PB108 Foldable Wing Unmanned Aerial Vehicle System

Introduction

The PB108 foldable-wing unmanned aerial vehicle (UAV) can be folded into a launch tube for storage, transportation, and deployment, making it easy to carry and use. It is equipped with a visible and infrared dual payload for reconnaissance of target areas. The PB108 UAV system features a modular design, facilitating production and maintenance.

Architecture of UAV

· Functions

This product is a reconnaissance-type foldable-wing UAV equipped with a visible and infrared dual payload. It is used for reconnaissance of target areas. The product is launched using a tube-based air ejection method. The workflow is shown in the diagram below:

Figure 1: Workflow Diagram

· Composition

The PB108 foldable-wing UAV consists of the aircraft platform subsystem, control subsystem, and launch subsystem. The device block diagram is shown in Figure 2. The components of each subsystem are shown in Figures 3, 4, and 5. The equipment layout is shown in Figure 6.

Figure 2: System Composition Block Diagram

Figure 3: Flight Platform Subsystem Composition Block Diagram

Figure 4: Control Subsystem Composition Block Diagram

Figure 5: Launch Subsystem Composition Block Diagram

Figure 6: Onboard Equipment Installation Layout Diagram of the Aircraft Platform Subsystem

· Specifications

Table 1: Overall System Specifications

Composition of UAV Equipment

· Aircraft Platform Subsystem
The PB108 foldable wing UAV system is divided into three parts: the aircraft platform, the control subsystem, and the launch subsystem. The control subsystem consists of an independent handheld control terminal (Figures 8 and 9). The launch subsystem consists of a separate launch tube (Figure 10). Both are complete independent modules. The aircraft platform subsystem is mainly divided into nine modules: guidance head, fuselage, left forward wing, right forward wing, left rear wing, right rear wing, left V-shaped tail wing, right V-shaped tail wing, and propeller. The entire system is composed of 11 modules, as shown in the figure below:

Figure 7: Schematic Diagram of the Modular Structure Composition of the Aircraft Platform Subsystem

· Connection method:

①and④are connected by 4 M3 bolts.

②and③are connected by a torsion spring.

⑤and⑥are connected by a torsion spring.

④and⑦are connected by a torsion spring.

④and⑧are connected by a torsion spring.

⑨and④are connected by two M3 set screws.

· Control Subsystem
The control subsystem of the folding-wing UAV system adopts a portable design and is 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 into one compact and easy-to-use system. The joysticks, switches, and buttons on the control terminal or workstation are mapped to UAV operation commands. The folding-wing UAV features a simple operational logic with powerful capabilities. Its built-in link operates in the 1.4GHz frequency band, providing stable data transmission over a distance of 10 km. Additionally, it can be equipped with a 30 km or 50 km link as needed.

Figure 8: Physical Image of the Handheld Control Terminal

Figure 9: Physical Image of the Dual-Screen Workstation

· Launch Subsystem
The launch subsystem uses nitrogen as the power source and launches the folding-wing UAV by instantaneously releasing nitrogen gas. The subsystem features an integrated design with the following characteristics: easy operation, no infrared signature, low noise, no risk of explosion caused by propellant chamber ignition, and the ability to withstand low temperatures and high-altitude environments.

Figure 10: Physical Image of the Launch subsystem

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