Product overview
The Lyncon Technology GHQ-400 is a powered fixed-wing UAV platform with a conventional aerodynamic arrangement, a high-aspect-ratio mid-mounted wing and a V-tail. A two-cylinder, two-stroke piston engine drives its rear pusher propeller. Tricycle wheeled landing gear supports rolling departures and recoveries from simple airfields. Its mission roles include weather modification, logistics support and transport delivery, while its payload integration capability extends to reconnaissance equipment and precision-guided weapons. The aircraft is designed for recovery and reuse.
Integration provisions include at least 60 kg of mission payload capacity and 1.3 kW of electrical power for mission equipment. Compatible payload categories identified for the aircraft include electro-optical pods and SAR radar; listed payload configurations also include an airborne communications base station. An electro-optical pod supports search, surveillance, tracking and target aiming. Dedicated flight-control and navigation systems provide one-button takeoff and landing and autonomous flight. Standard air-to-ground communications cover 80 km under line-of-sight conditions, with upgrades offered as required.
Cruise speed is 130–180 km/h, with a maximum of 200 km/h. The 15-hour endurance figure requires 150 kg of fuel, flight at 2000 m and at least 150 km/h, and 5% fuel remaining at landing. The takeoff and landing ground run is no more than 600 m at 1100 m altitude on a hard, flat surface with a slope no greater than 3%. Four people can assemble or disassemble one aircraft within 30 minutes, supporting deployment and transport.
Specifications
| Specification | Value & conditions |
|---|---|
| Airframe architecture | Conventional aerodynamic layout with a high-aspect-ratio mid-mounted wing and V-tail. |
| Propulsion | Two-cylinder, two-stroke piston engine driving a pusher propeller. |
| Landing gear and recovery | Tricycle wheeled landing gear for rolling takeoff and landing. |
| Payload integration | Can accommodate electro-optical pods, SAR radar and other reconnaissance payloads, as well as precision-guided weapons. |
| Flight control and navigation | Integrated dedicated flight-control and navigation systems, one-button takeoff and landing, and fully autonomous flight. |
| Operator training | Operators can execute flight plans after basic training. |
| Multi-aircraft control | Supports multiple aircraft from one station, with provision to expand into coordinated multi-aircraft missions. |
| Service ceiling | Greater than 5000 mAltitude above sea level. |
| Flight altitude | 500–3000 mAltitude above sea level. |
| Cruising speed | 130–180 km/h |
| Maximum flight speed | 200 km/h |
| Endurance | 15 h150 kg of fuel; 2000 m altitude; speed ≥150 km/h; 5% fuel remaining at landing. |
| Takeoff and landing ground run | ≤600 m1100 m altitude; hard, flat surface with slope ≤3%. |
| Crosswind capability | Can take off and land in direct crosswinds ≥7 m/s.During takeoff and landing. |
| Airborne wind resistance | Can withstand continuous winds ≥15 m/s.During flight; continuous wind. |
| Electrical power capacity | 1.3 kWFor mission equipment. |
| Communication range | 80 kmAir-to-ground line of sight; standard configuration, upgradeable as required. |
| Horizontal and elevation positioning accuracy | Both better than 10 m.RMS accuracy. |
| Mission payload capacity | ≥60 kg |
| Flight service life | ≥500 flight hours |
| Takeoff and landing cycles | ≥100 cycles |
| Assembly or disassembly time | ≤30 minFour people working on one aircraft. |
| Listed payload configurations | Airborne communications base station and electro-optical pod. |
| Electro-optical mission functions | Search, reconnaissance, surveillance, tracking and target aiming.With an electro-optical pod integrated. |
| Application areas | Weather modification, logistics transport support and transport delivery. |
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