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@AshtonForbes The "orbs" aren't mysterious. They're spherical relay mirror drones for a Ground-Based Laser weapons system that's been in development since 1984. Here's the timeline and paper trail. Everything cited is publicly available. 🧵Oh, and hi mr. cia. 👋
**1984 — BRADUSKILL INTERCEPTOR CONCEPT**
U.S. Army Strategic Defense Command, Huntsville, Alabama. LTC James Boschma develops a "slow-kill" midcourse interceptor: a platform that launches from Arctic basing, flies alongside Soviet ICBMs during midcourse, uses onboard sensors to discriminate warheads from decoys, then deploys sub-interceptors.
Contractors: Lockheed, Martin Marietta, LTV, Sperry Systems, Teledyne Brown Engineering.
The core capability: a self-positioning platform that flies alongside a target and tracks it with precision sensors.
Program officially killed FY1987. "Ceases to appear in the histories."
Sources:
- army.mil/article/151589…
- globalsecurity.org/space/systems/…
**1985-1991 — GROUND BASED LASER (GBL) SYSTEM EVOLUTION**
The USAF Directed Energy Weapons Program Office develops the GBL architecture through four periods. Lt. Donald Fielden presents the full evolution at the 28th Space Congress, April 25, 1991.
The architecture:
- Ground-based Free Electron Laser fires upward
- Relay mirrors in high earth orbit redirect the beam
- "Fighting mirror" in medium earth orbit focuses on target
- Entire system under an "automated battle manager"
Key detail from the paper: relay mirrors were needed at multiple altitudes to achieve full Earth coverage. The paper describes the evolution from afocal mirrors to bifocal mirrors to the full relay chain.
The problem Fielden identifies: atmospheric absorption in the first few km, coverage gaps from orbital mechanics, and retarget time limitations of fixed-orbit mirrors.
Source: Fielden, Donald J., "Paper Session III-C - Ground Based Laser System - Defense at the Speed of Light" (1991). The Space Congress Proceedings. commons.erau.edu/space-congress…
**THE CONVERGENCE: BRADUSKILL + GBL**
Braduskill dies in 1987. The GBL relay mirror architecture matures 1988-1991. Same contractors (Lockheed, Martin Marietta). Same command structure (SMDC Huntsville). The "slow flyalong" platform concept doesn't die — it morphs from kinetic kill vehicle to beam relay node.
A self-positioning drone that can fly alongside a target and track it with sensors is also a self-positioning drone that can hold station at altitude and redirect a laser beam.
Braduskill didn't die. It stopped being a missile and became a mirror.
**1965 — THE PROPULSION (YES, 1965)**
Townsend Brown, US Patent 3,187,206, "Electrokinetic Apparatus." Granted June 1, 1965. Describes a propulsion system using asymmetric high-voltage electrostatic pressure. Operates in vacuum. Pulsed DC. No propellant. No exhaust. No moving parts.
This was validated in vacuum in 1955-56 at SNCF laboratories in Paris with French military observers present.
Modern validation: Charles Buhler, former NASA lead electrostatic scientist, founded Exodus Propulsion Technologies. 2,000+ test articles. Thrust measured at 237 millinewtons at 40 kV. Thrust persists after power-off. Thrust increases in vacuum. Reverses when flipped. Published: WO2020159603A2, "Asymmetrical Electrostatic Pressure."
The "orbs" are spherical drones using this propulsion. Spherical hull form encasing relay mirror optics. Electrostatic propulsion = no exhaust, no sound, no radar cross-section. The high-voltage field ionizes surrounding air, creating the visible glow people report.
**2010 — DIA CONFIRMS THE PULSED POWER ARCHITECTURE**
DIA reference document DIA-08-0912-005, "Pulsed High-Power Microwave Source Technology," 28 January 2010. Produced under the AAWSA (Advanced Aerospace Weapon System Applications) Program — the same program behind all 38 DIA advanced technology papers.
