scholarly journals Robust PD+ Control Algorithm for Satellite Attitude Tracking for Dynamic Targets

2021 ◽  
Vol 2021 ◽  
pp. 1-15
Author(s):  
Gao Shan ◽  
Li You ◽  
Xue Huifeng ◽  
Yao ShuYue
Keyword(s):  
Angular Velocity ◽  
Sliding Mode ◽  
External Disturbance ◽  
Control Analysis ◽  
Pd Controller ◽  
Analysis Model ◽  
Control Torque ◽  
Pd Control ◽  
Satellite Attitude ◽  
Attitude Tracking

In this paper, a PD + controller combined with the sliding mode surface is proposed to improve system convergence rate and efficiency on control torque for satellite attitude tracking control. A sliding mode surface with the maneuver stage is constructed by the Euler axis; hence, the constant angular velocity is achieved. The PD + controller with the variable structure and auxiliary term is constructed to track the desired sliding mode surface. The Lyapunov function in PD control analysis is modified to simplify stability analysis. Model uncertainty, external disturbance, control torque constraint, and angular velocity constraint are taken into consideration, and a novel method to reduce the overshoot of angular velocity is proposed. The performance and superiority of the proposed method are demonstrated by numerical simulation results.

Finite time control strategy for satellite attitude maneuver based on hybrid actuator

2017 ◽  
Vol 40 (9) ◽  
pp. 2798-2806 ◽  
Author(s):  
Dong Ye ◽  
Xiao Zhang ◽  
Xucheng Wan ◽  
Zhaowei Sun
Keyword(s):  
Control Strategy ◽  
Finite Time ◽  
Sliding Mode ◽  
External Disturbance ◽  
Reference Trajectory ◽  
Terminal Sliding Mode ◽  
Time Control ◽  
Satellite Attitude ◽  
Attitude Maneuver ◽  
Attitude Tracking

In this paper, a Nonsingular Terminal Sliding Mode Control (NTSMC) strategy is investigated to address the finite-time attitude tracking problem of a rigid spacecraft. Hybrid thruster and flywheel actuator system is used for rapid reorientation under external disturbance. The reference torque is obtained from time-optimal attitude trajectory, and it is exerted on the satellite by thrusters in the form of feedforward compensation. Owing to thruster output torque deviation, initial measurement error and external disturbances, the practical trajectory of a satellite would deviate from reference trajectory. In order for the satellite to track the reference trajectory in finite time, the correction torque is deduced based on the error between reference trajectory and real-time measurements, and then applied through flywheels in the form of feedback compensation. The NTSMC method is used to solve nonsingular problem and to improve the control precision of the satellite attitude tracking issue. The numerical simulation results show that this control strategy is effective and it has great robustness.

Robust spacecraft attitude tracking control with integral terminal sliding mode surface considering input saturation

2018 ◽  
Vol 41 (2) ◽  
pp. 405-416 ◽  
Author(s):  
Haitao Chen ◽  
Shenmin Song ◽  
Xuehui Li
Keyword(s):  
Finite Time ◽  
Sliding Mode ◽  
External Disturbance ◽  
Input Saturation ◽  
External Disturbances ◽  
Terminal Sliding Mode ◽  
Modeling Uncertainty ◽  
Finite Time Convergence ◽  
Attitude Tracking ◽  
Attitude Tracking Control

This paper studies the finite time spacecraft attitude tracking control problem, while considering modeling uncertainty, external disturbances and control input saturation. A novel integral terminal sliding mode surface (ITSMS) is designed by combining the fast terminal sliding mode surface (FTSMS) with a low pass filter to achieve a fast finite time convergence rate for the control system, without input singularity. An auxiliary signal is used to compensate for the effects of actuator saturation. The basic controller is first formulated based on the ITSMS, fast-TSM-type reaching law and auxiliary system, in the presence of an external disturbance and input saturation. Then, an adaptive control procedure is introduced, which simultaneously handles modeling uncertainty and external disturbance, thereby creating an adaptive attitude tracking controller. The proposed controller provides a fast finite time convergence rate for the control system, based on the newly designed ITSMS, while simultaneously compensating for modeling uncertainty, external disturbances and input saturation, without restricting the parameter selection process nor requiring repeated differentiation of nonlinear functions. Finally, digital simulation results are presented and demonstrate the effectiveness of the proposed controllers.

