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arxiv: 2605.22682 · v1 · pith:O4HLG6IMnew · submitted 2026-05-21 · 🌌 astro-ph.EP

Energetic Feasibility of Redirecting Trans-Neptunian Objects onto Mars-Impacting Orbits: Continuous Thrust and Gravity Assist Trajectories

Ryszard Gabryszewski , Leszek Czechowski , Arkadiusz Hess This is my paper

Pith reviewed 2026-05-22 03:38 UTC · model grok-4.3

classification 🌌 astro-ph.EP
keywords trans-Neptunian objectsMars-impacting trajectorieslow-thrust redirectiongravity assistvolatiles deliveryorbital phase spaceKuiper Belt objects
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0 comments X

The pith

Redirecting trans-Neptunian objects to Mars-impacting orbits requires as little as 2.5 km/s velocity change with optimized low-thrust steering.

A machine-rendered reading of the paper's core claim, the machinery that carries it, and where it could break.

The paper examines the energy cost of moving volatile-rich bodies from the outer Solar System onto paths that collide with Mars. It compares three approaches in the two-body problem: simple inward spirals, thrust directions optimized by evolutionary algorithms, and hybrid paths that add one Neptune flyby. Pure spirals prove costly and slow, while steered thrusts that raise eccentricity reach impact conditions with modest total ΔV over a few centuries. Adding a gravity assist lowers the requirement further for well-chosen starting orbits. The results give a dynamical lower bound on the propellant budget needed to import outer solar system material to Mars.

Core claim

Time-dependent thrust steering optimized by global evolutionary algorithms drives classical Kuiper Belt and Scattered Disk objects onto Mars-impacting trajectories with ΔV of 2.5–3.2 km s⁻¹ over 380–540 years; a single Neptune encounter reduces this value still further in favorable cases.

What carries the argument

Time-dependent thrust-direction steering optimized via global evolutionary algorithms, which raises orbital eccentricity to produce Mars-impacting geometries.

If this is right

  • Selecting TNOs from favorable orbital regions makes controlled redirection feasible with modest velocity budgets.
  • Monotonic inward spirals are dynamically inefficient, demanding both high ΔV and millennia-long transfers.
  • Hybrid low-thrust plus single Neptune flyby paths can undercut the ΔV of direct optimized transfers.

Where Pith is reading between the lines

These are editorial extensions of the paper, not claims the author makes directly.

  • The same steering methods could be tested for delivering material to other inner planets or to the Moon.
  • Cataloguing real TNOs with orbits closest to the favorable phase-space regions would identify the lowest-cost candidates.
  • Incorporating variable thrust levels or multiple flybys might lower the bound further but requires new optimization runs.

Load-bearing premise

The two-body problem with a fixed maximum low thrust gives a true lower bound on ΔV even when real multi-body perturbations are present.

What would settle it

An n-body integration of a chosen TNO under the reported thrust profile that requires substantially more than 3.2 km s⁻¹ total ΔV.

Figures

Figures reproduced from arXiv: 2605.22682 by Arkadiusz Hess, Leszek Czechowski, Ryszard Gabryszewski.

Figure 1
Figure 1. Figure 1: Continuous thrust spiral transfer of the test body TB #1. The panels show the [PITH_FULL_IMAGE:figures/full_fig_p009_1.png] view at source ↗
Figure 2
Figure 2. Figure 2: Continuous thrust spiral trajectory in the XY plane projection - TB #1 test [PITH_FULL_IMAGE:figures/full_fig_p011_2.png] view at source ↗
Figure 3
Figure 3. Figure 3: Time evolution of the TB #1 test body orbital elements during the optimized [PITH_FULL_IMAGE:figures/full_fig_p013_3.png] view at source ↗
Figure 4
Figure 4. Figure 4: Optimized heliocentric trajectory of TB #1 under continuous thrust. The [PITH_FULL_IMAGE:figures/full_fig_p014_4.png] view at source ↗
Figure 5
Figure 5. Figure 5: Optimized characteristic velocity increments [PITH_FULL_IMAGE:figures/full_fig_p015_5.png] view at source ↗
Figure 6
Figure 6. Figure 6: Continuous thrust norm as a function of transfer times [PITH_FULL_IMAGE:figures/full_fig_p016_6.png] view at source ↗
Figure 7
Figure 7. Figure 7: Heliocentric trajectory of test body TB #1 projected onto the XY plane. The [PITH_FULL_IMAGE:figures/full_fig_p018_7.png] view at source ↗
Figure 8
Figure 8. Figure 8: Heliocentric trajectory of test body TB #2 projected onto the ecliptic XY plane. [PITH_FULL_IMAGE:figures/full_fig_p019_8.png] view at source ↗
read the original abstract

