FW108 Foldable Wing Unmanned Aerial Vehicle System

Introduction

The loitering munition UAV system adopts an integrated design for storage, transportation, and launch. The UAV platform can be folded into the launch tube and is deployed using a tube-based ejection method. It is equipped with a dual-optical payload (visible light/infrared) and functional payloads such as spectrum suppression, anti-radiation, or warheads. It is designed to strike enemy medium and large tanks, armored vehicles, or fortifications and can be used for vehicle-mounted cluster launches to conduct saturation attacks on enemy areas.

 

Architecture of UAV

· Functions

This product is a reconnaissance-type folding-wing UAV equipped with a dual-optical payload consisting of visible light and infrared sensors. It is designed for reconnaissance missions in target areas. The UAV is launched using a tube-based air ejection system. The operational workflow is shown in the following diagram:

 

 

Figure 1: Workflow Diagram

 

· Composition

The PB180 foldable wing UAV consists of the aircraft platform subsystem, control subsystem, and launch subsystem. The equipment block diagram is shown in Figure 2. The components of each subsystem are shown in Figures 3, 4, and 5, respectively. The equipment layout is shown in Figure 6.

 

 

Figure 2: System Composition Block Diagram

 

FFigure 3: Aircraft Platform Subsystem Composition Block Diagram

 

 

Figure 4: Control Subsystem Composition Block Diagram

 

 

Figure 5: Launch Subsystem Composition Block Diagram

 

 

 

· Specifications

 

Table 1: Overall System Specifications

Takeoff weight	≤30kg	Tube exit velocity	≥30m/s
Fuselage Length	＜1.9m	Folded diameter	＜0.18m
Visible light resolution	2560×1440	Visible light FOV (field of view)	51°×30°
Infrared resolution	640×512	Infrared FOV	24°×18°
Wingspan	＜2.5m	Cruisie speed	108~144km/h
Warhead weight	≤7kg	Maximum Flight Speed	144km/h
Operational Altitude	80m-500m	Control Radius	10km/30km/50km
Endurance	≥120min	Launch Method	gas ejection/propellant
Service Ceiling	4000m（altitude）	Wind Resistance	Level 4
Operating temperature	-40℃~50℃	Storage temperature	-55℃~65℃

 

Composition of UAV Equipment

· Control Subsystem

The control subsystem of the foldable wing UAV system features a portable design, available in two forms: a handheld control terminal and a dual-screen workstation. It integrates remote control, data transmission, image transmission, and ground station functions. The system is compact and easy to operate. The joysticks, switches, and buttons on the control terminal or workstation are mapped to the operational commands of the UAV. The operation logic of the foldable wing UAV is simple yet powerful. Its built-in link operates in the 1.4GHz frequency band and provides stable data transmission within a 10-kilometer range. Additionally, links with 30-kilometer or 50-kilometer ranges can be configured according to requirements.

 

 

Figure 6: Physical Image of Handheld Control Terminal

 

 

Figure 7: Physical Image of Dual-Screen Workstation

 

 

Figure 8: Radio Communication

 

 

· Launch Subsystem

The launch subsystem uses nitrogen as the power source, releasing nitrogen instantaneously to launch the folding-wing UAV. The launch subsystem is designed as an integrated system with the following features: easy operation, no infrared signature, low noise, no risk of explosion caused by a gunpowder launch chamber, and the ability to withstand low temperatures and adapt to high-altitude environments.

 

 

 

Figure 9: Physical Image of Single-Tube/Cluster Launcher

 

 

Figure 10: One-Station Six-UAV Mission Flight Diagram

 

 

Operational Process of Loitering Munitions

1）Retract the Vertical Stabilizer
Simultaneously rotate the left and right vertical tail fins 90 degrees forward, fold them towards the sides of the fuselage, and then secure them in place.
2）Fold the Forward Wings
Fold the left forward wing 90 degrees towards the tail until the wing edge is parallel to the fuselage axis. Fold the right forward wing 90 degrees towards the tail until the wing edge is parallel to the fuselage axis. At the same time, keep the forward wings and vertical tail fins in the folded position.
3）Fold the Rear Wings
Fold the left rear wing 90 degrees towards the nose until the wing edge is parallel to the fuselage axis. Fold the right rear wing 90 degrees towards the nose until the wing edge is parallel to the fuselage axis, then keep them stationary.
4）Retract the Propulsion Propeller
Rotate the propeller hub horizontally, and fold the left and right propellers towards the aircraft's nose until the propellers are close to the vertical tail.
5）Place the aircraft into the launch tube
Keep the aircraft horizontal, rotate the hub to make it as horizontal as possible. Install the booster block at the rear of the aircraft (Note: the hub must be embedded in the matching slot of the booster block!).
Keep the launch tube in a horizontal position. Align the tail of the aircraft with the opening of the launch tube. With the front wings facing upwards and the rear wings facing downwards, slowly push the aircraft into the launch tube.
6）Check the alignment and positioning of the aircraft inside the launch tube
After the aircraft is loaded into the launch tube, if the front end of the seeker aligns with the pre-marked position inside the tube, it indicates that the aircraft is properly installed, and the process of folding the aircraft into the tube is complete. If the alignment is not correct, it means the aircraft is not properly installed and needs to be removed and reloaded into the tube.

 

 

Equipment Images