Hang-flight test
The payload flight‑test service provides comprehensive support for unmanned aerial vehicles equipped with specific payloads—such as radar, sensors, or weapons—by conducting flight tests, collecting data, and performing validation.
The objective is to validate equipment performance, system compatibility, and flight safety. Services encompass test design and preparation, flight testing and data acquisition, as well as data analysis and verification. Customized testing services can be tailored to meet diverse user requirements by selecting appropriate UAV types.
Hanging aircraft type
AIRCRAFT TYPE
Performance Parameters
PERFORMANCE PARAMETERS
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Performance Parameters
Wingspan: 12.54 m
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Payload capacity
Nose Payload Bay: With a capacity of 60 liters, it can accommodate and mount various mission payloads. The nose bay is detachable and can be adaptively redesigned and replaced to suit the size and configuration of the mission payload.
Airframe Payload Bay: Capacity 78 L; dimensions: 620 mm (L) × 400 mm (W) × 360 mm (H); equipped with a mounting plate on the bottom for installing various payload devices. Maximum internal payload capacity ≥ 80 kg.
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Performance Parameters
Wingspan: 6.27 m
Cockpit length: 3.27 m
Wing area: 3 m²
Maximum rate of climb: 5 m/s
Cruise altitude: 2000 m
Cruise speed: 120–150 km/h
Usable fuel: ≥48 L
Takeoff and landing method: Vertical takeoff and landing
Power supply capability: 28 V / 700 W -
Onboard payload space
Front equipment bay: 29 L in capacity, with dimensions of 33 × 33 × 26 cm. It can accommodate and mount various mission payloads. Rear equipment bay: 16.6 L in capacity, measuring 26 × 25 × 25 cm, with an installation plate on the bottom for mounting different payload devices. Note: The combined maximum weight of internal and external mounts is 40 kg.
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External mounting capability
Nose-mounted hardpoint: One nose-mounted hardpoint with a 1 kg weight limit, capable of carrying electro-optical pods, cameras, thermal imaging sensors, and other payloads.
Under-fuselage hardpoints: One under-fuselage hardpoint, located directly beneath the fuselage, with a maximum payload of 40 kg and maximum dimensions of 1200 mm × 265 mm × 300 mm.
Wing hardpoints: There are four wing hardpoints in total, two on each side. Each hardpoint can carry 20 kg, and loads must be symmetrically distributed.
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Performance Parameters
Power type: Electric
Wheelbase: 2.6 m
Unfolded dimensions: 2.2 × 1.9 × 0.72 m (excluding propeller deployment)
Folded dimensions: 1.3 × 0.9 × 0.72 m
Standard load: 50 kg
Maximum load: 70 kg
Hovering endurance: ≥50 min
Standard payload endurance: ≥35 min
Maximum level-flight speed: ≥18 m/s
Maximum ascent rate: ≥5 m/s
Maximum takeoff weight: ≥160 kg
Flight altitude: ≥500 m (relative height) -
Payload space
Lower mounting bay: The maximum dimensions of the payload that can be mounted are 90 cm in length, 40 cm in width, and 30 cm in height, with length and height adjustable as needed. It can accommodate either fixed payloads or jettisonable payloads.
Side-mounted loading areas: Each side has dimensions of 76 cm long, 25 cm wide, and 30 cm high; the length can be adjusted as needed, but only for fixed loads.
Note: The maximum load capacity is 70 kg. When loading on both sides, the weight must be evenly distributed.
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Performance Parameters
Power type: Electric
Wheelbase: 2.8 m
Unfolded dimensions: 3.1 × 3.1 × 1.1 m (excluding propeller deployment)
Folded dimensions: 1.9 × 1.2 × 1.1 m
Standard load: 100 kg
Maximum load: 120 kg
Hovering endurance: ≥50 min
Standard payload endurance: ≥35 min
Maximum level-flight speed: ≥18 m/s
Maximum climb rate: ≥5 m/s
Maximum takeoff weight: ≥220 kg
Flight altitude: ≥500 m (relative height) -
Payload space
Lower mounting bay: The maximum payload dimensions are 130 cm in length, 60 cm in width, and 50 cm in height; the length and height can be adjusted to accommodate different payloads. This bay can carry either fixed payloads or jettisonable payloads.
Side-mounted load zones: Each side has dimensions of 130 cm in length, 20 cm in width, and 50 cm in height; the length is adjustable to accommodate the payload, and only fixed loads are permitted.
Note: The maximum load capacity is 120 kg; when loading on both sides, the weight must be evenly distributed.
Overall Layout
OVERALL LAYOUT
Platform Structural Design
The GHQ-600 unmanned aerial vehicle platform features a conventional twin-tailboom configuration with a high-mounted horizontal stabilizer and a rear‑pusher engine layout, along with a high‑aspect‑ratio midwing. Its near‑rectangular fuselage cross‑section provides excellent payload‑carrying efficiency.
Takeoff and Landing and Maneuvering Characteristics
The UAV is equipped with a retractable tricycle landing gear and takes off and lands on a runway, demonstrating excellent ground‑based target‑recognition capabilities and adaptability to takeoff and landing operations.
Mission payload capacity
The platform boasts robust payload‑carrying capabilities, enabling it to simultaneously host reconnaissance payloads such as electro‑optical pods and SAR radars, while also accommodating weapon‑carrying payloads and mission‑specific payloads configured for human‑targeting missions.
Task adaptability
This unmanned aerial vehicle exhibits strong adaptability across a variety of mission scenarios and can be widely employed to meet diverse operational requirements, including reconnaissance, strike, and personnel‑tracking missions.
Fixed-wing section
It employs a conventional twin-tailboom, high‑mounted horizontal tail, and rear‑pusher engine configuration, with a cantilevered high‑wing of rectangular planform. Meanwhile, the twin tailbooms extend forward to form the mounting structure for the rotor‑drive system, further reducing structural weight.
Engine
It is installed behind the fuselage’s aft fire‑proof panel. It employs a sliding‑type landing gear, which features a simple structure and light weight.
Rotor section
It employs a quadrotor configuration with an H‑type layout and a four‑axis, eight‑propeller arrangement, offering high power redundancy.
Whole machine
It is manufactured using carbon-fiber composite materials through a vacuum-assisted, heated and pressurized molding process, resulting in a lightweight yet high-strength structure.
XCD-160 Quadrotor Drone
The frame features a minimalist design, constructed from high-strength aluminum alloy tubing and manufactured through CNC machining, fixture‑based positioning, and low‑temperature welding.
The entire machine adopts an X‑type layout.
Foldable design reduces transport volume. The arms are made of carbon fiber to minimize weight. The landing gear is formed by bending high‑strength aluminum alloy tubes, offering lightweight construction and high strength.
Payload hang‑flight operations
This aircraft can be used for short-range, heavy‑payload logistics delivery missions as well as a variety of payload‑carrying flight operations.
Rack Design and Materials
The frame features a minimalist design, constructed from high-strength aluminum alloy tubing and manufactured through CNC machining, tool‑assisted positioning, and low‑temperature welding. The entire unit adopts an X‑shaped configuration and incorporates a foldable design to minimize transport volume.
Arm and Landing Gear Structure
The robotic arm is made of carbon fiber to reduce weight. The landing gear is fabricated by bending high-strength aluminum alloy tubes, offering both lightweight construction and high strength.
Application scenarios
This aircraft can be used for short-range, heavy‑payload logistics delivery missions as well as a variety of payload‑carrying flight operations.
