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the claim

Orbital rendezvous is achievable using continuous low-thrust ion engines.

the verdict
SUPPORTED
the evidence backs this
Recorded sources
5 sources for · 0 against

Counts group repeated records of the same source within each side. They do not measure evidence strength or source independence.

Is it true that orbital rendezvous is achievable using continuous low-thrust ion engines?

Yes. Orbital rendezvous using continuous low-thrust ion engines is well-supported by trajectory optimization research and operational mission planning.

Verdict: SUPPORTED · 5 sources for, 0 against · Last checked

The analysis

The retrieved papers consistently focus on trajectory optimization, control algorithms, and methods to achieve orbit raising and rendezvous using continuous low-thrust propulsion systems. No papers refute the claim, so the verdict is SUPPORTED.

Evidence for · 5
Minimum-time low-thrust many-revolution geocentric trajectories with analytical costates initialization
2021
This study develops an analytical costates initialization method specifically for obtaining minimum-time low-thrust geocentric rendezvous trajectories.
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Wu, D., Wang, W., Jiang, F., & Li, J. (2021). Minimum-time low-thrust many-revolution geocentric trajectories with analytical costates initialization. doi.org. https://doi.org/10.1016/j.ast.2021.107146

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More for · 4
Reinforced Lyapunov controllers for low-thrust lunar transfers
2024
This paper investigates low-thrust trajectory design and control laws that aid rendezvous operations.
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Holt, H., Baresi, N., & Armellin, R. (2024). Reinforced Lyapunov controllers for low-thrust lunar transfers. doi.org. https://doi.org/10.1007/s42064-024-0212-x

Initial Costate Approximation for Rapid Orbit Raising with Very Low Propulsive Acceleration
2024
This paper evaluates analytical procedures for continuous low-thrust orbit transfers and rendezvous trajectories.
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Quarta, A. (2024). Initial Costate Approximation for Rapid Orbit Raising with Very Low Propulsive Acceleration. doi.org. https://doi.org/10.3390/app14031124

Multiphase Homotopic Approaches for Best Solution to Low-Thrust Geocentric Trajectories
2024
This work presents multiphase homotopic approaches for optimizing low-thrust geocentric trajectories with rendezvous boundary conditions.
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Guo, X., Wu, D., & Jiang, F. (2024). Multiphase Homotopic Approaches for Best Solution to Low-Thrust Geocentric Trajectories. doi.org. https://doi.org/10.1109/TAES.2024.3370499

Starting modes of multidirectional electrodeless plasma thruster with closed ring-shaped gas discharge chamber.
2025
This paper discusses continuous propulsion maneuvers required for satellite operations, specifically highlighting satellite rendezvous.
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AI, S., AA, A., AD, P., PO, S., & VD, T. (2025). Starting modes of multidirectional electrodeless plasma thruster with closed ring-shaped gas discharge chamber.. doi.org. https://doi.org/10.1038/s41598-025-24995-5

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What does the evidence say?

The retrieved papers consistently focus on trajectory optimization, control algorithms, and methods to achieve orbit raising and rendezvous using continuous low-thrust propulsion systems. No papers refute the claim, so the verdict is SUPPORTED.

Receipt History
first checked04 Aug 2026
judged → SUPPORTED · 8504 Aug 2026
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