 방식의 회전에서 나타나는 "Gimbal Lock" 현상을 그림과 수식으로 설명하고, 이의 해결방안으로 동원되는 사원수(quaternion)의 원리와 적용 방법에 대해서도 서술하였다.

• 제어로봇시스템학회논문지
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• 제4권5호
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• pp.674-679
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• 1998

In this paper, a new coarse alignment algorithm is proposed for roughly determining the initial attitude of the vehicle. The algorithm, referred as two-step coarse alignment algorithm, computes roll and pitch angle of the vehicle using accelerometer outputs, and then determines yaw angle with gyro outputs. With the geometric relation between sensor outputs and attitude angles, the algorithm error is analytically derived and compared with the previous coarse alignment algorithm that computes a transformation matrix using accelerometer md gyro outputs simultaneously. The simulation is also performed by varying the sensor errors. The results show that the proposed two-step coarse alignment algorithm has better performance for east tilt angle.

• 제어로봇시스템학회논문지
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• 제6권3호
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• pp.291-297
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• 2000

This paper presents an attitude determination algorithm for the local level strapdown inertial navigation where the body the earth and the transport rate can be calculated separately using a DCM computation scheme, Also presented is a velocity determination algorithm taking into account the attitude variation caused by he change of the navigation frame. The proposed algorithm are implemented using three samples of the velocity and the angle within the integration interval.

• 대한수학회지
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• 제56권4호
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• pp.1131-1158
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• 2019

An ideal right-angled pentagon in hyperbolic 4-space ${\mathbb{H}}^4$ is a sequence of oriented geodesics ($L_1,{\ldots},L_5$) such that $L_i$ intersects $L_{i+1},i=1,{\ldots},4$, perpendicularly in ${\mathbb{H}}^4$ and the initial point of $L_1$ coincides with the endpoint of $L_5$ in the boundary at infinity ${\partial}{\mathbb{H}}^4$. We study the geometry of such pentagons and the various possible augmentations and prove identities for the associated quaternion half side lengths as well as other geometrically defined invariants of the configurations. As applications we look at two-generator groups ${\langle}A,B{\rangle}$ of isometries acting on hyperbolic 4-space such that A is parabolic, while B and AB are loxodromic.

• 대한수학회지
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• 제56권3호
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• pp.595-622
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• 2019

An ideal right-angled pentagon in hyperbolic 4-space ${\mathbb{H}}^4$ is a sequence of oriented geodesics ($L_1,{\ldots},L_5$) such that Li intersects $L_{i+1},\;i=1,\;{\ldots},\;4$, perpendicularly in ${\mathbb{H}}^4$ and the initial point of $L_1$ coincides with the endpoint of $L_5$ in the boundary at infinity ${\partial}{\mathbb{H}}^4$. We study the geometry of such pentagons and the various possible augmentations and prove identities for the associated quaternion half side lengths as well as other geometrically defined invariants of the configurations. As applications we look at two-generator groups ${\langle}A,B{\rangle}$ of isometries acting on hyperbolic 4-space such that A is parabolic, while B and AB are loxodromic.

• 방송공학회논문지
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• 제1권2호
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• pp.176-187
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• 1996

본고는 로보트 팔의 선단에 부착된 카메라에 의하여 촬영된 일련의 스테레오 영상을 이용하여 운동물체의 3차원 자세 (위치와 방향)를 정확히 추정하는 방법을 다룬다. 본고는 이미 발표된 바 있는 연구결과를 확장한 것으로서[1], 2차원 영상의 측정잡음 뿐만아니라[1], 또한 로보트 팔의 죠인트 각도의 랜덤잡음이 함께 존재할 경우 world 좌표계 (또는 로보트 기지좌표계)를 기준으로 한 운동물체의 3차원 자세의 추정에 중점을 둔다. 이를 위하여, 다음 사항에 근거하여 선형 Kalman 필터를 유도한다. (1) 2차원 영상의 측정잡음이 3차원 공간으로 전파되는 것을 분석함으로써, 이에 기인한 물체좌표계의 방향오차를 카메라 좌표계를 기준으로 하여 모델링한다; (2) 죠인트 각도 오차에 의한 로보트 선단좌표계의 방향오차를 (1)의 결과와 결합하여 extended Jacobian matrix를 유도한다; 그리고 (3) 본질적으로 비선형인 물체의 회전운동을 quaternion을 도입함으로써 선형화 한다. 운동 파라메터는 추정된 quaternion으로부터 반복 최소자승 방법을 이용하여 계산된다. 모의실험 결과, 추정오차가 상당히 감소되고, 실제의 운동 파라메터가 참 값으로 정확히 수렴함을 알 수 있다.

• International Journal of Aeronautical and Space Sciences
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• 제12권1호
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• pp.43-56
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• 2011

An integrated system composed of guidance, navigation and control (GNC) system for autonomous proximity operations and the docking of two spacecraft was developed. The position maneuvers were determined through the integration of the state-dependent Riccati equation formulated from nonlinear relative motion dynamics and relative navigation using rendezvous laser vision (Lidar) and a vision sensor system. In the vision sensor system, a switch between sensors was made along the approach phase in order to provide continuously effective navigation. As an extension of the rendezvous laser vision system, an automated terminal guidance scheme based on the Clohessy-Wiltshire state transition matrix was used to formulate a "V-bar hopping approach" reference trajectory. A proximity operations strategy was then adapted from the approach strategy used with the automated transfer vehicle. The attitude maneuvers, determined from a linear quadratic Gaussian-type control including quaternion based attitude estimation using star trackers or a vision sensor system, provided precise attitude control and robustness under uncertainties in the moments of inertia and external disturbances. These functions were then integrated into an autonomous GNC system that can perform proximity operations and meet all conditions for successful docking. A six-degree of freedom simulation was used to demonstrate the effectiveness of the integrated system.

• 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.