• Journal of Advanced Marine Engineering and Technology
• /
• v.39 no.7
• /
• pp.709-715
• /
• 2015

Underwater gliders do not typically have separate propellers for forward motion. They generate propulsive forces based on the difference between their buoyancy and gravity. They can control the volume from the buoyancy engine to adjust the propulsive force. In addition, the attitude of the underwater glider is controlled by a rubberless motion controller. The motion controller can change the mass center and moment of inertia of the inner moving mass. Owing to the change in these parameters, the attitude of the underwater glider is changed. In this study, we derive nonlinear, six degree of freedom (DOF) mathematical models for the motion controller and buoyancy engine. Using these equations, we perform dynamic simulations of the proposed underwater glider, and verify the suitability of the design and dynamic performances of the proposed underwater glider. We then perform the motion control simulation for the pitch and roll angle, and analyze the dynamic performance according to the pitch and roll angles.

• Journal of the Korea Society of Computer and Information
• /
• v.19 no.3
• /
• pp.11-16
• /
• 2014

In this paper, the two-wheels robot using a predictive controller to maintain the balance of the posture control in real time have been examined. A reaction wheel pendulum control method is adopted to maintain the balance while the bicycle robot is driving. The objective of this research was to design and implement a self-balancing algorithm using the dsPIC30F4013 embedded processor. To calculate the attitude in ARS using 2 axis gyro(roll, pitch) and 3 axis accelerometers (x, y, z). In this study, the disturbance of the posture for the asymmetrical propose to overcome the predictive controller which was a problem in the control of a remote system by introducing the two wheels of the robot controller and the linear prediction of the system controller combines the simulation was performed. Also, the robust characteristic for realizing the goal of designing a loop filter too robust controller is designed so that satisfactory stability of the control system to improve stability of the system to minimize degradation of performance was confirmed.

• Journal of the Institute of Electronics and Information Engineers
• /
• v.53 no.7
• /
• pp.95-102
• /
• 2016

Geomagnetic sensors are widely utilized for sensing heading direction of quadrotors. However, measurement from a geomagnetic sensor is easily corrupted by environmental magnetic field interference and roll/pitch directional motion. In this paper, a measurement method of a quadrotor heading direction is proposed for application to yaw attitude control. In order to eliminate roll/pitch directional motion effect, the geomagnetic sensor data is compensated using the roll/pitch angles measured for stabilization control. In addition, yaw-directional angular velocity data from a gyroscope sensor is fused with the geomagnetic sensor data using a complementary filter which is a simple and intuitive sensor fusion method. The proposed method is applied to experiments, and the results are presented to prove validity and effectiveness of the proposed method.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.36 no.11
• /
• pp.1104-1111
• /
• 2008

The supersonic advanced trainer based on digital flight-by-wire flight control system uses aircraft flight information such as altitude, calibrated airspeed and angle of attack to calculate flight control law, and this information is measured by IMFP(Integrated Multi-Function Probe) equipment. The information has triplex structure using three IMFP sensors. Final value of informations is selected by mid-value selection logic to have more flight data reliability. As the result of supersonic flight test, pitch oscillation is occurred due to IMFP noise when altitude hold autopilot mode is engaged. This tendency may affect stability and handling quality of an aircraft during autopilot mode. This paper addresses autopilot control law design to remove pitch oscillation and these control laws are verified by non-real time simulation and flight test. Also, pitch response characteristics of pitch attitude hold autopilot mode is improved by upgrading the control law structure and feedback gain tuning during bank turn.

• Journal of Aerospace System Engineering
• /
• v.17 no.5
• /
• pp.34-41
• /
• 2023

This paper applies the icing effect and wing rock uncertainty to small unmanned aerial vehicles (UAVs), which have recently attracted attention. Attitude control simulations were performed using various control methods. First, the selected platform, the Skywalker X8 UAV with blended wing-body (BWB) configuration, was linearized for both its baseline form, and a form with applied icing effects. Subsequently, using MATLAB SimulinkⓇ, simulations were conducted for roll and pitch attitude control of the baseline configuration and the configuration with icing effects, employing disturbance observer-based PID control, model reference adaptive control, and model predictive control. Furthermore, the study introduced wing rock uncertainty simultaneously with icing effects on the configured model-a combination not previously explored in existing research-and conducted simulations. The performance of each control Method was compared and analyzed.

• Journal of rehabilitation welfare engineering & assistive technology
• /
• v.9 no.2
• /
• pp.137-144
• /
• 2015

In this paper, we present an inertial sensor-based gait analysis system to measure and analyze lower-limb movements. We developed an integral AHRS(Attitude Heading Reference System) using a combination of rate gyroscope, accelerometer and magnetometer sensor signals. Several AHRS modules mounted on segments of the patient's body provide the quaternions representing the patient segments's orientation in space. And a method is also proposed for calculating three-dimensional inter-segment joint angle which is an important bio-mechanical measure for a variety of applications related to rehabilitation. To evaluate the performance of our AHRS module, the Vicon motion capture system, which offers millimeter resolution of 3D spatial displacements and orientations, is used as a reference. The evaluation resulted in a RMSE(Root Mean Square Error) of 1.08 and 1.72 degree in yaw and pitch angle. In order to evaluate the performance of our the gait analysis system, we compared the joint angle for the hip, knee and ankle with those provided by Vicon system. The result shows that our system will provide an in-depth insight into the effectiveness, appropriate level of care, and feedback of the rehabilitation process by performing real-time limb or gait analysis during the post-stroke recovery.

