Analytical solutions to the matrix inequalities in the robust control scheme based on implicit Lyapunov function for spacecraft rendezvous on elliptical orbit

Tian, Xiwen; Jia, Yingmin

doi:10.1049/iet-cta.2017.0176

Cited by 8 publications

(8 citation statements)

References 27 publications

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“…Proof: The two-impulse trajectory subjected to fixed initial (r i ) and final (r i+1 ) positions with a fixed time of flight (∆t i+1,i ), has a position vector r at t that is introduced previously in (10). From (10), the squared 2-norm of r can be written as…”

Section: A Trajectory Boundednessmentioning

confidence: 99%

“…Optimal impulsive approaches based on the primer vector solutions are investigated in [6]- [8]. Gao et al discussed the robust H ∞ control of relative motion [9], while solutions to the matrix inequalities are proposed by Tian and Jia [10]. Mesbahi and Hadaegh studied the formation flying control via graphs, matrix inequalities, and switching [11].…”

Section: Introductionmentioning

confidence: 99%

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On the Impulsive Formation Control of Spacecraft Under Path Constraints

Shakouri

2019

IEEE Trans. Aerosp. Electron. Syst.

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This paper deals with the impulsive formation control of spacecraft in the presence of constraints on the position vector and time. Determining a set of path constraints can increase the safety and reliability in an impulsive relative motion of spacecraft. Specially, the feasibility problem of the position norm constraints is considered in this paper. Under assumptions, it is proved that if a position vector be reachable, then the reach time and the corresponding time of impulses are unique. The trajectory boundedness of the spacecraft between adjacent impulses are analyzed using the Gerschgorin and the Rayleigh-Ritz theorems as well as a finite form of the Jensen's inequality. Some boundaries are introduced regarding the Jordan-Brouwer separation theorem which are useful in checking the satisfaction of a constraint. Two numerical examples (approximate circular formation keeping and collision-free maneuver) are solved in order to show the applications and visualize the results.

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Section: A Trajectory Boundednessmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

On the Impulsive Formation Control of Spacecraft Under Path Constraints

Shakouri

2019

IEEE Trans. Aerosp. Electron. Syst.

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“…As an example, besides the methodologies based on closed-loop control techniques, similar to the approaches that rely on the Lyapunov function (Tian and Jia, 2017), another solution is to apply specific modifications to the variables or the problem formulation for constraints satisfaction. Shape-based techniques and control transformation (Ayyanathan and Taheri, 2022) are in this category of methods.…”

Section: Introductionmentioning

confidence: 99%

Trajectory optimization of space vehicle in rendezvous proximity operation with evolutionary feasibility conserving techniques

Shirazi

Ceberio

Lozano

2023

Engineering Applications of Artificial Intelligence

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“…Over the last few decades, several robust control methodologies have been explored for solving the attitude regulation problem, 8‐14 however these strategies have only shown the asymptotic stability of the system, which is considerably less desirable than finite‐time convergence. The infinite settling time associated with asymptotic stability becomes impractical for a real‐time operation of many high‐risk missions.…”

Section: Introductionmentioning

confidence: 99%

Fault‐tolerant finite‐time adaptive higher order sliding mode control with optimized parameters for attitude stabilization of spacecraft

Amrr

Sarkar

Banerjee

et al. 2021

Intl J Robust & Nonlinear

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This article considers the problem of attitude regulation of rigid spacecraft under the effect of inertial ambiguity, exogenous disturbances, input saturation, and actuator uncertainties. In this regard, an adaptive second‐order sliding mode control (ASOSMC) is designed to provide robustness against the lumped disturbances (the combination of uncertainties and faults). The ASOSMC presents a two‐fold advantage over conventional SMC. The use of adaptive law eliminates the assumption of a priori knowledge on the upper bounds of the disturbances. Further, the SOSMC methodology alleviates the high‐frequency chattering in the input without compromising robustness. The theoretical analysis under the proposed strategy guarantees the convergence of sliding surface and system states to the origin in a finite‐time. Besides, this work also resolves the inbuilt problem of unwinding in the quaternion‐based attitude representation. Further, the nominal parameters of the proposed control law are optimized offline using an ant lion optimization method. The numerical simulation validates the effectiveness of the proposed controller by comparing its performance with the other existing controllers.

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Analytical solutions to the matrix inequalities in the robust control scheme based on implicit Lyapunov function for spacecraft rendezvous on elliptical orbit

Cited by 8 publications

References 27 publications

On the Impulsive Formation Control of Spacecraft Under Path Constraints

On the Impulsive Formation Control of Spacecraft Under Path Constraints

Trajectory optimization of space vehicle in rendezvous proximity operation with evolutionary feasibility conserving techniques

Fault‐tolerant finite‐time adaptive higher order sliding mode control with optimized parameters for attitude stabilization of spacecraft

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