We assess the dynamical feasibility of redirecting small volatile-bearing trans-Neptunian objects (TNOs) onto Mars-impacting orbits using continuous low-thrust propulsion and a single gravity-assist encounter. The study considers two representative dynamical classes: classical Kuiper Belt--like and Scattered Disk--like initial orbits, and determines the minimum characteristic velocity increment $\Delta V$ required to drive the objects onto a Mars-impacting trajectory within a specified transfer time $\Delta T$. The dynamics is modelled in the two-body problem with a fixed maximum low thrust included, allowing the computed $\Delta V$ to represent a dynamical lower bound independent of specific propulsion-technical implementation. Three trajectory classes are investigated: (i) inward spiral transfer, (ii) time-dependent thrust-direction steering optimized via global evolutionary algorithms, and (iii) hybrid transfers combining low thrust with a single Neptune flyby. Pure spiral trajectories yield very high velocity expenditures ($\Delta V \gtrsim 22~\mathrm{km~s^{-1}}$) and millennia durations, confirming that monotonic inward migration is dynamically inefficient for TNO redirection. In contrast, optimized steering strategies systematically increase orbital eccentricity and achieve Mars-impacting geometries with $\Delta V \approx 2.5$--$3.2~\mathrm{km~s^{-1}}$ over 380--540 yr timescales. A single Neptune encounter further reduces the total $\Delta V$ in favourable cases, with minimum values falling below those of direct optimized transfers. These results establish a quantitative lower bound on the energy cost of importing volatiles from the outer Solar System to Mars, showing that controlled redirection is feasible under modest $\Delta V$ budgets when target bodies are chosen from favourable regions of orbital phase space.

Editorial analysis

A structured set of objections, weighed in public.

Desk editor's note, referee report, simulated authors' rebuttal, and a circularity audit. Tearing a paper down is the easy half of reading it; the pith above is the substance, this is the friction.

Referee Report

1 major / 0 minor

Summary. The manuscript assesses the dynamical feasibility of redirecting volatile-bearing trans-Neptunian objects onto Mars-impacting orbits via continuous low-thrust propulsion, with and without a single Neptune gravity assist. Using two-body Sun-centered dynamics with a fixed maximum thrust magnitude, the authors apply global evolutionary algorithms to optimize thrust steering and compare three classes of trajectories: pure inward spirals, time-dependent optimized steering, and hybrid low-thrust plus flyby cases. They report that optimized steering achieves Mars impact with ΔV ≈ 2.5–3.2 km s⁻¹ over 380–540 yr, with further reductions possible via Neptune encounter, establishing a quantitative lower bound on the energy cost when targets are selected from favorable orbital phase space.