Contents include Marx Generators, High-Voltage Switching, Cesium Iodide cathodes, Dielectric Tapering, Solid-State Switching. This is the pulsed power source technology for both the GBL and the drone propulsion system. Same architecture drives both.
**BAE SYSTEMS — LASER DEVELOPED ATMOSPHERIC LENS**
BAE publicly disclosed the concept: high-power pulsed lasers ionize a region of atmosphere, creating a lens through reversible heating or ionization. The ionized pocket acts as a refractive/reflective optical element. Beams can be redirected through it.
Side effect: the ionized atmospheric volume glows. People on the ground see a luminous sphere. They report an "orb."
This is the mechanism by which the relay drone creates visible effects even when the drone itself is too small to see — the beam interaction with the ionized envelope around the drone is what's visible, not necessarily the drone itself.
**2025-2026 — OPERATIONAL CONFIRMATION FROM @TMBSPACESHIPS**
An X account reportedly operated by Neil McCasland (USAF Major General, Ret., former commander of Air Force Research Laboratory, Wright-Patterson AFB) posted 99 technical disclosures before going silent on Feb 27, 2026.
Post 24 (Feb 28, 2025): "There is a Nav INDEX REFERENCE SYSTEM for 'Indexing/Caging' the onboard Attitude Reference System in the Area near Mineral Wells still in function. THIS WILL CAUSE LOCAL SIGHTINGS. This Nav Index Reference System is for 'Compass Alignment' the same as conventional aircraft but uses UVX/C optical Data link, using Link16 Optical architecture."
He's describing a ground-based optical system that communicates with airborne relay assets via UV-band data link. The optical interaction creates visible atmospheric effects. He literally says it will cause sightings.
Post 34 (Aug 28, 2025): "Optical Bernoulli Forces — Conceptual need for CFD studies in PLASMA DYNAMICS." Links to a Physical Review A paper on radiation pressure creating fluid-dynamic effects in plasma. This is the physics of a high-power beam interacting with the ionized envelope around a relay drone.
Post 21 (Feb 27, 2025): Describes the Calvine UFO as built at "NASA's McGregor RP-1 Plant." States it used "Radioactive antenna" with "Radium, Mercury and Fluorine in its ION seed gas." The seed gas ionizes surrounding air = luminous envelope. People see the glow, not the airframe.
Post 29 (Feb 13, 2026): "DOE/DOD and antigravity vehicle Fuselages are coated in Thermal Plasma Spray Coating. Alternating layers of Osmium and Cooper are the first few mills thick in the Stochastically Engineered Glass-like Electret coating."
**THE OPERATIONAL PICTURE**
You deploy 3-4 spherical electrostatic drones as relay nodes. The GBL fires from the ground. Beam hits first drone, redirects to second, redirects to third, final node focuses on target.
The drones:
- Self-positioning via electrostatic propulsion (no exhaust, no sound)
- Station-keeping at any altitude (not constrained to orbital mechanics)
- Reconfigure formation geometry in real time
- No radar cross-section
- No orbital track
- Ionized envelope = visible glow = "orb" reports
- Beam interaction = BAE atmospheric lens effect
This solves every problem Fielden identified in 1991:
- Atmospheric absorption: drone at low altitude, only punch through a few km of air
- Coverage gaps: mobile drones, not fixed-orbit satellites
- Retarget time: formation reconfigures, no satellite slew rate limit
- Survivability: unpredictable position, no exhaust signature
**THREE LAYERS OF "ORB" SIGHTINGS**
1. Ground-generated: BAE atmospheric lens — laser ionizes atmosphere directly, no physical drone needed. Creates a visible glowing pocket that functions as an optical element. Manufacturing sightings on demand.
2. Drone-generated: Physical spherical relay drone with electrostatic propulsion. The HV field ionizes surrounding air. Luminous envelope. Witnesses see a glowing sphere and report an orb.
