Astroship models laser-ablation redirection of near-Earth asteroids — turning their mass into propellant-free transit, natural radiation shielding, and an in-situ resource depot for missions beyond Mars.
A textured 3D reconstruction built from the real mission imagery below. Drag to rotate, scroll to zoom — or tap any thumbnail below to switch target.
A simplified heliocentric model plotting Earth, Mars, Jupiter and all thirteen candidates by their real semi-major axis and eccentricity from the JPL Small-Body Database. Scrub the timeline 2026–2050; treat spacing and phase as illustrative — this is not a JPL HORIZONS ephemeris.
Tangential Δv from continuous ablation is converted to a semi-major-axis shift via Δa = 2a²vΔv/μ. Small, low-mass targets shift visibly; large ones barely move — that contrast is the physics.
Adjust laser power, coupling coefficient and ablation duration to see reaction thrust, acceleration and accumulated Δv for the header's selected target — live, in SI units.
Top-down view of the target's orbit around the Sun. The dashed line is the unmodified orbit; the solid colored line is the orbit after the semi-major axis shift Δa produced by the settings above.
Thirteen tracked near-Earth objects, filterable by spectral class. Thumbnails marked REAL IMAGERY are unretouched frames from the cited spacecraft or radar campaign; objects without a resolved close-up show a placeholder.
Every real spacecraft encounter behind the data on this platform, in chronological order — from the first asteroid landing to the missions still ahead.
Order-of-magnitude comparison for a Mars-class deep-space cargo transit, using published dry-mass and Δv figures for reference chemical vehicles.
| METRIC | ASTROSHIP CONCEPT | CHEMICAL ROCKETS | ADVANTAGE RATIO |
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Core astrodynamics and ablation-propulsion relations used throughout this platform's live calculators.
Momentum coupling coefficient C_m converts incident laser power directly into reaction thrust from the plasma plume.
Mass ejection rate scales with laser power and inversely with the specific ablation energy of the target regolith.
Combining coupling efficiency and ablation energy yields effective specific impulse, typically 1500–3500 s for silicate/carbonaceous regolith.
For ejected mass Δm much smaller than asteroid mass M_A, cumulative ablation produces a gradual, controllable orbital shift.
Heliocentric speed v at distance r depends on semi-major axis a and μ = 1.327×10¹¹ km³/s². A perihelion burn maximizes aphelion change (Oberth effect).
Beer–Lambert attenuation through regolith depth x; a few meters of cover reduce GCR/SPE dose to habitable levels.
Used to derive each body's orbital period from its semi-major axis for the timeline simulator.
Computed from aphelion Q and perihelion q distances, both taken directly from the JPL Small-Body Database.
A weak, continuous thermal recoil force from anisotropic re-radiation of absorbed sunlight. Drift rate scales roughly as da/dt ∝ 1/(ρD) — inversely with bulk density ρ and diameter D — so it matters most for small bodies like VK184, shifting the orbit by thousands to tens of thousands of km over decades. It is a perturbation to account for, not a propulsion mechanism.
This platform's methodology is grounded in an independent student research project analyzing 2007 VK184...