Nonlinear optimal attitude control of spacecraft using novel state-dependent coefficient parameterizations

Yao, Junyu; Hu, Qinglei; Zheng, Jianying

doi:10.1016/j.ast.2021.106586

Cited by 20 publications

(9 citation statements)

References 26 publications

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“…Equation (6) and Equation ( 7) can be used to linearize the system around a stationary point (ω = 0 and Q = [0 0 0 − 1] T , assuming there is no net external torque, g cm = 0), which leads to Equation (11).…”

Section: Linear Control Based On Lqrmentioning

confidence: 99%

“…Equation ( 13) has been shown to satisfy SDRE conditions in the majority of statespace with exception of the region on which the angular velocity is close to 0 (the pair(A,B) loses rank in such region). In practical problems, regarding such a region, one approach is to switch to another SDC parametrization [11] or to resort to LQR. Note such the known limitation of this particular parametrization of SDRE imposes laxity.…”

Section: Nonlinear Control Based On Sdrementioning

confidence: 99%

“…Obtaining a good estimate of such a ROA, especially of a higher-order system, is a challenging task in itself. In fact, [11] states that analytical ROA for nonlinear systems with dimensions greater than two is usually unavailable. Such a task becomes even more difficult since the closed-loop matrix of SDRE is usually not available in the closed form [12].…”

Section: Introductionmentioning

confidence: 99%

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An Approach to Evaluate the Region of Attraction of Satellites Controlled by SDRE

Romero

Souza

2022

Wseas Transactions on Systems

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The control of a satellite can be designed with success by linear control theory if the satellite has slow angular motions. However, for fast maneuvers, the linearized models are not able to represent the effects of the nonlinear terms. One candidate technique for the design of the satellite’s control under fast maneuvers is the State- Dependent Riccati Equation (SDRE). SDRE provides an effective algorithm for synthesizing nonlinear feedback control by allowing nonlinearities. Nonetheless, much criticism has been leveled against the SDRE because it does not provide assurance of global asymptotic stability. Additionally, there are situations in which global asymptotic stability cannot be achieved (e.g., systems with multiple equilibrium points). Therefore, especially in aerospace, estimating the region of attraction (ROA) is fundamental. The Brazilian National Institute for Space Research (INPE, in Portuguese) was demanded by the Brazilian government to build remote-sensing satellites, such as the Amazonia-1 mission. In such missions, the satellite must be stabilized in three axes so that the optical payload can point to the desired target. In this paper, we share an approach to evaluate the ROAs of Amazonia-1 controlled by LQR (the linear counterpart of SDRE) and SDRE. The initial results showed SDRE has a larger ROA than LQR.

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Section: Linear Control Based On Lqrmentioning

confidence: 99%

Section: Nonlinear Control Based On Sdrementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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An Approach to Evaluate the Region of Attraction of Satellites Controlled by SDRE

Romero

Souza

2022

Wseas Transactions on Systems

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“…The naturally coupled characteristics between the attitude dynamics and the position dynamics are strong. Traditionally, the control schemes of attitude 5,6,7,8 and of position 9,10,11,12 are developed independent, it may result the satisfactory control performance cannot be realized. The 6-DOF control of the spacecraft with considering of the strong couplings has become a severe challenge.…”

Section: Introductionmentioning

confidence: 99%

“…FIGURE5 Responses of 𝑟 𝑒 of the chaser with the proposed controller (left) and the PD-type 𝐻∞ controller (right).…”

mentioning

confidence: 99%

Six degrees of freedom adaptive finite-time control for spacecraft approaching to a non-cooperative target

Zhu

Luo

Guo

et al. 2022

Preprint

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The six degrees of freedom (6-DOF) adaptive finite-time control for spacecraft with unknown uncertainties and disturbances approaching to a non-cooperative target is investigated in this study. The system of the spacecraft with coupled relative translation and relative rotation are modeled. Considering the unknown mass and inertia uncertainties and the state-dependent disturbances, a coupled 6-DOF adaptive finite-time tracking control law with a self-adjustment function is developed to achieve high precision proximity operations between chaser and non-cooperative target. The convergence performance is improved by the designed self-adjustment function. The unknown mass, inertia and disturbance are estimated by adaptive update laws. The properties of the proposed control law are discussed through the comparison of simulation results.

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State‐dependent indirect hp‐pseudospectral method for rigid spacecraft attitude optimal control problem

Liu,

2024

Asian Journal of Control

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The state‐dependent indirect ‐pseudospectral (SDIHP) method for rigid spacecraft attitude control is presented in this paper. The optimal controller is obtained by the SDIHP method through classifying the attitude optimal control problem as a nonlinear quadratic optimal control problem. In the proposed control scheme, successive state‐dependent coefficient (SDC) parameterization is initially applied to the spacecraft dynamics to derive an available linear system to decrease the calculation cost and speed. Then, the indirect ‐adaptive spectral discretization is developed to convert the resultant optimal control problem into a sequence of linear equations, which can improve the global computational efficiency and guarantee the solving precision. Hence, the optimal control can be efficiently solved using basic matrix operations under the necessary collocation points based on the ‐adaptive features. Considering the inertia uncertainties and external disturbances, a state feedback controller is generated by the receding horizon control (RHC) framework to improve the robustness. Simulation results are included to show the effectiveness and performance of the suggested optimal method.

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Nonlinear optimal attitude control of spacecraft using novel state-dependent coefficient parameterizations

Cited by 20 publications

References 26 publications

An Approach to Evaluate the Region of Attraction of Satellites Controlled by SDRE

An Approach to Evaluate the Region of Attraction of Satellites Controlled by SDRE

Six degrees of freedom adaptive finite-time control for spacecraft approaching to a non-cooperative target

State‐dependent indirect hp‐pseudospectral method for rigid spacecraft attitude optimal control problem

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