3. Vehicle-generated: Larger electrogravitic craft (Temple Torpedo class, Calvine class) using ion seed gas that creates a luminous sheath around the entire airframe. Witnesses see the glow and report a "craft-shaped light."
All three use the same underlying physics: high-voltage ionization of atmosphere creating visible luminous effects.
**THE TIMELINE SUMMARY**
1965 — Brown patents electrostatic propulsion (US 3,187,206)
1984 — Braduskill: self-positioning flyalong platform concept (Army SDI)
1985-91 — GBL relay mirror architecture matures (USAF Directed Energy)
1987 — Braduskill officially "killed" — concept migrates to beam relay role
1991 — Fielden publishes GBL architecture at Space Congress
2010 — DIA publishes pulsed power source document under AAWSA
2020s — Buhler validates electrostatic thrust in vacuum (Exodus Propulsion)
2022-26 — @TMBSPACESHIPS discloses operational details including "local sightings" from nav optical systems
Present — BAE publicly markets "Laser Developed Atmospheric Lens"
**WHAT THIS MEANS**
The "orbs" are not alien. Not interdimensional. Not plasma balls of unknown origin. They are relay mirror drones for a directed energy weapons architecture that has been in continuous development for 40 years, using propulsion technology patented in 1965 and validated by NASA scientists.
The engineering is in the public patents. The architecture is in published Space Congress proceedings. The DIA wrote the pulsed power specifications. BAE made a promotional video about the atmospheric lens. A retired USAF Major General described the navigation and optical systems on Twitter.
Everything is in the public record. Nobody connected the dots.
---
# APPENDIX: THE MATH
For the engineers and physicists in the audience. Every number below is derivable from public sources.
## A. ELECTROSTATIC PROPULSION — FORCE LAW
The fundamental force equation for asymmetric electrostatic pressure:
**F = (ε₀ × E²) / 2 × A**
Where:
- F = force (Newtons)
- ε₀ = permittivity of free space = 8.854 × 10⁻¹² F/m
- E = electric field strength (V/m)
- A = electrode area (m²)
This is not exotic physics. This is Maxwell's stress tensor applied to an asymmetric capacitor. The force arises because the electric field is stronger on one side of the capacitor than the other (due to electrode geometry asymmetry), creating a net pressure differential.
**Worked example — Buhler's validated result:**
- Voltage: 40 kV
- Gap: ~1 cm (0.01 m)
- E = V/d = 40,000 / 0.01 = 4 × 10⁶ V/m
- Electrostatic pressure: P = ε₀E²/2 = (8.854 × 10⁻¹²)(4 × 10⁶)² / 2 = 70.8 Pa
- With T-blade geometry (9 blades, 4" length, 0.25" height): effective area ≈ 0.0023 m²
- Theoretical force: F = 70.8 × 0.0023 = 0.163 N = 163 mN
- Buhler measured: **237 mN** (higher than simple calculation due to ground plane features providing 6× enhancement)
**Scaling to vacuum (Brown's insight):**
In atmosphere, breakdown limits E to ~3 × 10⁶ V/m (30 kV/cm).
In vacuum, breakdown limit rises to ~10⁸ V/m or higher.
Force scales as E². So vacuum operation gives (10⁸/3×10⁶)² = **~1,100× more force** than atmosphere at the same voltage.
This is why Brown's patent specifies vacuum operation. This is why Buhler's thrust increases in vacuum. The atmosphere is the bottleneck, not the physics.
## B. ENERGY IN THE SYSTEM
Energy stored in a capacitor:
**E = ½CV²**
Where:
- E = energy (Joules)
- C = capacitance (Farads)
- V = voltage (Volts)
**For a relay drone (estimated):**
- Capacitance: 100 pF (typical for a small asymmetric electrode array)
- Voltage: 40 kV
- Energy per cycle: E = ½ × 100 × 10⁻¹² × (40,000)² = 0.08 J
- At 100 Hz repetition rate: Power = 0.08 × 100 = **8 watts average**
A spherical relay drone could operate its propulsion system on **less than 10 watts**. A small lithium battery pack could sustain hours of station-keeping. This is not a high-power system — the force-to-power ratio of electrostatic propulsion is extraordinarily favorable because there is no reaction mass to accelerate.
