• 디지털산업정보학회논문지
• /
• 제13권3호
• /
• pp.11-17
• /
• 2017

The aerial support air sculptures currently exhibited in indoor spaces are similar to simple ad balloons, using multiple rope strands. Users now want more advanced unfixed sculptures, and hope these will develop into buoyant sculptures that can maintain the attitudes that users want on their own. This study investigated an attitude control system for unfixed levitation sculptures that can levitate with no rope and continuously maintain a certain attitude at a height specified by the user. To facilitate levitation, the exterior part of the sculpture was made of lightweight fibers, and the interior part was filled with helium gas. The controller was composed of a microprocessor of the dsPIC30F line from microchip, gyro, acceleration, and earth magnetic field sensors, and a highly efficient brushless DC (BLDC) electric motor. The attitude and position control system requires scheduling considering the trajectories of the sculpture and the control system, because the roles of the overall components are more important than those of a single controller. Furthermore, the system was designed like a fusion system that is expanded and controlled as a total controller, because it is interconnected with various sensors. The attitude control system of buoyant sculptures was implemented in this study, such that it can actively cope with the position, direction, stopping, and time aspects. The system performance was then evaluated.

• International Journal of Aeronautical and Space Sciences
• /
• 제4권1호
• /
• pp.75-87
• /
• 2003

The primary objective of this study is to demonstrate ground-based experiment for the attitude control of spacecraft. A two-axis rotational simulator with a flexible ann is constructed with on-off air thrusters as actuators. The simulator is also equipped with payload pointing capability by simultaneous thruster and DC servo motor actuation. The azimuth angle is controlled by on-off thruster command while the payload elevation angle is controlled by a servo-motor. A thruster modulation technique PWM(Pulse Width Modulation) employing a time-optimal switching function plus integral error control is proposed. An optical camera is used for the purpose of pointing as well as on-board rate sensor calibration. Attitude control performance based upon the new closed-loop control law is demonstrated by ground experiment. The modified switching function turns out to be effective with improved pointing performance under external disturbance. The rate sensor calibration technique by Kalman Filter algorithm led to reduction of attitude error caused by the bias in the rate sensor output.

• 전기학회논문지
• /
• 제67권7호
• /
• pp.871-877
• /
• 2018

In this paper, we propose a triple nested PID control scheme for stable hovering of a quadrotor and propose a complementary filter based sensor fusion technique to improve the performance of attitude, altitude and velocity measurement. The triple nested controller has a structure in which a double nested attitude controller that has the angular velocity PD controller in inner loop and the angular PI controller in outer loop, is nested in a velocity control loop to enable stable hovering even in the case of disturbance. We also propose a sensor fusion technique by applying a complementary filter in order to reduce the noise and drift error included in the acceleration and gyro sensor and to measure the velocity by fusing image, gyro, and acceleration sensor. In order to verity the performance, we applied the proposed control and measurement scheme to hovering control of quadrotor.

• 제어로봇시스템학회:학술대회논문집
• /
• 제어로봇시스템학회 1995년도 Proceedings of the Korea Automation Control Conference, 10th (KACC); Seoul, Korea; 23-25 Oct. 1995
• /
• pp.115-118
• /
• 1995

This paper present an attitude control using quaternions as feedback attitude errors. The Euler's eigenaxis rotation provides the shortest angular path between two attitudes. This eigenaxis rotation can be achieved by using quaternions since quaternions are related with the eigenaxis. The suggested controller uses error quaternions and body angular rates and generates a decoupling control torque that counteracts the natural gyroscopic coupling torque. The momentum dumping strategy using the earth magnetic field is also applied in this paper to unload the angular momentum of the reaction wheels used in the attitude control.

• 제어로봇시스템학회논문지
• /
• 제11권3호
• /
• pp.233-239
• /
• 2005

This paper presents the design and evaluation of a tiltrotor attitude controller. The implemented response type of the command augumentation system is Attitude Command Attitude Hold. The controller architecture can alleviate the need for extensive gain scheduling and thus has the potential to reduce development time. The control algorithm is constructed using the feedback linearization technique. And an on-line adaptive architecture that employs a neural network compensating the model inversion error caused by the deficiency of full knowledge tiltrotor aircraft dynamics is applied to augment the attitude control system. The use of Lyapunov stability analysis guarantees boundedness of the tracking error and network parameters. The performance of the controller is evaluated against ADS-33E criteria, using the nonlinear tiltrotor simulation code for Bell TR301 developed by KARI. (Korea Aerospace Research Institute)

