A Low-Complexity PD-Like Attitude Control for Spacecraft With Full-State Constraints

Mehdi Golestani; Khalid A. Alattas; Sami Ud Din; Fayez F.M. El-Sousy; Saleh Mobayen; Afef Fekih

doi:10.1109/ACCESS.2022.3159480

A Low-Complexity PD-Like Attitude Control for Spacecraft With Full-State Constraints

Mehdi Golestani, Khalid A. Alattas, Sami Ud Din, Fayez F.M. El-Sousy, Saleh Mobayen, Afef Fekih

Electrical Engineering

Research output: Contribution to journal › Article › peer-review

7 Scopus citations

Abstract

The problem of attitude control for rigid spacecraft under the attitude and angular velocity constraints is investigated in this study. Particularly, a simple structure constrained proportional-derivative (PD)-like control is proposed which contains two portions. The first portion is a conventional PD control to provide convergence of the system states; whereas the second portion provides the desired performance specifications such as convergence rate, overshoot and steady-state bound for attitude and rotation velocity to improve the attitude pointing accuracy and pointing stability. The distinctive property of the suggested constrained control method is to ensure the desired performance in transient and steady-state phases for all the system states. It also possesses much simpler structure compared to the existing constrained control techniques since it is based on a new methodology. The simulation results conducted on a rigid spacecraft verify the efficiency of the proposed approach.

Original language	English
Pages (from-to)	30707-30715
Number of pages	9
Journal	IEEE Access
Volume	10
DOIs	https://doi.org/10.1109/ACCESS.2022.3159480
State	Published - 2022

Keywords

PD control
Rigid spacecraft
attitude control
prescribed performance control

Access to Document

10.1109/ACCESS.2022.3159480

Cite this

@article{e9b5dac20c92474cb23291c4039b6cd3,

title = "A Low-Complexity PD-Like Attitude Control for Spacecraft With Full-State Constraints",

abstract = "The problem of attitude control for rigid spacecraft under the attitude and angular velocity constraints is investigated in this study. Particularly, a simple structure constrained proportional-derivative (PD)-like control is proposed which contains two portions. The first portion is a conventional PD control to provide convergence of the system states; whereas the second portion provides the desired performance specifications such as convergence rate, overshoot and steady-state bound for attitude and rotation velocity to improve the attitude pointing accuracy and pointing stability. The distinctive property of the suggested constrained control method is to ensure the desired performance in transient and steady-state phases for all the system states. It also possesses much simpler structure compared to the existing constrained control techniques since it is based on a new methodology. The simulation results conducted on a rigid spacecraft verify the efficiency of the proposed approach.",

keywords = "PD control, Rigid spacecraft, attitude control, prescribed performance control",

author = "Mehdi Golestani and Alattas, \{Khalid A.\} and Din, \{Sami Ud\} and El-Sousy, \{Fayez F.M.\} and Saleh Mobayen and Afef Fekih",

note = "Publisher Copyright: {\textcopyright} 2022 IEEE.",

year = "2022",

doi = "10.1109/ACCESS.2022.3159480",

language = "English",

volume = "10",

pages = "30707--30715",

journal = "IEEE Access",

issn = "2169-3536",

publisher = "Institute of Electrical and Electronics Engineers Inc.",

}

TY - JOUR

T1 - A Low-Complexity PD-Like Attitude Control for Spacecraft With Full-State Constraints

AU - Golestani, Mehdi

AU - Alattas, Khalid A.

AU - Din, Sami Ud

AU - El-Sousy, Fayez F.M.

AU - Mobayen, Saleh

AU - Fekih, Afef

PY - 2022

Y1 - 2022

N2 - The problem of attitude control for rigid spacecraft under the attitude and angular velocity constraints is investigated in this study. Particularly, a simple structure constrained proportional-derivative (PD)-like control is proposed which contains two portions. The first portion is a conventional PD control to provide convergence of the system states; whereas the second portion provides the desired performance specifications such as convergence rate, overshoot and steady-state bound for attitude and rotation velocity to improve the attitude pointing accuracy and pointing stability. The distinctive property of the suggested constrained control method is to ensure the desired performance in transient and steady-state phases for all the system states. It also possesses much simpler structure compared to the existing constrained control techniques since it is based on a new methodology. The simulation results conducted on a rigid spacecraft verify the efficiency of the proposed approach.

AB - The problem of attitude control for rigid spacecraft under the attitude and angular velocity constraints is investigated in this study. Particularly, a simple structure constrained proportional-derivative (PD)-like control is proposed which contains two portions. The first portion is a conventional PD control to provide convergence of the system states; whereas the second portion provides the desired performance specifications such as convergence rate, overshoot and steady-state bound for attitude and rotation velocity to improve the attitude pointing accuracy and pointing stability. The distinctive property of the suggested constrained control method is to ensure the desired performance in transient and steady-state phases for all the system states. It also possesses much simpler structure compared to the existing constrained control techniques since it is based on a new methodology. The simulation results conducted on a rigid spacecraft verify the efficiency of the proposed approach.

KW - PD control

KW - Rigid spacecraft

KW - attitude control

KW - prescribed performance control

UR - http://www.scopus.com/inward/record.url?scp=85126530798&partnerID=8YFLogxK

U2 - 10.1109/ACCESS.2022.3159480

DO - 10.1109/ACCESS.2022.3159480

M3 - Article

AN - SCOPUS:85126530798

SN - 2169-3536

VL - 10

SP - 30707

EP - 30715

JO - IEEE Access

JF - IEEE Access

ER -

A Low-Complexity PD-Like Attitude Control for Spacecraft With Full-State Constraints

Abstract

Keywords

Access to Document

Other files and links

Fingerprint

Cite this