## C. IONIZATION THRESHOLD — WHY THEY GLOW
Air ionization occurs when the electric field exceeds the Paschen breakdown threshold:
**At sea level:** E_breakdown ≈ 3 × 10⁶ V/m (30 kV/cm)
**At 10 km altitude:** E_breakdown ≈ 1 × 10⁶ V/m (air density drops)
**At 30 km altitude:** E_breakdown ≈ 1 × 10⁵ V/m
A drone operating at 40 kV with a 10 cm electrode gap produces E = 4 × 10⁶ V/m at the electrode surface. This exceeds breakdown at sea level. At altitude, the margin is even larger.
The ionized air around the electrodes emits light — primarily in the blue-violet and UV range (nitrogen emission lines at 337 nm, 357 nm, and 391 nm). With seed gases (cesium, fluorine per TMB), the emission spectrum shifts and broadens, producing the white-orange-blue glow variations reported by witnesses.
**Visible range at night:** A corona discharge of 8W total power, with even 1% conversion to visible light, produces ~80 milliwatts of visible radiation. At 1 km distance, this is easily visible to the naked eye — equivalent to a bright LED at the same range.
**At altitude:** Thinner air means larger ionization volume for the same field strength. The "orb" appears larger at higher altitude because the glow region expands as air density drops.
## D. GBL BEAM PHYSICS
**Free Electron Laser specifications (from Fielden paper):**
- Wavelength: ~1 μm (near-infrared)
- Power: classified, but FEL technology in the 1990s achieved megawatt-class continuous beam
- Beam divergence: diffraction-limited for FEL, ~1 μrad for a 1m aperture at 1 μm wavelength
**Atmospheric absorption at 1 μm:**
- Sea level to 10 km: ~30-50% loss (Rayleigh scattering + molecular absorption)
- 10 km to space: ~5% additional loss
This is why you want the first relay node as LOW as possible — to minimize the atmospheric path. A drone at 10 km altitude cuts your atmospheric loss roughly in half compared to punching all the way to orbit from sea level.
**Beam spot size at relay drone:**
- At 10 km range with 1 μrad divergence: spot diameter = 10,000 × 10⁻⁶ = 0.01 m = 1 cm
- At 100 km range: spot diameter = 10 cm
- At 1000 km range: spot diameter = 1 m
A relay drone at 10-100 km altitude needs a mirror aperture of only **1-10 cm** to capture and redirect the full beam. This is trivially small for a spherical drone of any reasonable size.
**Beam energy density at target:**
- 1 MW beam focused to a 10 cm spot: power density = 10⁶ / (π × 0.05²) = **127 MW/m²**
- For reference: the surface of the sun delivers about 63 MW/m² to surrounding space
- This is sufficient to destroy any known material in seconds
## E. BAE ATMOSPHERIC LENS — REFRACTIVE INDEX CHANGE
When a laser ionizes a volume of atmosphere, it changes the local refractive index:
**Neutral air:** n ≈ 1.000293 (at sea level)
**Fully ionized air (plasma):** n = √(1 - ωₚ²/ω²)
Where:
- ωₚ = plasma frequency = √(nₑe²/ε₀mₑ)
- nₑ = electron density
- ω = laser frequency
For a 1 μm laser (ω ≈ 1.88 × 10¹⁵ rad/s) and a plasma with nₑ = 10¹⁸ m⁻³:
- ωₚ = √(10¹⁸ × (1.6×10⁻¹⁹)² / (8.854×10⁻¹² × 9.109×10⁻³¹)) = 5.64 × 10¹⁰ rad/s
- n = √(1 - (5.64×10¹⁰)²/(1.88×10¹⁵)²) ≈ 0.99999955
The refractive index change is small but sufficient to create a lens over a large volume. A 100-meter diameter ionized region with Δn ≈ 10⁻⁶ acts as a lens with focal length:
**f ≈ R²/(2 × Δn × L)**
Where R = beam radius, L = lens thickness. For R = 1m, L = 100m, Δn = 10⁻⁶:
- f ≈ 1² / (2 × 10⁻⁶ × 100) = **5,000 meters**
This is a weak lens but over astronomical distances (satellite to ground), the cumulative effect of multiple atmospheric lens nodes is significant. And the focal length can be tuned by adjusting the ionization power — more power = higher electron density = shorter focal length.