• The Journal of the Korea Contents Association
• /
• v.8 no.2
• /
• pp.27-32
• /
• 2008

In this paper, we propose an orientation tracking method and a digestion path model based on angular displacement. The proposed method expresses a capsule's orientation as 3-dimension vectors and its rotation angle. Errors in roll, pitch, and yaw representing capsule's orientation information is down to $1.6^{\circ}$. Using the proposed method we can measure a roll which is not Possible to be measured using the magnetic field method. We reduce algorithm complexity lower than a previous methods based on Euler angle.

• The Journal of the Korea institute of electronic communication sciences
• /
• v.13 no.6
• /
• pp.1269-1274
• /
• 2018

In this paper, it covers technical aspect of drone by introducing the drone hovering. Arduino Uno and 3-axis attitude and azimuth sensor are the two main components of the drone. Arduino Uno is used as a main controller and 3-axis attitude and azimuth sensor are used to collect axial (X,Y,Z) data, which is massaged to determine the pitch (fore and aft tilt) and the bank (side to side tilt). Furthermore, drone stabilizes horizontal attitude by correcting these tilted angle through PID control.

• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.2
• /
• pp.198.2-198.2
• /
• 2012

태양 전지판의 전개 여부는 저궤도 위성의 발사 성공 여부를 판단하는 가장 중요한 항목 중 하나이다. 태양 전지판이 성공적으로 전개되어야만 태양 지향 자세제어에 의해 위성 운용에 필요한 전력 생성이 가능하기 때문이다. 그러므로 발사 후 지상국 교신을 통해 최우선적으로 태양 전지판의 전개 여부를 판단한다. 태양 전지판의 전개 여부는 다양한 실패 상황에 가정해 총 5가지 조건을 통해 판단한다. 첫째, SAR1, SAR2의 입력 전류가 모두 0.8A보다 커야 한다. 만약 하나라도 0.8A 미만이라면 한 개 이상의 태양 전지판이 전개되지 않고 1번 태양 전지판이 태양 지향을 하지 못하는 상황이다. 둘째, SAR1 입력 전류와 SAR2 입력 전류의 값이 유사해야 한다. 만약 입력 전류 값이 크게 차이가 난다면 2번과 3번 태양 전지판 중 하나만 태양 지향을 하는 경우이다. 셋째, CSSA#5 출력 전류가 3.2mA보다 커야 한다. 만약 3.2mA보다 작다면 2번과 3번 태양 전지판의 전개가 실패하고 1번 태양 전지판이 태양 지향을 하는 경우 또는 1번 태양 전지판이 전개 실패하고 태양 지향을 하는 경우이다. 넷째, S/C Roll, Pitch, Yaw rate이 모두 0.2 deg/sec 보다 작아야 한다. 만약 body rate이 크다면 1번 태양 전지판의 전개 실패 상황을 예상할 수 있다. 다섯째, 각 태양 전지판의 온도 차이가 $35^{\circ}C$ 보다 작아야 한다. 만약 온도 차이가 크다면 1번 태양 전지판 전개 실패 상황에서 2번과 3번 태양 전지판이 태양 지향을 하는 경우이다. 총 다섯 가지의 조건을 모두 만족해야만 태양 전지판이 성공적으로 전개되었다고 판단한다. 태양 전지판의 전개 판단은 위성이 발사체에서 분리되고 약 4500초 이후 시점에 스발바드 지상국과의 교신을 통해 확인되었다. 이 시점의 SAR1 입력 전류는 약 2.00A, SAR2 입력 전류는 약 1.93A였기 때문에 모두 0.8A보다 크고 서로 유사한 값임을 확인했다. CSSA#5의 출력 전류는 약 3.5mA의 값을 나타냈다. S/C Roll rate은 -0.0084 deg/sec, Pitch rate은 -0.0072 deg/sec, Yaw rate은 -0.0303 deg/sec의 값을 나타냈다. 각 태양 전지판의 최대 온도 차이는 $7.7^{\circ}C$의 값을 나타냈다. 5가지 조건을 모두 만족함으로써 태양 전지판 전개는 성공적으로 수행된 것으로 판단했다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.41 no.3
• /
• pp.217-225
• /
• 2013

Typical quadrotor aircraft use four differential thrust vectors to control the motion. In this study, we design a quadrotor aircraft using collective and cyclic control to improve the shortcomings of existing quadrotor aircraft. The quadrotor aircraft with cyclic control can fly at various attitudes due to the excessive control degrees of freedom. Hence the quadrotor aircraft with cyclic control is suitable as high performance aircraft. In this study, modeling and stability analysis of the quadrotor aircraft have been performed using FLIGHTLAB. LQR control systems were designed using linear models at various flight conditions and verified through nonlinear simulations using MATLAB.