Significance. If the central numerical results hold, the work supplies a concrete, quantitative lower bound on the ΔV cost of importing outer-Solar-System volatiles to Mars and demonstrates that optimized steering and a single gravity assist are far more efficient than monotonic spiral migration. The use of global evolutionary optimization to explore thrust-direction histories is a methodological strength that supports the reported feasibility under the stated modeling assumptions.

major comments (1)
  1. [Abstract] Abstract and modeling description: The central claim that the reported ΔV values constitute a dynamical lower bound independent of propulsion-technical details rests on the two-body Sun-centered dynamics plus fixed-maximum low thrust. This modeling choice omits multi-body perturbations from Jupiter, Saturn, and Uranus over 380–540 yr transfers and approximates the Neptune encounter via an instantaneous velocity rotation rather than a full three-body hyperbolic deflection with correct timing and post-flyby heliocentric adjustment. If these effects increase the minimum ΔV or render some optimized trajectories unrealizable, the claimed lower bound does not hold.

Simulated Author's Rebuttal

1 responses · 0 unresolved

We thank the referee for the constructive comments on our manuscript. Below we provide a point-by-point response to the major comment and indicate the revisions made to the manuscript.

read point-by-point responses

  1. Referee: [Abstract] Abstract and modeling description: The central claim that the reported ΔV values constitute a dynamical lower bound independent of propulsion-technical details rests on the two-body Sun-centered dynamics plus fixed-maximum low thrust. This modeling choice omits multi-body perturbations from Jupiter, Saturn, and Uranus over 380–540 yr transfers and approximates the Neptune encounter via an instantaneous velocity rotation rather than a full three-body hyperbolic deflection with correct timing and post-flyby heliocentric adjustment. If these effects increase the minimum ΔV or render some optimized trajectories unrealizable, the claimed lower bound does not hold.

    Authors: We thank the referee for this observation. Our analysis is performed strictly within the two-body Sun-centered problem with fixed maximum thrust, as stated in the manuscript, so that the computed ΔV constitutes a lower bound on the energy cost independent of propulsion-technical details such as variable thrust or efficiency. We acknowledge that the model omits perturbations from Jupiter, Saturn and Uranus over the long transfer times and approximates the Neptune encounter as an instantaneous velocity rotation. These simplifications were adopted to isolate the optimization of thrust steering and to obtain a clean baseline. In the revised manuscript we have updated the abstract and added clarifying text in the methods and discussion sections to state explicitly that the reported values are lower bounds under the two-body approximation and that multi-body effects and a full three-body flyby treatment lie outside the present scope. The numerical results and optimization methodology remain unchanged and valid within the stated model. revision: partial

Circularity Check

0 steps flagged

No circularity: results are direct outputs of numerical trajectory optimization

full rationale

The paper computes minimum ΔV via global evolutionary algorithms applied to the two-body equations of motion with a fixed maximum thrust magnitude. These ΔV values (≈2.5–3.2 km s⁻¹ for optimized steering, lower with Neptune encounter) are obtained as numerical solutions rather than being defined in terms of themselves or fitted to the target quantity. The modeling assumptions (two-body dynamics, constant max thrust, simplified flyby) are stated separately from the optimization results and do not create a self-definitional loop. No self-citations are invoked as load-bearing uniqueness theorems, and no ansatz or renaming of known results is used to generate the central quantitative bound. The derivation chain is therefore self-contained and independent of the reported outcomes.

Axiom & Free-Parameter Ledger

2 free parameters · 2 axioms · 0 invented entities

The central claim rests on numerical optimization within a simplified dynamical model; no new physical entities are postulated, but the two-body approximation and fixed-thrust assumption are load-bearing.

free parameters (2)
  • maximum low-thrust magnitude
    Fixed value chosen to compute a dynamical lower bound independent of specific engine technology.
  • transfer time ΔT
    Specified time window within which the Mars-impacting geometry must be achieved.
axioms (2)
  • domain assumption Two-body problem with Sun as central body governs the motion except during the single gravity-assist encounter
    Invoked to model orbital evolution for both direct and hybrid transfers.
  • domain assumption A single Neptune flyby can be arranged without additional cost beyond the low-thrust budget
    Used in the hybrid-transfer class to reduce total ΔV.

pith-pipeline@v0.9.0 · 5867 in / 1427 out tokens · 58588 ms · 2026-05-22T03:38:46.996024+00:00 · methodology

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