The ARGUS-PD/POD-7K architecture drawn as one orbital demonstrator, so the parts the papers screen separately can be seen together: a seven-kilometre driver of 1,000 × 7 m cells at 150 MJ each energised as a travelling wave, the solar generation and pulse-energy buffer that feed it, the converters and radiators that survive it, the magnetic vector control that points it, and the modular projectile whose deposited mass budget is the actual subject of Paper I. Pick a family member, drag to orbit, click any subsystem to label it, then fire. The camera rides the projectile down the bore and stays with it — the Moon at roughly a third of the way out and Mars at two-thirds swell and fall behind on their own, because every body sits at its true relative size on a log-compressed range — and holds on the body at intercept so the impact is the thing you watch. Every subsystem traces to Paper II, the projectile budget to Paper I, and the attitude loop to the geomagnetic companion paper.
Illustrative & conceptual — not to scale, not a buildable design. A hypothetical planetary-defence research demonstrator in orbit (the series declares no operational altitude; geometry and placement are schematic). Only the projectile mass allocations (deposited budget, total 0.300 kg reference) and the 1,000-cell / 32-face / 0.505 m-collar figures are quantitative. No operational targeting, fire-control, pulsed-power, coil, capacitor or rail engineering is shown or implied — the on-screen auto-aim and lead-corrected shots are game-style illustration of the papers’ pointing hierarchy, not a firing solution.
The engagement scenario is this visualiser’s invention, not a finding of the papers. An inbound body on an Earth-crossing track, a multi-shot campaign, cumulative deflection and a closing sequence of intercepts are all staged here to make the geometry legible. The papers claim none of them: Paper I §8 places “all Earth-intersecting states outside the intended research envelope” and states that delivered kinetic energy is calculable while useful deflection is not; Paper III §7.2 makes no E3 or E4 claim; and no salvo, warning window or intercept range appears anywhere in the series. 0.5 AU is a screening quotient — the normalising range R/v used to compare family members (Paper I §6.2) — not a stated intercept distance; it is drawn here as a marked gate for exactly that reason. Ranges are log-compressed (Moon 384,400 km → Mars ~54.6e6 km → target 0.5–1.5 AU) so all of it fits one frame; body diameters are true relative to each other.
◉ TARGET CAM
orbital demonstrator · illustrativedrag · scroll · click a part
0 km/sready◐ auto-aim ON · slewing bore onto asteroid
⚑ Forces
accelerating Lorentz force (down the bore) drive-cell field forces vector-control steering force (exit trim) geomagnetic field B (Earth's field · external/inertial) commanded dipole m (magnetorquer loop axis) slew torque τ = m × B (under-actuated: ⟂ B · slow) asteroid's Earth-bound track deflected track — misses Earth vector-control authority: ±1.5° exit-steering conereachable radius ≈ range·tan1.5°Cone × range sets the reachable impact footprint (illustrative control-authority envelope — not fire-control).
Earth 12,742 km — ≈1,820× the structure (off scale ↑)
Driver 7,000 m (reference)
ISS ~110 m
target ~100 m
projectile 0.5 m
Deflection — planetary defence (illustrative)
≈ — flight windows in a notional 1-yr warning
each imparts Δv ≈ —
Repeated small nudges walk it off an Earth-bound track — not one Hollywood hit. Illustrative — not operational.
Subsystems
Click to inspect · grounded in Paper II
Projectile (iso-energy family)
Target body
Select a subsystem to see its role and provenance.
Provenance: driver = 1,000 × 7 m cells, 150 MJ/cell (Paper II §2.3); projectile = 32-gon core (vertex Ø 0.050 m, 0.150 kg diamond-equivalent) with a 0.200 m² coupling collar (0.505 m equivalent Ø, 0.090 kg, 0.45 kg/m², ~21.4 MN) — a ~10:1 collar:core diameter ratio (Paper I §2). Deposited budget total 0.300 kg. Subsystems from Paper II's integrated architecture (solar generation & long-duration buffer; fast-pulse store discharging 428.571 GJ admitted energy through the ~14 ms launch, of which ~150 GJ becomes projectile kinetic energy at the assumed 35% efficiency; converters; radiators). Family: iso-energy 150 GJ set (reference_family.csv); members are illustrative material tiers — the 0.150 kg diamond-equivalent core is the Paper I reference (diamond's density caps its mass at this geometry), heavier members are dense-metal (tungsten-class) penetrators of broadly similar size, since the papers fix mass and velocity but not material. Impact per Paper I §8 — delivered energy is calculable; useful deflection is not. Earth imagery: NASA Earth Observatory (public domain); Mars & Sun textures courtesy PlanetPixelEmporium (James Hastings-Trew); asteroid + surface-view regolith map from three.js examples (NASA/USGS); smoke/vapour particle sprites from OpenGameArt.org (CC0/public domain); station surface textures (photovoltaic cells, metal plates, brushed metal) and the cracked-ground texture used by the stage-2 destruction from ambientCG.com (CC0). The ⛰ surface view is an illustrative phenomenological staging of hypervelocity impact regimes (surface energy coupling vs deep momentum coupling) — not a hydrocode result. Schematic and not to scale.