Optimal low-thrust linearized elliptic orbit rendezvous considering the communication window

Lin, Xuemei; Zhang, Gang; Ma, Huidong

doi:10.1016/j.actaastro.2022.05.004

Cited by 5 publications

(2 citation statements)

References 25 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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show abstract

“…Extensive research and classification of low-thrust low-energy transfers between low Earth and lunar orbits using indirect optimal control are thoroughly examined in [7]. On the other hand, direct methods rely on discretization/parametrization and transform the optimal control problem into a nonlinear programming problem [8][9][10] to solve transfer [11], rephasing [12], and rendezvous [13][14][15][16] problems. Both approaches struggle with significant sensitivity to the initial guess, lead to numerous local extrema, and incur high computational costs during the optimization process.…”

Section: Introductionmentioning

confidence: 99%

Minimum-Energy Transfer Optimization between Near-Circular Orbits Using an Approximate Closed-Form Solution

Suslov,

Shirobokov,

Tselousova

2023

Aerospace

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This paper explores the use of the averaging method in the optimal control problem related to the multirevolution orbital transfer of a spacecraft with low-thrust capabilities. The regularized equations of motion are expressed using modified equinoctial elements with the eccentric longitude as a fast variable. The control function is represented as a Fourier series relative to the eccentric longitude. The classical averaging technique’s usage results in the averaged trajectory depending only on a limited number of optimization parameters. Moreover, when transferring between near-circular orbits, the averaged motion can be estimated using analytical formulas. As such, the optimal multiorbit flight problem is simplified to nonlinear programming with fewer parameters, thereby accelerating the optimal solution’s derivation. Two practical examples illustrate the technique’s application: orbital transfer near the geostationary orbit and circular orbit raising maneuver. The solutions derived are compared with Pontryagin extremals.

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Optimal Multi-impulse Elliptic Rendezvous Using Stagnation Escaping Whale Optimization Algorithm

Shim,

Kim,

Lee

2024

Int. J. Aeronaut. Space Sci.

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Optimal low-thrust linearized elliptic orbit rendezvous considering the communication window

Cited by 5 publications

References 25 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

Minimum-Energy Transfer Optimization between Near-Circular Orbits Using an Approximate Closed-Form Solution

Optimal Multi-impulse Elliptic Rendezvous Using Stagnation Escaping Whale Optimization Algorithm

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