• 한국항공우주학회지
• /
• 제49권2호
• /
• pp.129-138
• /
• 2021

최근 다양한 지상 및 우주 임무 수행을 위한 위성 개발이 활발히 진행되고 있음에 따라 위성의 고정밀·고기동성을 고려한 위성 자세제어 또한 요구되는 추세이다. 임무 수행 최적화를 위하여 고기동성의 제어 모멘트 자이로(Control Moment Gyros, CMG)를 위성에 장착하여 반작용 휠(Reaction Wheel, RW)과 같은 기존의 구동기에서 비롯되는 기동 제약을 완화시킬 수 있다. 또한, 구동기 자체의 제약 특성으로 인하여 위성의 각속도 제한이 발생하게 된다. 본 논문에서는 이를 고려한 CSCMG(Constant Speed CMG)장착 위성의 자세제어를 위하여 슬라이딩 모드 기반 제어기를 설계하였고, 리아푸노프 안정성을 확인하였으며 마지막으로 수치 시뮬레이션을 통하여 제어기 성능 분석을 진행하였다.

• 한국항공우주학회지
• /
• 제50권6호
• /
• pp.393-400
• /
• 2022

고고도 교전 시 사용되는 궤도수정 및 자세제어 시스템(Divert and Attitude Control System, DACS)은 고가이며 복잡하다. 본 논문에서는 비교적 단순하고 저가인 추력벡터제어(Thrust Vector Control, TVC)를 탑재한 유도탄의 고고도 종말 유도조종 루프를 제안한다. 본 유도조종 루프는 쿼터니언 피드백 제어기법을 이용하여 진 비례항법유도로 산출된 가속도 명령으로부터 변환된 추력 자세각 명령을 추종하며 유도를 수행한다. 고고도에서 탄도탄에 대한 교전 시뮬레이션을 통하여 제안한 유도조종 루프의 성능을 분석한다.

• International Journal of Aeronautical and Space Sciences
• /
• 제7권2호
• /
• pp.14-25
• /
• 2006

This paper is focused on designing an implementable control law to perform spacecraft various missions using momentum exchange devices such as reaction wheels(RWs) and control moment gyros(CMGs). A compact equation of motion of a spacecraft installed with various momentum exchange devices is derived in this paper. A hybrid control law is proposed for precision attitude control of agile spacecraft. The control law proposed in this paper allocates control torque to the CMGs and the RWs adequately to satisfy the precision attitude control and large angle maneuver simultaneously. The saturation problem of reaction wheels and the singularity problem of control moment gyros are considered. The problems are successfully resolved by using the proposed hybrid closed loop control law. Finally, the proposed hybrid control law is demonstrated by numerical simulations.

• 한국초등과학교육학회지:초등과학교육
• /
• 제31권2호
• /
• pp.208-215
• /
• 2012

A creative science writing program was developed, and applied to 2nd grade elementary students. Two 2nd grade elementary school classes in Seoul district were selected for the current study. A Pretest-Posttest Control Group Design was applied. The experimental group adopted the creative science writing program and the control group maintained traditional lectures for 12 classes. TTCT(Torrance Test of Creative Thinking) figural test and a scientific attitude test were conducted on both groups. According to the analysis, TTCT score of the experimental group was significantly higher than that of the control group (p<.01). Among several subscales of TTCT, elaboration and resistance to premature closure was especially improved. Also, scientific attitude scale of the experimental group was significantly higher than that of the control group (p<.01). Among subscales of scientific attitude, the creative science writing program was effective on improving students' open-mindedness, critical mindedness, cooperation, voluntariness, and endurance. Gender was not a factor in the improvement of both students' creativity and scientific attitude.

• 한국초등과학교육학회지:초등과학교육
• /
• 제20권2호
• /
• pp.281-291
• /
• 2001

The purpose of this study was to identify the effect of mind map activity on scientific attitude and science achievement in elementary school science. The subjects of this study were fifth-grade students selected from two classes in elementary school located in Seoul. The subjects were classified into two groups: One group is composed of thirty-eight students(experimental group) who were participated in mind map activity, and the other is composed of thirty-five students(control group) who were participated in traditional teaching situation. Pretest showed that there were no significant differences between experimental and control group in scientific attitude and science achievement. The results were as follows: First, the experimental group showed a significant improvement in the post-test science achievement compared to the control group. Second, the experimental group showed insignificant improvement in the post-test scientific attitude compared to the control group. Third, female students and mid-ranking group showed a significant improvement in the post-test science achievement. Fourth, in sex and academic ranking, experimental group did not show significant difference in the post-test scientific attitude. In conclusion, mind map activity was more effective than traditional teaching situation on science achievement. But mind map activity was less uneffective than traditional teaching situation on scientific attitude.