Engineering Deep Dive

Platform
Technology

Persistent Core architecture, QRAM rapid-swap interface, variable-geometry propulsion, and solar-structural energy systems — engineered for 10-year service life in extreme environments.

Ch 8.1

Persistent Core

The Core contains everything that does not change: flight control, power management, computing, thermal regulation, communication. Standardized, hardened, mass-producible.

STRUCTURE

Load-Bearing Carbon Fiber

Not a container — a structural member. Carbon fiber shear webs carry wing bending moments through the Core. FEA-validated to 6g ultimate load factor with 3g operational limit.

6gUltimate Load

3gOperational

15%Safety Margin

COMPUTING

Integrated Intelligence

Flight controller, MERCURY AI processor, power management unit, thermal regulation, and mesh communication — all housed in the standardized Core chassis. Mission modules connect; intelligence stays resident.

PRODUCTION

Mass Production Ready

Identical Core across all units. Standardized SKU wings. Modular payload accessories. Production sequence from raw prepreg to flight-ready in defined assembly stages with repeatability targets.

REPAIR

Field Maintainable

10+ year service life with field repair capability. Individual component replacement without depot-level maintenance. Single-technician configuration swap in under three minutes.

10yrService Life

1Technician

Ch 8.1 cont.

QRAM System

Quick-Release Aerodynamic Mount: the mechanical, electrical, and data interface between Persistent Core and mission modules. Field reconfiguration without tools, without calibration, without ground support equipment.

MECHANICAL

Tool-Free Interface

Precision-machined aluminum alloy alignment pins with spring-loaded retention. Structural load transfer via shear lug interface. 500N·m torque capacity. Self-aligning within 0.1mm positional tolerance.

ELECTRICAL

48V Power Bus

48V/30A primary power, 5V/3A auxiliary logic. Automatic polarity protection. Hot-swap capable with <100ms reconnection. Laser-welded connector-less cell strings for solar integration.

DATA

Gigabit + CAN Bus

Gigabit Ethernet for MERCURY sensor data. CAN bus for control surface actuation. USB 3.0 for high-bandwidth payload. Automatic parameter adaptation on wing recognition — no manual calibration.

PNEUMATIC

VTOL-Ready Interface

Future VTOL tri-rotor module uses same QRAM interface with additional pneumatic channel. Standard wing for routine missions. VTOL wing for special operations. Three-minute swap, identical procedure.

<3minFull Swap

6Wing Configs

Validated Swap Timeline

Wing Release

0:15

Payload Swap

0:45

Wing Attach

0:30

System Check

0:30

Pre-Flight

0:40

TARGET: <3:00 TOTAL · SINGLE TECHNICIAN · NO TOOLS REQUIRED

Ch 8.2

Advanced Propulsion

One engine. One propeller. Two axes of motion. The propeller gimbals — 0–90° pitch for vertical-to-horizontal thrust transition, ±25° yaw for directional control in hover. No tilt mechanisms. No single-point failures.

01°

Thrust Vectoring Gimbal

Servo-driven gimbal with 0–90° pitch range and ±25° yaw authority. Carbon fiber gimbal frame, 2213 hollow shaft motor, 11×4.7" propeller (takeoff). Custom dynamic inversion mixer in INAV flight controller.

02⟳

Variable-Geometry Propeller

Morphing blade: span via Nitinol shape-memory alloy (0.3s), sweep via electric screwjack (0.5s), pitch continuously variable 15–45°. 25% hover efficiency gain, 15% cruise gain, 40% max speed improvement vs. fixed compromise.

03↑

Rocket-Style Vertical Launch

Automated launch sequence: spool to 100% thrust, gimbal to 90° (vertical), launch. Vertical ascent to transition altitude, gimbal sweeps 90°→0°, fixed-wing mode. 15–20% more energy than runway takeoff — acceptable for runway independence.

04↓

Starship-Style Landing

Unlike Starship's suicide burn, Phantom maintains hover capability throughout descent. Throttle margin preserved. Slope tolerance ±5°, roughness 50mm, substrate-independent. 15 km/h wind limit, 25 km/h gusts.

05△

VTOL Tri-Rotor Module

Optional QRAM attachment: 2× wing root motors (2212 900KV, 10" counter-rotating), 1× tail motor (tilts 0–90°). 120A peak hover, 40A cruise. +1.2kg, –25% endurance. Same QRAM interface, 3-minute swap.

06⚡

Transition Control

INAV with custom dynamic inversion mixer. Ailerons and V-tail active above 30% airspeed. Thrust vectoring primary below 30%. Gain-scheduled blended region during transition — seamless handover between flight modes.

Propulsion Specifications

Parameter	Takeoff / Hover	Cruise	Notes
Motor	2213 Hollow Shaft	Same	Single engine philosophy
Propeller (takeoff)	11×4.7"	—	Variable geometry
Propeller (cruise)	—	9×6"	Morphed for efficiency
Pitch range	15°	45°	Continuous, in-flight
Gimbal pitch	90° (vertical)	0° (horizontal)	0.3s transition
Gimbal yaw	±25°	0°	Hover directional control
Hover figure of merit	+25% vs fixed	—	Variable geometry benefit

Ch 8.3

Energy & Solar Systems

Solar-electric architecture with photovoltaic cells laminated directly into wing skin. Theoretically unlimited daylight endurance. Night operations bridged by 222Wh structural battery.

Desert Hawk Power Budget

Peak Solar Output 600W

Realistic Average (80%) 480W

Cruise Load 230W

Daylight Surplus +250W

Battery Capacity 222 Wh

Night Reserve 46 min

Daylight Endurance ∞

Battery Technology Roadmap

From Storage to Structure

2024

NMC 811 Lithium-Ion

Separate module, 2.1kg. Standard energy storage architecture.

222 Wh Capacity

2026

Solid-State Lithium

Higher energy density, improved thermal stability, QRAM-compatible module.

300 Wh Capacity

2028

Semi-Structural Battery

Battery integrated into non-load-bearing wing skin panels. Partial mass elimination.

350 Wh Effective Wh/kg

2030

Full Structural Battery Wing

Carbon fiber serves as electrode. Polymer matrix is electrolyte. The wing IS the battery. 90% structural performance of pure CFRP.

420 Wh Structural Wh

Structural Analysis

Load Paths
& Margins

QRAM-wing assembly validated for ultimate loads without permanent deformation, and operational loads without fatigue degradation over 1,000 flight hours. No flutter predicted below 1.5× dive speed.

Load Case	Limit Load	Ultimate Load (1.5×)	Status
2.5g level flight	Design cruise	3.75g	✓ PASS
3.0g pull-up maneuver	Operational limit	4.5g	✓ PASS
Vertical gust (15 m/s)	Structural limit	—	✓ PASS
Landing ground loads	2× landing weight	3×	✓ PASS
Torsional QRAM load	500 N·m	750 N·m	✓ PASS
Ultimate load factor	4g	6g	✓ PASS (+15% margin)

DEFLECTION

Wing Tip Limits

Maximum wingtip deflection under operational load within elastic limit. No plastic deformation at limit loads. Flutter speed exceeds 1.5× maximum dive speed. Divergence speed >2.0× Vne for all configurations.

MATERIALS

Material Allowables

Carbon fiber prepreg primary structure. Epoxy resin matrix with aerospace-grade void fraction <1%. Tensile allowable 800 MPa (structural battery wing: 1,200 MPa at 90% pure CFRP). All allowables include environmental degradation factors.