Earth-Data-Ring

For an isolated seed aircraft at 1,000 kg with no cable/refrigeration/link-converter load, propulsion is 9.81 kW. With 5 kW computing and 1 kW auxiliaries, night demand is 15.81 kW. A 12 h night requires 189.72 kWh delivered. At an assumed 80% usable depth and 95% discharge efficiency, nameplate storage is 249.63 kWh; a 300 Wh/kg pack would weigh 832 kg. Pack specific energy is a design input, not a cell-level claim.

m_battery = t_nightP_night /(DoD × η_discharge × e_pack)

The allocated 200 kg pack supplies only 45.6 kWh, or 2.88 h at this demand. Substituting the larger battery raises propulsion. Keeping the non-battery mass at 800 kg and L/D fixed, solving m = 800 + 12(0.00981m + 6)/(0.8 × 0.95 × 0.30) gives about 2,307 kg, including 1,507 kg of batteries. This already violates the original mass case and requires about 687 kWh/day before charging losses, versus 408 kWh/day from the reference 12 h solar profile. It fails continuous isolated operation.

Sweep night duration 10–16 h, pack energy 200–400 Wh/kg, useful depth 0.7–0.9 and discharge efficiency 0.90–0.98. At fixed 15.81 kW, battery mass spans roughly 448–2,008 kg before iteration. Recharging also costs energy (e.g. divide delivered night energy by 0.95 × 0.95 for an assumed charge/discharge pair). Evaluate verified lower-power flight modes, load shedding, scheduled landing, larger collection area or explicitly external power. The complete ring can reduce routine overnight storage but still needs fault and recovery reserves.

For a uniformly illuminated circular aperture, a far-field diffraction screen is θ ≈ 1.22λ/D to the first null, with spot radius r ≈ θR. At 10 GHz (λ ≈ 0.030 m), D = 3 m and R = 1 km give θ ≈ 12.2 mrad and r ≈ 12.2 m; the far-field boundary 2D²/λ ≈ 600 m is satisfied. A receiver reaching the first null would be about 24.4 m wide, incompatible with treating it as a small accessory. The first-null radius is not 100% capture.

Across f = 5.8–10 GHz, D = 1–5 m and R = 0.1–10 km, solve Fresnel propagation when R is not well beyond 2D²/λ. Do not use a far-field link formula that predicts capture above unity. Aperture area, taper, polarization, atmospheric loss, beam jitter and spillover set the measured capture fraction. A 1 mrad pointing error shifts the beam 1 m at 1 km and 20 m at 20 km. An initial test target is ≤1 mrad RMS; receiver dimensions and measured spillover must determine the actual limit.

η_hop = η_DC→RF × η_{propagation/capture} × η_RF→DC × η_regulator
P_received = P_sent × ∏η_hop,i

An explicitly assumed link uses 0.80 × 0.80 × 0.90 × 0.95 = 0.5472. Ten, fifty and one hundred identical hops retain only 0.241%, about 8.1 × 10⁻¹²%, and about 6.5 × 10⁻²⁵%, respectively, before intermediate aircraft consume energy. Sweep the four factors over 0.60–0.85, 0.10–0.90, 0.65–0.90 and 0.90–0.98: one-hop efficiency spans about 3.5–67.5%. These independent ranges do not imply any selected combination is achievable. Microwave links suit measured local transfers and gaps; they cannot silently carry half a planet’s power through lossless relays. [3] [12]

For ground delivery, a hypothetical 20 km slant range with the same 3 m, 10 GHz aperture gives a first-null radius near 244 m. The example downlink factor 0.80 × 0.80 × 0.90 × 0.90 = 0.5184 includes DC–RF, path/capture, rectification and final conversion. It is not inferred from the small interaircraft receiver. Compute elevation, steering limits, ground footprint, rain loss, sidelobes and receiver area for each ground site. At 10 kW RF output and 80% source efficiency, the transmitter alone must reject 2.5 kW of heat.

