Adaptive prescribed performance attitude control for RLV with mismatched disturbance

2021 ◽  
pp. 106918
Author(s):  
Bailing Tian ◽  
Zhiyu Li ◽  
Xiuyun Zhang ◽  
Qun Zong
Keyword(s):  
Attitude Control ◽  
Prescribed Performance ◽  
Mismatched Disturbance

Event-triggered neuroadaptive attitude control for spacecraft with fixed-time prescribed performance

2020 ◽  
Author(s):  
Qi Li ◽  
Xueping Wang ◽  
Qiuxiong Gou ◽  
Zhiqi Niu ◽  
Li Ding ◽  
...  
Keyword(s):  
Attitude Control ◽  
Fixed Time ◽  
Prescribed Performance ◽  
Event Triggered

Prescribed Performance Fine Attitude Control for a Flexible Hypersonic Vehicle with Unknown Initial Errors

2017 ◽  
Vol 20 (6) ◽  
pp. 2357-2369 ◽  
Author(s):  
He‐Wei Zhao ◽  
Yong Liang ◽  
Xiu‐Xia Yang ◽  
Yun‐An Hu
Keyword(s):  
Attitude Control ◽  
Hypersonic Vehicle ◽  
Prescribed Performance ◽  
Initial Errors

Simple model-free attitude control design for flexible spacecraft with prescribed performance

2018 ◽  
Vol 233 (8) ◽  
pp. 2760-2771 ◽  
Author(s):  
Chao Zhang ◽  
Guangfu Ma ◽  
Yanchao Sun ◽  
Chuanjiang Li
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Control Design ◽  
Relevant Information ◽  
Tracking Accuracy ◽  
Attitude Control System ◽  
Prescribed Performance ◽  
Control Approach ◽  
Model Free ◽  
Flexible Vibrations

In this paper, a model-free attitude control approach is proposed for the spacecraft in the presence of external disturbances and flexible vibrations with both complexity and performance concerns. By utilizing prescribed performance and backstepping techniques, the controller is constructed in a simple form without requiring any relevant information of the attitude control system dynamics. Moreover, fuzzy/neural network approximations, observers, or adaptive laws are not adopted into the control design, so that the related problems introduced by these estimation structures can be avoided. Numerical simulations in different cases show that the control system can obtain quick and smooth dynamic process and expected tracking accuracy despite the influence of disturbances and flexible vibrations, which demonstrates the effectiveness of the proposed scheme. Owing to the above good features, it is suitable for practical engineering.

scholarly journals Prescribed Performance-Based Event-Driven Fault-Tolerant Robust Attitude Control of Spacecraft under Restricted Communication

Electronics ◽  
2021 ◽  
Vol 10 (14) ◽  
pp. 1709
Author(s):  
Syed Muhammad Amrr ◽  
Abdulrahman Alturki ◽  
Ankit Kumar ◽  
M. Nabi
Keyword(s):  
Attitude Control ◽  
Data Transfer ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
Control Input ◽  
Prescribed Performance ◽  
Event Trigger ◽  
Steady State Responses ◽  
Complex Nonlinear Systems ◽  
State Responses

This paper explores the problem of attitude stabilization of spacecraft under multiple uncertainties and constrained bandwidth resources. The proposed control law is designed by combining the sliding mode control (SMC) technique with a prescribed performance control (PPC) method. Further, the control input signal is executed in an aperiodic time framework using the event-trigger (ET) mechanism to minimize the control data transfer through a constrained wireless network. The SMC provides robustness against inertial uncertainties, disturbances, and actuator faults, whereas the PPC strategy aims to achieve a predefined system performance. The PPC technique is developed by transforming the system attitude into a new variable using the prescribed performance function, which acts as a predefined constraint for transient and steady-state responses. In addition, the ET mechanism updates the input value to the actuator only when there is a violation of the triggering rule; otherwise, the actuator output remains at a fixed value. Moreover, the proposed triggering rule is constituted through the Lyapunov stability analysis. Thus, the proposed approach can be extended to a broader class of complex nonlinear systems. The theoretical analyses prove the uniformly ultimately bounded stability of the closed-loop system and the non-existence of the Zeno behavior. The effectiveness of the proposed methodology is also presented along with the comparative studies through simulation results.

Fault-tolerant attitude control for flexible spacecraft subject to input and state constraint

2020 ◽  
Vol 42 (14) ◽  
pp. 2660-2674
Author(s):  
Mehdi Golestani ◽  
Seyed Majid Esmaeilzadeh ◽  
Bing Xiao
Keyword(s):  
Attitude Control ◽  
Actuator Saturation ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
Fixed Time ◽  
State Constraint ◽  
Flexible Spacecraft ◽  
Convergence Time ◽  
Prescribed Performance ◽  
High Attitude

This paper considers the problem of fault-tolerant attitude control for a flexible spacecraft subject to input and state constraint. Particularly, a new sliding mode-based attitude control with fixed-time convergent for the flexible spacecraft is developed in which the convergence rate of the system state is improved both far from and at close range of the origin. In contrast to the existing complicated prescribed performance controls (PPC), the proposed PPC possesses a much simpler structure due to the use of a novel constraint concept without employing error transformation. It also introduces a modified prescribed performance function (MPPF) to explicitly determine the settling time. It is rigorously proved that the attitude variable is kept within the predefined constraint boundaries even when the actuator saturation is taken into account. Moreover, the proposed controller is inherently continuous and the chattering is effectively reduced. An adaptive mechanism is developed in which no prior knowledge of the lumped uncertainties is required. Finally, numerical simulations are presented to demonstrate that the proposed controller is able to successfully accomplish attitude control with high attitude pointing accuracy and stability. More specifically, it provides faster convergence (improvement percentage of convergence time (IP_CT) is about 18%) and more accurate control (improvement percentages of MRPs (IP_MRPs) and angular velocity (IP_AV) are about 60% and 80%, respectively) under healthy actuators. Values of IP_CT, IP_CT, and IP_AV are 50%, 99.9% and 99.9% under faulty actuators, respectively.

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