Feedback tracking control of optimal reference trajectories for spacecraft relative motion

Vepa, Ranjan

doi:10.1016/j.asr.2022.02.005

Cited by 5 publications

(2 citation statements)

References 34 publications

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“…Regarding the problem of orbital maneuver planning using cold gas propulsion or electric propulsion, many studies use trajectory optimization methods based on continuous thrust; however, need to solve more complex nonlinear programming problems [10][11][12], and the amount of calculation is also huge. In order to simplify the calculation, the impulsive planning model can still be used in the modeling of the maneuvering trajectory planning problem based on the micro-thruster, but the corresponding constraints need to be proposed to achieve the impulsive approximation of the finite thrust [13].…”

Section: Introductionmentioning

confidence: 99%

A time-fuel hybrid optimal guidance for micro/nano satellite’s glideslope approach

Zeng,

Xu,

Chen

et al. 2024

J. Phys.: Conf. Ser.

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Aimed at the trajectory planning problem of micro/nano satellites’ approaching missions under multiple constraints, this paper proposes a V-bar glideslope maneuver optimization method considering both time and fuel consumption. A dual-objective trajectory optimization model is established based on the CW motion equation, considering the constraints of trajectory and impulse. The optimal solution set of the glideslope point position and maneuvering time is obtained by employing the NSGA2 algorithm. In order to reduce computational complexity, a method for simplifying trajectory optimization is proposed. By solving a constrained dual-impulse optimization problem, the feasible range of distance and transfer time between adjacent glideslope points are obtained, which transforms the constraint equations of the glideslope maneuver optimization into the search space of optimization variables. The problem is simplified to an unconstrained optimization problem. Finally, a simulation is conducted with the approaching mission of a typical micro/nano satellite. The results demonstrate that the proposed method can provide an optimal solution set considering both fuel and time consumption, offering a flexible maneuver planning strategy for on-orbit application.

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Section: Introductionmentioning

confidence: 99%

A time-fuel hybrid optimal guidance for micro/nano satellite’s glideslope approach

Zeng,

Xu,

Chen

et al. 2024

J. Phys.: Conf. Ser.

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“…To achieve an on-orbit service mission, the mission spacecraft must approach the target spacecraft first. As an important basis for proximity and docking operations, spacecraft relative motion has become a hot research topic in the space field, such as modeling and analysis of nonlinear spacecraft relative motion [6][7][8][9], estimation for spacecraft relative motion reachable set [10,11], stability analysis and study of spacecraft relative motion [12] and control for spacecraft relative motion [13,14], and so on. The design of spacecraft relative motion orbit has been widely used in space on-orbit service missions.…”

Section: Introductionmentioning

confidence: 99%

Application of the Relative Orbit in an On-Orbit Service Mission

Zhang²,

et al. 2023

Electronics

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To achieve an on-orbit service mission, the mission spacecraft must approach the target spacecraft first, which is based on the spacecraft’s relative motion. To enhance the safety and reliability of on-orbit service missions, the relative hovering orbit was proposed and needed to be studied further. A high-precision design method for hovering orbit is presented based on the relative dynamics model of spacecraft in this paper. Firstly, based on the stability analysis of the spacecraft relative dynamics model, a method to determine the initial value of periodic relative motion orbit is explored, and an example is given to verify the validity of the method. Then, through theoretical analysis, the formulae of control acceleration required during the hovering flying mission were put forward for both without considering perturbation and with considering J2 perturbation, and numerical simulations for hovering orbit were made to verify the feasibility of the approaches proposed. Simulation results show that the control acceleration curves are smooth, which indicates that the hovering flying mission is easier to achieve, and the control method based on sliding mode control theory is adopted for hovering control. The relative hovering method proposed can provide references in space on-orbit service missions for practical engineers.

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Trajectory Optimization and Feedback Control

Vepa

2024

Space Vehicle Maneuvering, Propulsion, Dynamics and Control

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Feedback tracking control of optimal reference trajectories for spacecraft relative motion

Cited by 5 publications

References 34 publications

A time-fuel hybrid optimal guidance for micro/nano satellite’s glideslope approach

A time-fuel hybrid optimal guidance for micro/nano satellite’s glideslope approach

Application of the Relative Orbit in an On-Orbit Service Mission

Trajectory Optimization and Feedback Control

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