Magnetic attitude tracking control of gravity gradient microsatellite in orbital transfer

2019 ◽  
Vol 123 (1269) ◽  
pp. 1881-1894
Author(s):  
Liang Sun ◽  
Zhiwen Wang ◽  
Guowei Zhao ◽  
Hai Huang
Keyword(s):  
Tracking Control ◽  
Sliding Mode ◽  
Tracking Error ◽  
Gravity Gradient ◽  
Control Torque ◽  
Orbital Transfer ◽  
Attitude Tracking ◽  
Lyapunov Stability Analysis ◽  
Attitude Tracking Control ◽  
The Magnetic Field

ABSTRACTThe problem of the magnetic attitude tracking control is studied for a gravity gradient microsatellite in orbital transfer. The contributions of the work are mainly shown in two aspects: (1) the design of an expected attitude trajectory; (2) a method of the magnetic attitude tracking control. In orbital transfer, the gravity gradient microsatellite under a constant thrust shows complicated dynamic behaviours. In order to damp out the pendular motion, the gravity gradient microsatellite is subject to the the attitude tracking problem. An expected attitude trajectory is designed based on dynamic characteristics revealed in the paper, which not only ensures the flight safety of the system, but also reduces the energy consumption of the controller. Besides, the control torque produced by a magnetorquer is constrained to lie in a two-dimensional plane orthogonal to the magnetic field, so an auxiliary compensator is proposed to improve the control performance, which is different from existing magnetic control methods. In addition, a sliding mode control based on the compensator is presented, and the Lyapunov stability analysis is performed to show the global convergence of the tracking error. Finally, a numerical case of the gravity gradient microsatellite is studied to demonstrate the effectiveness of the proposed tracking control.

scholarly journals Reaction Wheel Installation Deviation Compensation for Overactuated Spacecraft with Finite-Time Attitude Control

2013 ◽  
Vol 2013 ◽  
pp. 1-10 ◽  
Author(s):  
Aihua Zhang ◽  
Jianfei Ni ◽  
Hamid Reza Karimi
Keyword(s):  
Finite Time ◽  
Attitude Control ◽  
Sliding Mode ◽  
External Disturbance ◽  
Control Technique ◽  
Adaptive Sliding Mode Control ◽  
Reaction Wheel ◽  
Compensation Control ◽  
Attitude Tracking ◽  
Attitude Tracking Control

A novel attitude tracking control scheme is presented for overactuated spacecraft to address the attitude stabilization problem in presence of reaction wheel installation deviation, external disturbance and uncertain mass of moment inertia. An adaptive sliding mode control technique is proposed to track the uncertainty. A Lyapunov-based analysis shows that the compensation control law can guarantee that the desired attitude trajectories are followed in finite-time. The key feature of the proposed control strategy is that it globally asymptotically stabilizes the system, even in the presence of reaction wheel installation deviation, external disturbances, and uncertain mass of moment inertia. The attitude track performance using the proposed finite-time compensation control is evaluated through a numerical example.

Robust Intelligent Fault-Tolerant Based Finite-Time Attitude Control for Quadrotor UAV Without Angular Velocity Measurements

2021 ◽  
Author(s):  
Kang Liu ◽  
Rujing Wang
Keyword(s):  
Angular Velocity ◽  
Finite Time ◽  
Attitude Control ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
External Disturbance ◽  
Input Saturation ◽  
Parametric Uncertainty ◽  
Accurate Information ◽  
Terminal Sliding Mode

Abstract This study considers the problem of finitetime attitude control for quadrotor unmanned aerial vehicles (UAVs) subject to parametric uncertainties, external disturbances, input saturation, and actuator faults. Under the strong approximation of radial basis function neural networks (RBFNN), an adaptive finitetime NN observer is first presented to obtain the accurate information of unavailable angular velocity. More importantly, an adaptive mechanism to adjust the output gain of the fuzzy logic system (FLS) is developed to avoid the selection of larger control gains, and can even work well without the prior information on the bound of the lumped disturbance. Based on the nonsingular fast terminal sliding mode manifold, a novel switching control law is designed by incorporating the adaptive FLS and fast continuous controller in order to remove the undesired chattering phenomenon and solve the negative effects induced from the parametric uncertainty, external disturbance, and actuator fault. To deal with the input saturation, an auxiliary system is constructed. The rigorous theoretical analysis is given to prove that all the signals in the closed-loop system are uniformly bounded, and tracking errors converge into bounded neighborhoods near the origin in finite time. Moreover, the issue of selecting control parameters is analyzed in detail. Last but not least, the comparative simulation results show the validity and feasibility of the proposed control framework.

scholarly journals SMC-Based Synchronization of Multiple Inertial Measurement Units with Application to Attitude Tracking Control

2021 ◽  
Vol 2021 ◽  
pp. 1-9
Author(s):  
Yuping He ◽  
Shijie Zhang
Keyword(s):  
Attitude Control ◽  
Sliding Mode ◽  
External Disturbance ◽  
Zero Drift ◽  
Consensus Algorithm ◽  
Inertial Measurement Units ◽  
Inertial Measurement ◽  
Attitude Tracking ◽  
Measurement Units ◽  
Attitude Tracking Control

In this paper, the attitude control of aircraft with multiple inertial measurement units under the influence of unknown gyro zero drift and external disturbance is studied. First of all, the observers are designed to estimate the zero drift biases based on the consensus algorithm. The angular velocity used for aircraft control is obtained by compensating the biases. Then, considering the external disturbance in the aircraft motion, this paper introduces a super-twisting sliding-mode algorithm to design the observer in order to compensate the disturbance. In addition, based on the proposed observers, a controller is designed to realize attitude control of the aircraft with the gyro zero drift and the external disturbance. Finally, the simulation results are given to verify the effectiveness of the proposed control law.

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