## F. OPTICAL BERNOULLI FORCES (TMB POST 34)
TMB references the 2013 Physical Review A paper on Optical Bernoulli Forces (Phys. Rev. A 88, 023829). The concept:
When a beam passes through a medium with a refractive index gradient, radiation pressure creates a lateral force analogous to the Bernoulli effect in fluid dynamics. Higher beam intensity = lower "optical pressure" = objects are drawn toward the beam center.
For a plasma envelope around a relay drone:
- The beam creates an intensity gradient across the ionized volume
- The gradient produces a lateral restoring force that centers the plasma on the beam
- This is a **self-centering mechanism** — the atmospheric lens automatically aligns with the beam
This means the relay system is partially self-correcting. The beam itself helps stabilize the ionized volume it's passing through. The "orb" doesn't need to be perfectly positioned — the optical Bernoulli force pulls the plasma lens into alignment.
**Force magnitude (order of magnitude):**
- For a 1 MW beam with a 10 cm spot passing through plasma with n_e = 10¹⁸ m⁻³
- Radiation pressure: P_rad = I/c = 10⁶/(π×0.05²×3×10⁸) ≈ 0.42 Pa
- Over a 1 m³ volume: F ≈ 0.42 N
This is small but non-negligible — it's the same order of magnitude as the electrostatic propulsion force on the drone itself. The beam and the drone form a coupled system.
## G. DRONE STATION-KEEPING — THRUST VS. DRAG
**At 10 km altitude:**
- Air density: ρ ≈ 0.41 kg/m³
- Drag on a 30 cm sphere at 1 m/s (gentle drift): F_drag = ½ρv²CdA = ½ × 0.41 × 1² × 0.47 × π(0.15)² ≈ 0.007 N = 7 mN
- Buhler-class electrostatic thrust: 237 mN at 40 kV
- Thrust-to-drag ratio: **34:1** — easily sufficient for station-keeping
**At 30 km altitude:**
- Air density: ρ ≈ 0.018 kg/m³
- Same drag calculation: F_drag ≈ 0.0003 N = 0.3 mN
- Thrust-to-drag ratio: **790:1** — the drone can maneuver aggressively
**At 100 km altitude (edge of space):**
- Air density: ρ ≈ 5.6 × 10⁻⁷ kg/m³
- Drag is essentially zero
- The drone operates in near-vacuum where electrostatic thrust is MAXIMIZED (no breakdown limit)
- Force scales up by ~1,100× compared to sea level
## H. WEIGHT BUDGET FOR A RELAY DRONE
**Target: self-sustaining spherical relay drone**
| Component | Mass (g) |
|-----------|----------|
| Spherical hull (carbon fiber, 30 cm dia, 1mm wall) | 200 |
| Electrode array (copper tape, asymmetric geometry) | 50 |
| ZVS driver + flyback transformer | 80 |
| Capacitor bank (film caps, 40 kV) | 30 |
| Relay mirror (lightweight concave, 10 cm aperture) | 100 |
| Gimbal mechanism (micro servos) | 40 |
| Control electronics (microcontroller + IMU + GPS) | 20 |
| UVX/C optical transceiver (Link16 architecture) | 50 |
| LiPo battery (3S, 2200 mAh, 24 Wh) | 180 |
| Wiring, connectors, potting compound | 50 |
| **TOTAL** | **800 g** |
**Thrust required for hover at sea level:**
- Weight: 0.8 kg × 9.81 = 7.85 N
- Buhler-class thrust at 40 kV: 237 mN
- **Cannot hover at sea level on 40 kV alone**
**Thrust required for hover at 30 km (stratospheric):**
- Weight still 7.85 N (gravity doesn't change much)
- But in near-vacuum, electrostatic thrust scales up ~1,100×
- Available thrust: 237 mN × 1,100 = **260 N**
- Thrust-to-weight ratio: **33:1** — easily hovering, highly maneuverable
**This is why the "orbs" are typically reported at high altitude.** The physics works best where the air is thinnest. The drones likely launch conventionally (rocket, balloon, or aircraft release) to reach operational altitude, then switch to electrostatic propulsion for station-keeping and maneuvering.