For s = 1 km and μ = 0.05 kg/m, each assembly weighs 50 kg; a 40,000 km loop weighs 2,000 tonnes before additional distributed supports. Under a small-sag static approximation, horizontal tension H ≈ ws²/(8δ), w = μg. A 50 m sag gives H ≈ 1.23 kN from self-weight, before transverse drag, gusts and aircraft motion. At 10 km spacing, the same sag gives about 123 kN. Sag, curvature and allowable bend strain must be solved together. Distributed lifting surfaces may reduce endpoint loads but add mass, drag and controls.

A continuously moving ring cannot be treated as a set of independent aircraft tracks. Model wind shear, jet streams, route curvature, formation errors, cable oscillation, thermal contraction, icing at relevant altitudes, lightning, failure propagation and takeoff/landing/replacement. Validate tension, strain and control margins with flexible multibody dynamics and gust spectra.

The cold heat leak is 100 W per km in the reference, giving 2 kW of refrigerator input per node and 80 MW across the loop. For a 77 K cold stage rejecting to 300 K, ideal Carnot COP is 77/(300 − 77) ≈ 0.345; the assumed actual COP 0.05 is below that bound but still requires hardware evidence. Across q′ and COP ranges, refrigeration is 0.5–50 kW per 1 km assembly. Cooling hardware mass, coolant inventory, startup cooldown, vacuum maintenance and local failure recovery remain design constraints. [1] [2]

Zero conductor DC resistance does not eliminate refrigeration, resistive joints/interfaces, current-lead heat, converter loss or time-varying magnetic/AC losses. Separately meter these terms; cold joint heat adds to refrigerator load. Replace the small interface allowance with I²R_joint, current-lead heat and ripple-loss maps at actual through-current.

P = V_line-to-lineI; I_operating < I_c(T, B, strain), with declared margin

If a contiguous dark half consumes the reference 21.25 kW per node, each of two symmetric terminator feeds must carry about 212.5 MW before distribution losses. At 20 kV, that is 10,625 A per path. The illustrative 1 kA circuit carries only 20 MW and fails that aggregate demand. After loss of one path, the surviving route may face twice the transfer. At 200 kV the normal two-path current would still be about 1,063 A. Higher voltage, current capacity, insulation and superconductivity are separate choices; none is free in the mass budget.

Inductance, not DC resistance, limits current change. Test converter droop, current sharing, distributed modes, protection selectivity, stored magnetic energy (½LI²), quench detection, energy dumps and reclosure. Section isolation permits rerouting only if the remaining path and converters have capacity. Microwave bridges also need independently sufficient power and energy margins; they do not guarantee full service after a cut.

AI electricity becomes heat. Count AI, communication/control, converter and RF losses, warm interfaces, and refrigerator hot-side rejection Q_hot = Q_cold + P_refrigerator. The reference subtotal is 5 + 1 + 0.50 + 0.05 + 2.10 = 8.65 kW per node, before motor losses, absorbed sunlight and any active microwave source. It is a thermal subtotal, not extra electrical demand to add again.

Q_net = A_rad[εσ(T_rad⁴ − T_effective⁴) + h(T_rad − T_air)] − Q_absorbed

At ε = 0.9, T_rad = 320 K and effective radiative surroundings at 250 K, the radiative-only net flux is about 336 W/m²: 8.65 kW requires about 25.8 m² of emitting surface. This is an ideal screen with no absorbed sunlight and no convection credit. At 300–350 K with the same surroundings, it becomes roughly 40.4–15.3 m². Include Earth/sky view factors, solar absorption, air temperature, airspeed-dependent convection, pressure drop, heat exchanger mass and drag. Space-radiator performance cannot be copied directly into an atmospheric design. [7]

Calculate plane-of-array irradiance through the whole day, cloud/weather statistics, latitude, season, bank angle, shading and outages. True airspeed determines lift; winds determine ground track and crossflow. Altitude changes density, weather, solar input, cooling and approved operations. No universal permitted altitude is assumed. Connect the energy ledger to Earth Radiator; solar electricity reallocates incoming sunlight and must not be counted as newly created energy.