Finite-Time Control for 6-DOF Coupling On-Orbit Service Spacecraft With Pre-Defined Maximum Settling Time Guaranteed
In this paper, for the precise relative motion control of the 6-DOF on-orbit service spacecraft, motivated by discovering a proper method to flexibly adjust the settling time before the control system design, a constraint function is proposed. Considering the ability of pre-defined performance techn...
| Main Authors: | , , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
IEEE
2021-01-01
|
| Series: | IEEE Access |
| Subjects: | |
| Online Access: | https://ieeexplore.ieee.org/document/9416640/ |
| _version_ | 1819127872634224640 |
|---|---|
| author | Yufeng Gao Chuanjiang Li Dongyu Li |
| author_facet | Yufeng Gao Chuanjiang Li Dongyu Li |
| author_sort | Yufeng Gao |
| collection | DOAJ |
| description | In this paper, for the precise relative motion control of the 6-DOF on-orbit service spacecraft, motivated by discovering a proper method to flexibly adjust the settling time before the control system design, a constraint function is proposed. Considering the ability of pre-defined performance techniques to pre-design response behaviors, a relevant control named by Pre-defined Maximum Settling Time Control (PMSTC) is investigated. Under the proposed framework, a PMSTC for spacecraft systems is designed with the aid of the power integrator-adding technique. The proposed controller allows us to design the response performance of a closed-loop system in advance, e.g., maximum settling time, maximum steady-state error, and maximum overshoot. More importantly, the PMSTC is able to separate the coupling of the settling time and the choosing of control parameters, which thus alleviate the complexity of the control design. The closed-loop system of the 6-DOF spacecraft showcases the full power of this approach, based on which, the rationality and effectiveness of the algorithm have been verified. To illustrate the characteristics of this algorithm, this paper compares the proposed algorithm with some state-of-the-art algorithms and analyzes the effect of parameters in detail. |
| first_indexed | 2024-12-22T08:18:50Z |
| format | Article |
| id | doaj.art-a2f004b528a24c4c9773ed593b8d68c8 |
| institution | Directory Open Access Journal |
| issn | 2169-3536 |
| language | English |
| last_indexed | 2024-12-22T08:18:50Z |
| publishDate | 2021-01-01 |
| publisher | IEEE |
| record_format | Article |
| series | IEEE Access |
| spelling | doaj.art-a2f004b528a24c4c9773ed593b8d68c82022-12-21T18:32:49ZengIEEEIEEE Access2169-35362021-01-019656056562110.1109/ACCESS.2021.30760179416640Finite-Time Control for 6-DOF Coupling On-Orbit Service Spacecraft With Pre-Defined Maximum Settling Time GuaranteedYufeng Gao0https://orcid.org/0000-0002-1539-4829Chuanjiang Li1https://orcid.org/0000-0001-7994-0836Dongyu Li2https://orcid.org/0000-0001-8338-0536Department of Control Science and Engineering, Harbin Institute of Technology, Harbin, ChinaDepartment of Control Science and Engineering, Harbin Institute of Technology, Harbin, ChinaSchool of Cyber Science and Technology, Beihang University, Beijing, ChinaIn this paper, for the precise relative motion control of the 6-DOF on-orbit service spacecraft, motivated by discovering a proper method to flexibly adjust the settling time before the control system design, a constraint function is proposed. Considering the ability of pre-defined performance techniques to pre-design response behaviors, a relevant control named by Pre-defined Maximum Settling Time Control (PMSTC) is investigated. Under the proposed framework, a PMSTC for spacecraft systems is designed with the aid of the power integrator-adding technique. The proposed controller allows us to design the response performance of a closed-loop system in advance, e.g., maximum settling time, maximum steady-state error, and maximum overshoot. More importantly, the PMSTC is able to separate the coupling of the settling time and the choosing of control parameters, which thus alleviate the complexity of the control design. The closed-loop system of the 6-DOF spacecraft showcases the full power of this approach, based on which, the rationality and effectiveness of the algorithm have been verified. To illustrate the characteristics of this algorithm, this paper compares the proposed algorithm with some state-of-the-art algorithms and analyzes the effect of parameters in detail.https://ieeexplore.ieee.org/document/9416640/On-orbit service spacecraft6-DOF spacecraftfinite-time stabilitypre-defined maximum settling time control |
| spellingShingle | Yufeng Gao Chuanjiang Li Dongyu Li Finite-Time Control for 6-DOF Coupling On-Orbit Service Spacecraft With Pre-Defined Maximum Settling Time Guaranteed IEEE Access On-orbit service spacecraft 6-DOF spacecraft finite-time stability pre-defined maximum settling time control |
| title | Finite-Time Control for 6-DOF Coupling On-Orbit Service Spacecraft With Pre-Defined Maximum Settling Time Guaranteed |
| title_full | Finite-Time Control for 6-DOF Coupling On-Orbit Service Spacecraft With Pre-Defined Maximum Settling Time Guaranteed |
| title_fullStr | Finite-Time Control for 6-DOF Coupling On-Orbit Service Spacecraft With Pre-Defined Maximum Settling Time Guaranteed |
| title_full_unstemmed | Finite-Time Control for 6-DOF Coupling On-Orbit Service Spacecraft With Pre-Defined Maximum Settling Time Guaranteed |
| title_short | Finite-Time Control for 6-DOF Coupling On-Orbit Service Spacecraft With Pre-Defined Maximum Settling Time Guaranteed |
| title_sort | finite time control for 6 dof coupling on orbit service spacecraft with pre defined maximum settling time guaranteed |
| topic | On-orbit service spacecraft 6-DOF spacecraft finite-time stability pre-defined maximum settling time control |
| url | https://ieeexplore.ieee.org/document/9416640/ |
| work_keys_str_mv | AT yufenggao finitetimecontrolfor6dofcouplingonorbitservicespacecraftwithpredefinedmaximumsettlingtimeguaranteed AT chuanjiangli finitetimecontrolfor6dofcouplingonorbitservicespacecraftwithpredefinedmaximumsettlingtimeguaranteed AT dongyuli finitetimecontrolfor6dofcouplingonorbitservicespacecraftwithpredefinedmaximumsettlingtimeguaranteed |