Saturated Attitude Control for Rigid Spacecraft Under Attitude Constraints

Hu, Qinglei; Liu, Yueyang; Dong, Hongyang; Zhang, Youmin

doi:10.2514/1.g004613

Cited by 29 publications

(7 citation statements)

References 24 publications

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“…In Figure 4, the control input of the control system is about 0.25 Nm under the FTCLFC, and the maximal values of the control input under the CLFC and the SMCLFC are 0.55 Nm and 0.35 Nm, respectively. To sum up, the FTCLFC can provide a better FIGURE 6 The MRPs under the CLFC in [25], SMCLFC in [26] and the FTCLFC (32) attitude stabilizing with less control input than the other two controllers. The values of the performance indexes of the three controllers are plotted in Figure 5.…”

Section: Figurementioning

confidence: 99%

“…Various attitude maneuver control techniques have been developed for spacecraft in the last few decades, to name a few, robust control [1][2][3][4][5][6], optimal control [7][8][9][10] and adaptive control [11][12][13][14][15]. Under the most of existing attitude controllers, the spacecraft can achieve attitude stabilization without considering some optimal performance index.…”

Section: Introductionmentioning

confidence: 99%

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Finite‐time attitude stabilization of rigid spacecrafts based on control Lyapunov functions

Zhang

2022

IET Control Theory & Appl

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In this paper, the control Lyapunov function (CLF) approach is adopted to investigate the finite-time attitude control of rigid spacecraft subject to parameter uncertainty and external disturbance. By using an extended state observer to estimate the parameter uncertainty and external disturbance, a finite-time CLF controller is proposed for attitude stabilization of the spacecraft system. The designed finite-time CLF controller includes two parts. The first part is a classical CLF based attitude controller, which is proposed to ensure the globally asymptotical stability of the nominal spacecraft system. The second one is a sliding mode controller, which is used to ensure the finite-time convergence performance of the spacecraft control system. The advantage of the designed controller is that the states of the system can converge into a small neighourhood of zero in finite time, and simultaneously the given performance index can be minimized. The practical finite-time stability of the resulted closed-loop system is proven via Lyapunov stability theory. Finally, simulation results illustrate the effectiveness of the developed finite-time controller.

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Section: Figurementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Finite‐time attitude stabilization of rigid spacecrafts based on control Lyapunov functions

Zhang

2022

IET Control Theory & Appl

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“…where c 7 kc,1ρ∞,2 8c2ρ0,1 and c 8 kc,1ρ∞,3 8c5ρ0,1 . On one hand, when t f,1 ≤ t < t c , it is obtained from (8) that ρ1 (t) = 0 and, together with (42) and (44), that the derivative of…”

Section: Virtual Controller Designmentioning

confidence: 99%

“…In [40], the artificial potential function on the attitude constraints and the according constrained attitude stabilization control scheme are elaborately designed. In [41]- [42], the potential-function-based attitude stabilization control schemes are also developed and are robust to the external disturbances. A hierarchical controller is designed for the spacecraft attitude stabilization in [43], where the attitude constraints and the input saturation are both considered.…”

Section: Introductionmentioning

confidence: 99%

Constrained Attitude Control of Uncertain Spacecraft With Appointed-Time Control Performance

Jia

et al. 2023

IEEE Trans. Syst. Man Cybern, Syst.

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“…For example, the Cassini spacecraft [7] used a constraint monitor and an avoidance function to ensure sun exclusion constraints on some of its instruments. Potential field methods such as those presented in [8][9][10] rely on a repulsive input to steer the closed loop system trajectory away from the constraints. While effective for some simple motion planning problems, is it rather difficult to construct the appropriate control functions that impose more complex constraints or objectives.…”

Section: B Related Workmentioning

confidence: 99%

Optimal Science-time Reorientation Policy for the Comet Interceptor Flyby via Sequential Convex Programming

Preda¹,

Hyslop²,

Bennani³

2021

Preprint

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This paper introduces an algorithm to perform optimal reorientation of a spacecraft during a high speed flyby mission that maximizes the time a certain target is kept within the field of view of scientific instruments. The method directly handles the nonlinear dynamics of the spacecraft, sun exclusion constraint, torque and momentum limits on the reaction wheels as well as potential faults in these actuators. A sequential convex programming approach was used to reformulate non-convex pointing objectives and other constraints in terms of a series of novel convex cardinality minimization problems. These subproblems were then efficiently solved even on limited hardware resources using convex programming solvers implementing second-order conic constraints. The proposed method was applied to a scenario that involved maximizing the science time for the upcoming Comet Interceptor flyby mission developed by the European Space Agency. Extensive simulation results demonstrate the capability of the approach to generate viable trajectories even in the presence of reaction wheel failures or prior dust particle impacts.

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Saturated Attitude Control for Rigid Spacecraft Under Attitude Constraints

Cited by 29 publications

References 24 publications

Finite‐time attitude stabilization of rigid spacecrafts based on control Lyapunov functions

Finite‐time attitude stabilization of rigid spacecrafts based on control Lyapunov functions

Constrained Attitude Control of Uncertain Spacecraft With Appointed-Time Control Performance

Optimal Science-time Reorientation Policy for the Comet Interceptor Flyby via Sequential Convex Programming

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