Solar sailing CubeSat attitude control method with satellite as moving mass

2019 ◽  
Vol 159 ◽  
pp. 331-341
Author(s):  
He Huang ◽  
Jun Zhou
Keyword(s):  
Attitude Control ◽  
Control Method ◽  
Moving Mass ◽  
Solar Sailing

scholarly journals Design and validation of an MPC controller for CMG-based testbed

2021 ◽  
Author(s):  
Matteo Facchino ◽  
Atsushi Totsuka ◽  
Elisa Capello ◽  
Satoshi Satoh ◽  
Giorgio Guglieri ◽  
...  
Keyword(s):  
Predictive Control ◽  
Attitude Control ◽  
High Speed ◽  
Control Method ◽  
Input Constraints ◽  
Virtual Reference ◽  
Control Moment ◽  
Pyramidal Configuration ◽  
Actuation Systems ◽  
Constraints Satisfaction

AbstractIn the last years, Control Moment Gyros (CMGs) are widely used for high-speed attitude control, since they are able to generate larger torque compared to “classical” actuation systems, such as Reaction Wheels . This paper describes the attitude control problem of a spacecraft, using a Model Predictive Control method. The features of the considered linear MPC are: (i) a virtual reference, to guarantee input constraints satisfaction, and (ii) an integrator state as a servo compensator, to reduce the steady-state error. Moreover, the real-time implementability is investigated using an experimental testbed with four CMGs in pyramidal configuration, where the capability of attitude control and the optimization solver for embedded systems are focused on. The effectiveness and the performance of the control system are shown in both simulations and experiments.

scholarly journals Deformation Reconstruction and High-Precision Attitude Control of a Launch Vehicle Based on Strain Measurements

2021 ◽  
Vol 2021 ◽  
pp. 1-20
Author(s):  
Liang Zhuang ◽  
Zhang Yulin
Keyword(s):  
High Precision ◽  
Attitude Control ◽  
Control Method ◽  
Launch Vehicles ◽  
Bending Vibration ◽  
Inverse Control ◽  
Deformation Parameters ◽  
Control Framework ◽  
Fbg Sensors ◽  
Dynamic Inverse

The development of launch vehicles has led to higher slenderness ratios and higher structural efficiencies, and the traditional control methods have difficulty in meeting high-quality control requirements. In this paper, an incremental dynamic inversion control method based on deformation reconstruction is proposed to achieve high-precision attitude control of slender launch vehicles. First, the deformation parameters of a flexible rocket are obtained via fiber Bragg grating (FBG) sensors. The deformation and attitude information is introduced into the incremental dynamic inverse control loop, and an attitude control framework that can alleviate bending vibration and deformation is established. The simulation results showed that the proposed method could accurately reconstruct the shapes of flexible launch vehicles with severe vibration and deformation, which could improve the accuracy and stability of attitude control.

Magnetorquer Based Vertical Damping Method for Microsatellite Attitude Control

2012 ◽  
Vol 263-266 ◽  
pp. 584-587
Author(s):  
Xu Guang Hou ◽  
Jian Yan ◽  
Jin Jin ◽  
Shun Liang Mei
Keyword(s):  
Power Supply ◽  
Attitude Control ◽  
Control Method ◽  
The Sun ◽  
Extreme Situation ◽  
Control Scheme ◽  
Solar Battery ◽  
Simulation Results ◽  
Electrical Source

Aiming at a three-axis stabilized microsatellite, a novel attitude control method, called magnetorquer based vertical damping, is proposed to avoid the occurrence of the worst situation that the non-solar-battery-plane spins towards the sun. DSP based simulation results based on DSP show that the vertical damping method outperforms the simple damping method when no orbit information is available, simultaneously the whole attitude control scheme is simple and effective. The proposed solution guarantees a stable power supply from the electrical source even under the extreme situation, which improves the reliability of the whole microsatellite system.

scholarly journals Research on Trajectory Planning and Tracking of Hexa-copter

2018 ◽  
Vol 173 ◽  
pp. 02008
Author(s):  
Qiyu Wang ◽  
Huijie Zhang ◽  
Jinrong Han
Keyword(s):  
Trajectory Planning ◽  
Flight Control ◽  
Attitude Control ◽  
Control Method ◽  
Sliding Mode ◽  
Interpolation Method ◽  
Spline Interpolation ◽  
Variable Structure ◽  
Flight Trajectory ◽  
Attitude Stability

In this paper, the flight control problem of hexa-copter is studied in detail from threedimensional trajectory planning to tracking. Then the cubic spline interpolation method is used to generate the trajectory by using these time marked waypoints. The flight trajectory curve produced by this method is smooth, twice differentiable, and it is easy to control implementation. The flight dynamics model of the UAV has the characteristics of multi-input multi-output, strong coupling, under-actuation, severe nonlinearity and external environmental disturbance. In order to improve the accuracy of flight trajectory and the stability of attitude control, a multi-loop sliding mode variable structure control method is proposed to achieve the hexa-copter flight trajectory tracking. The simulation results show that this method can track the predetermined flight trajectory and keep the attitude stability of the UAV normally.

Experimental study of rapid oscillation suppression of a pendulum on the basis of intermittent mass motion

2019 ◽  
Vol 26 (9-10) ◽  
pp. 840-850 ◽  
Author(s):  
Chaofeng Li ◽  
Zijian Zhang ◽  
Zixuan Zhang ◽  
Bangchun Wen
Keyword(s):  
Control Method ◽  
Structure Design ◽  
Mass Motion ◽  
Vertical Position ◽  
Experimental Setup ◽  
Continuous Control ◽  
Moving Mass ◽  
Oscillation Control ◽  
Efficient Suppression ◽  
The Stability

In this paper, the experimental setup of a pendulum with a moving mass is established to study the rapid suppression of pendulum oscillation. The intermittent motion of the moving mass is employed to achieve more efficient suppression. The proposed control method can reduce mass motion distance rapidly in the vicinity of the vertical position to ensure the stability of the system. The mass motion is triggered by recognizing the pendulum angle in real time so that the nonsynchronous motion can be avoided. With the verification of the accuracy of the controlled motion distance, the effects of several motion parameters of the moving mass are studied. Moreover, the experimental results reveal that the proposed control strategy is more efficient in oscillation suppressing than the traditional continuous control method. The experimental setup and the proposed approach can be applied in pendulum-like structure design and oscillation control.

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