| AIRFRAME |
| AF-001 | Nose cone / fwd fuselage | CFRP monocoque | 1 | Sensor bay ONLY — no engine obstruction |
| AF-002 | Centre fuselage | CFRP / Al 7075 hybrid | 1 | Main fuel, wing attach, main gear bay |
| AF-003 | Aft fuselage / engine bay | CFRP reinforced | 1 | Rear bulkhead engine mount, prop clearance |
| AF-004 | Main wing spar | CFRP unidirectional 16–20 m | 1 | Wet fuel wing, high-aspect-ratio |
| AF-005 | Wing skin panels | CFRP / Nomex honeycomb | 4 | Upper + lower, port + stbd, with fuel sealing |
| AF-006 | Inverted-V fin (port) | CFRP, ~45° cant angle | 1 | Combined ruddevator (rudder + elevator) |
| AF-007 | Inverted-V fin (stbd) | CFRP, ~45° cant angle | 1 | Combined ruddevator — NO separate H-stab |
| AF-008 | Engine cowling (rear) | Fiberglass / CFRP | 1 | Pusher prop cutout, exhaust exit aft |
| PROPULSION (PUSHER) |
| PR-001 | Engine — primary option | Rotax 915 iS, 141 hp / 105 kW | 1 | Rear centreline mount, AvGas / Mogas |
| PR-001B | Engine — alt option | PBS TE400 turboprop, ~160 hp | 1 | Higher altitude performance option |
| PR-002 | Pusher propeller | 3-blade constant-speed composite, 1.8–2.2 m | 1 | Rear-facing pusher orientation |
| PR-003 | Prop governor | MT-Propeller or Hartzell class | 1 | Automatic pitch control |
| PR-004 | FADEC / EFI | Dual-channel electronic fuel injection | 1 | Rotax iS native FADEC |
| PR-005 | Fuel system | Wet wing + centre fuselage tank, ~700 L | 1 set | Cross-feed valve, vent, fuel cap×4 |
| PR-006 | Fuel pump | Engine-driven + electric boost | 2 | Redundant pair |
| PR-007 | Oil cooler | Air-cooled side cowl exchanger | 1 | Rear cowl mount |
| PR-008 | Exhaust system | Stainless steel, rear exit | 1 | Optional IR suppressor baffles |
| PR-009 | Fire suppression | Halon-replacement, thermal detection loop | 1 | Engine bay auto/manual |
| PR-010 | Prop spinner | Composite + machined Al backing plate | 1 | Aerodynamic hub fairing |
| AVIONICS & FLIGHT CONTROL |
| AV-001 | Flight Control Computer | Dual-channel FCC, MIL-STD-1553B | 1 | Autopilot + guidance |
| AV-002 | INS / IMU | MEMS INS or ring-laser gyro | 1 | Dead-reckoning |
| AV-003 | GPS / GNSS Receiver | GPS + GLONASS multi-constellation | 1 | Primary position |
| AV-004 | Air Data Computer | Pitot-static + dual ADC | 2 | Airspeed, altitude, AoA |
| AV-005 | Radar Altimeter | Low-altitude terrain sensing | 1 | Terrain following / landing |
| AV-006 | TCAS / ADS-B | TCAS II + ADS-B In/Out | 1 | ICAO compliance |
| AV-007 | Ruddevator servo | High-torque digital servo | 2 | One per inverted-V fin — pitch+yaw combined |
| AV-008 | Aileron servo | High-torque digital servo | 2 | Port + stbd roll control |
| AV-009 | Flap servo | Medium-torque digital servo | 2 | Port + stbd, inboard wing |
| AV-010 | Flight Data Recorder | Crash-protected solid-state | 1 | HUMS + mission data |
| COMMUNICATIONS |
| CM-001 | SATCOM antenna | Ku-band conformal patch array | 1 | Dorsal fuselage mount |
| CM-002 | LOS datalink terminal | UHF/L-band directional | 1 | ~250–300 km range |
| CM-003 | VHF/UHF ATC radio | ICAO AM/FM transponder | 1 | ATC integration |
| CM-004 | HF backup radio | HF modem 2–30 MHz | 1 | C2 fallback |
| CM-005 | COMSEC / encryption | AES-256 all-links | 1 set | Mandatory for all datalinks |
| PAYLOAD |
| PL-001 | EO/IR gimbal turret | 3-axis, HD EO + MWIR, ±90°/±120° | 1 | Belly-nose mount — zero prop FOV obstruction |
| PL-002 | Laser rangefinder | Class 3B/4, co-bore-sighted EO/IR | 1 | Target geo-location |
| PL-003 | SAR radar (optional) | X-band SAR, STRIPMAP/SPOT | 1 | Wing or belly conformal pod |
| PL-004 | SIGINT antenna (optional) | Broadband passive RF, DF capability | 1 | Wingtip or fuselage sides |
| PL-005 | Payload computer | GPU-accelerated SBC | 1 | H.264/H.265 real-time, AI detection opt. |
| POWER & ELECTRICAL |
| PW-001 | Main alternator | Engine-driven AC, 2–4 kVA | 1 | Rotax native alternator |
| PW-002 | 28 VDC bus + PDU | Solid-state power controller | 1 | Fault isolation, load shedding |
| PW-003 | Emergency Li-ion battery | 28V, ≥30 min flight-critical loads | 1 | Engine-out continuity |
| PW-004 | BMS | Battery management, cell monitoring | 1 | Charge + health monitoring |
| PW-005 | Wiring harness | Shielded aviation-grade wire | 1 set | EMP / lightning TVS on all buses |
| LANDING GEAR |
| LG-001 | Nose gear strut | Oleo-pneumatic, steerable | 1 | Retractable |
| LG-002 | Main gear struts | Oleo-pneumatic, retractable | 2 | Port + stbd |
| LG-003 | Wheel brakes + ABS | Carbon disc + anti-skid controller | 2 | Main gear only |
| LG-004 | Emergency ballistic chute | MTOW-class, popgun deploy | 1 | Optional recovery system |