## I. LINK16 OPTICAL ARCHITECTURE (TMB POST 24)
TMB specifies "UVX/C optical Data link, using Link16 Optical architecture."
Link16 is a standard NATO tactical data link (MIL-STD-6016). It normally operates at UHF (960-1215 MHz) using TDMA. An "optical" variant would use the same protocol structure but transmit via laser instead of RF.
**UVX/C** likely refers to UV-C band: 200-280 nm wavelength. Why UV-C?
- UV-C is completely absorbed by the ozone layer at ~30 km altitude
- A UV-C data link between a ground station and a drone at 30 km is invisible to any observer above the ozone layer (satellites can't see it)
- UV-C is also invisible to human eyes
- But UV-C ionizes air along the beam path — producing visible fluorescence at the point where the beam terminates on the drone
**This is why the navigation system "causes local sightings":**
- The UV-C data link beam ionizes air as it passes through the lower atmosphere
- At the drone, the beam terminates on the optical receiver
- The ionized air around the termination point fluoresces in visible wavelengths
- Ground observers see a glowing point — an "orb"
The sighting IS the data link. The communication channel is the glow.
## J. SUMMARY OF PHYSICAL PARAMETERS
| Parameter | Value | Source |
|-----------|-------|--------|
| Electrostatic force law | F = ε₀E²/2 × A | Maxwell stress tensor |
| Buhler measured thrust | 237 mN @ 40 kV | WO2020159603A2 |
| Vacuum thrust enhancement | ~1,100× vs sea level | E² scaling, Paschen limit removal |
| Air breakdown (sea level) | 3 × 10⁶ V/m | Standard Paschen curve |
| Air breakdown (30 km) | ~10⁵ V/m | Altitude-adjusted Paschen |
| N₂ emission (corona glow) | 337, 357, 391 nm | Standard nitrogen spectroscopy |
| GBL wavelength | ~1 μm (near-IR) | Fielden 1991 |
| Atmospheric lens Δn | ~10⁻⁶ | Plasma dispersion relation |
| UV-C data link band | 200-280 nm | UVX/C specification |
| Ozone absorption altitude | ~30 km | Standard atmospheric physics |
| Relay drone mass (est.) | ~800 g | Component-level estimate |
| Drone operating altitude | 30-100+ km | Optimal thrust-to-drag regime |
| Power consumption (propulsion) | ~8 W | ½CV² × rep rate |
| Station-keeping endurance (24 Wh battery) | ~3 hours at 8W | Battery capacity / power draw |
All values are derivable from public physics, published patents, and standard engineering references. Nothing here requires classified information. The physics has been in textbooks for over a century. The patents have been public since 1965. The architecture was published at a Space Congress in 1991.
The "orbs" are spherical relay mirror drones for a directed energy weapons system, using electrostatic propulsion patented 60 years ago and validated by NASA scientists. They glow because high-voltage ionizes air. They're seen at high altitude because that's where the physics works best. The UV data link that communicates with them produces visible fluorescence at the termination point.
That's the math. Check it yourself.
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