Products / EVA-X MINI
Modular VTOL platform
One airframe. Three energy architectures.
EVA-X MINI shares one airframe, one payload bay, and one flight-control system across three powertrains — diesel-hybrid, compressed-hydrogen, and liquid-hydrogen — so the mission picks the energy source, not the other way around.
Platform architecture
A modular VTOL platform built around mission flexibility.
Common airframe and payload architecture; powertrain selected for the operating environment. Every variant shares the same wing, nacelles, landing gear, avionics, flight modes, and payload interfaces — only the energy module changes.
- Vertical takeoff and fixed-wing cruise in one compact platform
- Six-drone internal payload architecture
- Twin electric tiltrotors with common avionics and flight controls
- Diesel/heavy-fuel, compressed-H₂, or liquid-H₂ configurations
- No Chinese-manufactured flight-critical or propulsion components
The shared air vehicle
Same platform. Same numbers. Across every variant.
60 lb
Structural MTOW
72 in
Wingspan
34 in
Twin rotors
9.6 lb
Six-drone payload
70–80
Econ. cruise (mph)
24S
HV propulsion bus
EVA-X MINI shares one airframe, one payload bay, and one flight-control system across three powertrains — diesel-hybrid, compressed-hydrogen, and liquid-hydrogen — so the mission picks the energy source, not the other way around.
Three energy architectures
Match the powertrain to the mission.
Each configuration carries the same airframe and six-drone payload bay. What changes is endurance, signature, and logistics — pick the trade that fits the operating environment.
EVA-X MINI D
Diesel / heavy-fuel hybrid-electric
The baseline long-endurance configuration — liquid-fuel logistics, rapid field refueling, and the most mature build path.
Run time
5+ hr
Range
250+ mi
Fuel storage
1.2 gal diesel / JP-8 / Jet-A
Power unit
Generator, 3–4 kW continuous
Battery
400–600 Wh
Cruise speed
75–85 mph
- Liquid-fuel logistics and rapid field refueling
- Highest energy density of the three variants for long-duration missions
- Battery-buffered electric VTOL keeps the rotor architecture common across variants
Performance objectives remain subject to final engine/generator selection, BSFC, drag, and flight-test validation — Rev D engineering baseline, not certified performance.
EVA-X MINI H2-C
Compressed-hydrogen fuel cell hybrid
Lower vibration and zero combustion exhaust — a development configuration trading endurance for simpler hydrogen handling.
Run time
~2–3 hr (preliminary)
Range
~150–200 mi (preliminary)
Fuel storage
0.25–0.35 kg H₂, 350 bar Type IV
Power unit
Fuel cell, 3–4 kW class
Battery
600–1,000 Wh
Cruise speed
70–80 mph (economical)
- Fuel-cell electric cruise with battery-supported VTOL transients
- Reduced vibration and lower-temperature heat rejection
- Compressed-H₂ storage trades endurance for simpler handling than cryogenic LH₂
Development configuration; performance is not frozen until a compliant fuel-cell and tank system is selected.
EVA-X MINI H2-L
Liquid-hydrogen fuel cell hybrid
The advanced endurance development configuration — cryogenic storage aimed at diesel-class range with zero combustion exhaust.
Run time
5+ hr (development)
Range
250+ mi (development)
Fuel storage
Liquid H₂, ~1.0–1.5 kg, 12 L class
Fuel cell target
Fuel cell, 3–4 kW class, custom
Battery
600–1,000 Wh
Cruise speed
70–80 mph (economical)
- Higher hydrogen volumetric density than compressed gas
- Potential path to long-endurance hydrogen operation
- Common electric propulsion and payload architecture with H2-C
Advanced development configuration; tank mass, usable LH₂, boil-off, ground handling, and performance require supplier validation.
Side by side
Choose the energy architecture for the mission.
Most mature baseline
D
Diesel / heavy-fuel hybrid
5+ hr
Run time
250+ mi
Range
Liquid diesel
Fuel type — fast field refueling
Preliminary class
H2-C
Compressed hydrogen
~2–3 hr
Run time
~150–200 mi
Range
Compressed H₂
Fuel type — no combustion exhaust, lower vibration
Advanced development
H2-L
Cryogenic hydrogen
5+ hr
Run time
250+ mi
Range
Cryogenic H₂
Fuel type — no combustion exhaust, advanced endurance path
Payload architecture
A six-drone payload architecture multiplies mission reach.
Six internal payload drones at 1.6 lb each, released from a quick-release internal rack with common mission interfaces. The carrier aircraft handles VTOL launch, efficient transit, and deployment — the payload set can be tailored to the approved mission.
6
Payload drones
9.6 lb
Total payload
1.6 lb
Per drone
Drone wingspan
26.0 in / 66 cm
Drone length
16.5 in / 42 cm
Drone height
3.1 in / 8 cm
Drone weight
1.6 lb / 0.73 kg each
Drone battery
LiPo 6S 6000 mAh
Launch method
Internal bay / air drop
Supply chain policy
Designed around a U.S. / allied supply chain.
Country of manufacture and critical-component provenance are controlled procurement requirements — not a marketing claim. A common-platform bill of materials enables supplier qualification across all three variants, and prototype supplier selections remain subject to written provenance and qualification.
No China
No Chinese-manufactured flight-critical or propulsion components
Common BOM
Maximize cross-variant parts to preserve manufacturing leverage
Traceable
Country-of-origin documentation for every flight-critical subsystem
Production economics
Unit cost is designed to improve rapidly with scale.
Current planning estimates for the base aircraft, excluding mission payload sensors, NRE/tooling, ground station, and certification.
$53.2K
10-unit recurring estimate
$31.0K
100-unit recurring estimate
$18.9K
1,000-unit recurring estimate
- Largest cost-reduction opportunities: engine/generator, electric propulsion electronics, and composite airframe.
- A common airframe across D / H2-C / H2-L is intended to preserve manufacturing leverage.
- Hydrogen-variant production cost remains supplier-dependent and is not yet frozen.
Development path
From frozen suppliers to production release.
01
Freeze suppliers
Motor/prop, engine-generator, fuel cell, tanks, avionics.
02
Detailed CAD
Structures, tilt mechanism, energy bay, thermal system.
03
Ground validation
Powertrain, thermal, structural, and systems integration.
04
Flight envelope
VTOL, transition, cruise, endurance, and payload deployment.
05
Production release
Qualified BOM, tooling, QC, and acceptance test.