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Attachment 1 – Technical Specifications Compliance Matrix Company Name:
Submission Date:
INSTRUCTIONS
1. Attachment must be submitted in Word format.
2. Responses that do not meet requested specifications must be included in red font and underlined.
3. Responses that exceed requested specifications must be included in blue font and underlined.
4. Do not use terms such as “meets” or “compliant” in the technical comparison matrix. The matrix must be completed with actual specifications of the proposed boats. For example only:
| Item |
| Minimum Specification |
| Proposed (Incorrect) |
| Proposed (Correct) |
| Production Year |
| Recent model year, not older than 2025 |
| Not older than 2025 |
| 2026 |
| Seating Capacity |
| 5 |
| Compliant |
| 5 |
| Speed |
| Minimum speed requirement: 40 to 45 knots |
| Meets |
| 35-40 knots |
CLIN 001: Mid-range, backpack-portable, electric vertical take-off and landing (eVTOL) fixed-wing Unmanned Aircraft Systems (UAS) Quantity: 2 EA
GENERAL INFORMATION
Manufacturer
Year
Model
PICTURE(S)
Insert pictures prior to proposal submission and delete note.
A. Minimum Specifications
| Item |
| Minimum Requirements |
| Proposed |
| Configuration |
| Fixed-wing eVTOL (electric vertical take-off and landing) |
| Maximum Take-Off Weight |
| ≤ 19 lbs / 8.6 kg |
| Portability |
| Backpack/rucksack portable; all components transportable by a single operator |
| Deployment Time |
| Operational within 3 minutes from unpacking |
| Launch / Recovery |
| Fully autonomous vertical take-off and landing in confined spaces; no additional tools, launch equipment, or recovery nets required |
| Weather Protection |
| IP54 rating or better |
| Modularity |
| Rapid field reconfiguration between fixed-wing and multicopter configurations using the same core fuselage, ground controller, data link, sensors, and AI processing unit |
Flight Performance Specs:
| Maximum Endurance |
| ≥ 180 minutes (3 hours) under standard conditions |
| Cruise Speed Range |
| 29–39 knots (33–45 mph) |
| Wind Tolerance (Ground Operations) |
| ≥ 19 knots (22 mph) |
| Wind Tolerance (In-Flight) |
| ≥ 23 knots (26 mph) |
| Take-Off Altitude (MSL) |
| ≥ 3,000 m / 9,843 ft |
| Operating Altitude (MSL) |
| ≥ 4,500 m / 14,764 ft |
| Operating Temperature Range |
| -20°C to +45°C (-4°F to +113°F) |
Command Control & Communications:
| Operational Range (C2 & Video) |
| ≥ 40 km with standard antenna configuration |
| Encryption Standard |
| AES-256 or equivalent |
| Data Link |
| Encrypted IP Mesh network |
| Frequency Band |
| 2.2–2.5 GHz encrypted; dual-band options preferred |
| Extended Range Option |
| System shall support optional or included antenna upgrade to achieve ≥ 80 km range |
ELECTRO-OPTICAL / INFRARED (EO/IR) PAYLOAD:
The system shall be equipped with a stabilized, gyro-stabilized EO/IR gimbal payload meeting all minimum specs.
AI AND MISSION PROCESSING:
| Onboard AI Processor |
| High-performance embedded AI processor (minimum 16 GB equivalent) capable of real-time onboard processing |
| GNSS-Denied Navigation |
| System shall support autonomous navigation in GNSS-denied environments |
| Object Detection & Classification |
| AI-enabled onboard object detection, classification, and tracking |
| System Architecture |
| Open systems architecture to allow future capability expansion and software updates |
DUAL-CONFIGURATION CAPABILITY:
| The system shall support rapid field reconfiguration between: |
| • | Configuration A – Fixed-Wing eVTOL: For extended-endurance, long-range ISR missions |
| • | Configuration B – Multicopter: For confined-space, hover-capable operations |
Reconfiguration shall be achievable in the field without specialized tools. The core fuselage, ground control station, data link, sensors, and AI processing unit shall remain common across both configurations. Only the wing and/or boom assemblies shall require exchange.
CONSTRUCTION AND MATERIALS:
| • | Airframe: Lightweight, durable construction suitable for sustained operations in challenging maritime and coastal environments, including high humidity, salt air, and variable temperatures |
| • | Weather Resistance: All components shall be rated for operation in maritime environments | |
| • | Structural Integrity: System construction shall meet or exceed applicable international standards for professional UAS operations | |
UAS SYSTEMS:
| Each complete system shall include, at minimum: |
| 1. | UAS Airframe – Fixed-wing eVTOL platform |
| 2. | Multicopter Conversion Kit – Boom and rotor assembly enabling dual-configuration capability |
| 3. | Ground Control Station (GCS) – Ruggedized, field-operable controller (tablet or laptop-based) with all required hardware and software pre-installed |
| 4. | Mission Control Software – Tactical mission planning and flight control software, including all applicable licenses |
| 5. | Antenna System (Standard) – Providing ≥ 40 km C2 and video range |
| 6. | Antenna System (Extended Range) – Providing ≥ 80 km range |
| 7. | EO/IR Payload Sensor – Stabilized gimbal meeting all specifications in Section 3.5 |
| 8. | Flight Batteries and Charging Equipment – Sufficient quantity for sustained field operations |
| 9. | Transport / Carry Cases – Ruggedized, backpack-portable cases for all system components |
| 10. | Accessories – All cables, mounts, adapters, and ancillary equipment required for full system operation |
SPARE PARTS:
| The Contractor shall provide an initial spare parts package for each system, including: |
| • | Propulsion and motor spare parts kit (as applicable) |
| • | Electrical spare parts (fuses, connectors, switches) |
| • | Flight battery spares (minimum one additional flight battery per system) |
| • | Airframe consumables and structural repair materials |
| • | EO/IR payload consumables and protective components |
| • | Other consumable items as recommended by the manufacturer |
TOOLS AND EQUIPMENT:
The Contractor shall provide a complete tool kit for each system, including all tools necessary for routine field maintenance and minor repairs as specified in the maintenance manual.
