Adaptive robust control of coupled attitude and orbit for spacecraft with model uncertainties

Sun, Jun; Wu, Xiande; Zhang, Shijie; Guo, Fengzhi; Song, Tao

doi:10.1108/aeat-07-2016-0113

Cited by 3 publications

(3 citation statements)

References 7 publications

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“…Spacecraft maneuver control is essential technologies in space missions, such as deep-space explorations, resource exploration, disaster warning and military reconnaissance (Jia et al, 2019;Sun et al, 2018Sun et al, , 2020Xu, 2021;Zhang et al, 2021Zhang et al, , 2020. Unlike attitude-only or orbit-only control missions, attitude and orbit motion of rigid spacecraft must be fully considered in the controller design and stability analysis.…”

Section: Introductionmentioning

confidence: 99%

Non-singular fixed-time pose tracking control for spacecraft with dead-zone input

Chen

Zhang

et al. 2022

AEAT

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Purpose The purpose of this paper is to investigate the pose control of rigid spacecraft subject to dead-zone input, unknown external disturbance and parametric uncertainty in space maneuvering mission. Design/methodology/approach First, a 6-Degree of Freedom (DOF) dynamic model of rigid spacecraft with dead-zone input, unknown external disturbances and parametric uncertainty is derived. Second, a super-twisting-like fixed-time disturbance observer (FTDO) with strong robustness is developed to estimate the lumped disturbances in fixed time. Based on the proposed observer, a non-singular fixed-time terminal sliding-mode (NFTSM) controller with superior performance is proposed. Findings Different from the existing sliding-mode controllers, the proposed control scheme can directly avoid the singularity in the controller design and speed up the convergence rate with improved control accuracy. Moreover, no prior knowledge of lumped disturbances’ upper bound and its first derivatives is required. The fixed-time stability of the entire closed-loop system is rigorously proved in the Lyapunov framework. Finally, the effectiveness and superiority of the proposed control scheme are proved by comparison with existing approaches. Research limitations/implications The proposed NFTSM controller can merely be applied to a specific type of spacecrafts, as the relevant system states should be measurable. Practical implications A NFTSM controller based on a super-twisting-like FTDO can efficiently deal with dead-zone input, unknown external disturbance and parametric uncertainty for spacecraft pose control. Originality/value This investigation uses NFTSM control and super-twisting-like FTDO to achieve spacecraft pose control subject to dead-zone input, unknown external disturbance and parametric uncertainty.

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Section: Introductionmentioning

confidence: 99%

Non-singular fixed-time pose tracking control for spacecraft with dead-zone input

Chen

Zhang

et al. 2022

AEAT

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“…Works dedicated to the fault-tolerant attitude control of rigid body can be found in Zhang et al (2020), Yin et al (2018); Hu et al (2018), Sun et al (2018); and Xiao et al (2014). Sliding mode control (SMC) is vastly used to compensate for actuator faults in attitude synchronization and tracking because of rapid response, easy implementation and intrinsic robustness against the faults, disturbance and uncertainties (Zhang et al , 2019; Rezaei and Menhaj, 2018; Qiao et al , 2020).…”

Section: Introductionmentioning

confidence: 99%

Adaptive neural-based finite-time attitude synchronization and tracking control of multiple rigid bodies under actuator faults and saturation

Mihankhah

Doustmohammadi

2021

AEAT

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Purpose The purpose of this paper, is to solve the problem of finite-time fault-tolerant attitude synchronization and tracking control of multiple rigid bodies in presence of model uncertainty, external disturbances, actuator faults and saturation. It is assumed that the rigid bodies in the formation may encounter loss of effectiveness and/or bias actuator faults. Design/methodology/approach For the purpose, adaptive terminal sliding mode control and neural network structure are used, and a new sliding surface is proposed to guarantee known finite-time convergence not only at the reaching phase but also on the sliding surface. The sliding surface is then modified using a proposed auxiliary system to maintain stability under actuator saturation. Findings Assuming that the communication topology between the rigid bodies is governed by an undirected connected graph and the upper bounds on the actuators’ faults, estimation error of model uncertainty and external disturbance are unknown, not only the attitudes of the rigid bodies in the formation are synchronized but also they track the time-varying attitude of a virtual leader. Using Lyapunov stability approach, finite-time stability of the proposed control algorithms demonstrated on the sliding phase as well as the reaching phase. The effectiveness of the proposed algorithm is also validated by simulation. Originality/value The proposed controller has the advantage that the need for any fault detection and diagnosis mechanism and the upper bounds information on estimation error and external disturbance is eliminated.

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“…Due to the complexities involved in ADCS design, some efforts have been made to develop simpler algorithms (Akbaritabar et al , 2018; Sun et al , 2018). When the EO-mission requires to design and manufacture a custom ADCS (Tayebi et al , 2017; Hua et al , 2018) then the “design for performance” strategy can be one of the shortest ways to meet the PRs by determining the best values for ADCS DPs (Jia et al , 2019).…”

Section: Introductionmentioning

confidence: 99%

Remote sensing satellite’s attitude control system: rapid performance sizing for passive scan imaging mode

Kosari

Sharifi

Ahmadi

et al. 2020

AEAT

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Purpose Attitude determination and control subsystem (ADCS) is a vital part of earth observation satellites (EO-Satellites) that governs the satellite’s rotational motion and pointing. In designing such a complicated sub-system, many parameters including mission, system and performance requirements (PRs), as well as system design parameters (DPs), should be considered. Design cycles which prolong the time-duration and consequently increase the cost of the design process are due to the dependence of these parameters to each other. This paper aims to describe a rapid-sizing method based on the design for performance strategy, which could minimize the design cycles imposed by conventional methods. Design/methodology/approach The proposed technique is an adaptation from that used in the aircraft industries for aircraft design and provides a ball-park figure with little engineering man-hours. The authors have shown how such a design technique could be generalized to cover the EO-satellites platform ADCS. The authors divided the system requirements into five categories, including maneuverability, agility, accuracy, stability and durability. These requirements have been formulated as functions of spatial resolution that is the highest level of EO-missions PRs. To size, the ADCS main components, parametric characteristics of the matching diagram were determined by means of the design drivers. Findings Integrating the design boundaries based on the PRs in critical phases of the mission allowed selecting the best point in the design space as the baseline design with only two iterations. The ADCS of an operational agile EO-satellite is sized using the proposed method. The results show that the proposed method can significantly reduce the complexity and time duration of the performance sizing process of ADCS in EO-satellites with an acceptable level of accuracy. Originality/value Rapid performance sizing of EO-satellites ADCS using matching diagram technique and consequently, a drastic reduction in design time via minimization of design cycles makes this study novel and represents a valuable contribution in this field.

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Adaptive robust control of coupled attitude and orbit for spacecraft with model uncertainties

Cited by 3 publications

References 7 publications

Non-singular fixed-time pose tracking control for spacecraft with dead-zone input

Non-singular fixed-time pose tracking control for spacecraft with dead-zone input

Adaptive neural-based finite-time attitude synchronization and tracking control of multiple rigid bodies under actuator faults and saturation

Remote sensing satellite’s attitude control system: rapid performance sizing for passive scan imaging mode

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