HW-V230 Vertical takeoff and landing fixed-wing UAV

As a new unmanned flight platform, HW-V230 Oil-Electric Hybrid Vertical Takeoff and Landing UAV combines the characteristic of the fixed-wing UAV with long flight time and fast speed and the characteristic of the rotary-wing UAV with easy take-off and landing operations and low site requirements. The fixed wing part adopts the layout of single wingwith high chord ratio, inverted V-shaped tail, double tail brace and rear-engine; Thequadrotor section is combined with the double tail brace of the fixed wing section. UAV cancarry photoelectric pod and data link to complete reconnaissance, tracking, positioning andother tasks.

1.1 Main Technical Indexes

The main technical indexes of HW-V230 Oil-Electric Hybrid Vertical Take-off and Landing UAV are shown in table 1-1
Table 1-1 UAV Main Technical Index

1.2 Main Features
➢ No tools required for quick loading and unloading.
All connections of the whole machine are equipped with fast locking mechanism, without any tools, the assembly of the whole machine can be completed quickly with bare hands, and the electrical connection can be completed automatically when the mechanical connection is completed. It can be finished in 2 minutes from unpacking to assembling. The aircraft takes off directly from the transportation box after assembly.
➢ Good maintainability
Lithium battery pack and fuselage adopt quick loading and unloading mechanism, the replacement of battery can be completed within 10 seconds, and quickly take off again to perform tasks.
➢ Small carrying volume
A UAV, a set of spare batteries, a charger and a charger DC power supply, and a spare parts package can all be put into a 1.5m×0.6m×0.7m transport case


2.1 The System Composition
HW-V230 Oil-Electric Hybrid Vertical Takeoff and Landing UAV system consists of aircraft platform subsystem, load subsystem, measurement and control and information transmission subsystem and ground support subsystem. The system is shown in graph 2-1
2.2 Aircraft Platform Subsystem
The appearance of the aircraft platform is shown in graph 2-2, which adopts the layout of high chord ratio straight wing and double tail brace. The photoelectric pod is mounted on the nose, the other airborne equipment is mounted in the middle of the fuselage, and the engine is located at the rear of the fuselage.

2.2.1 Airborne Equipment Layout
The layout of UAV airborne equipment is shown in graph 2-3. Wherein, flight controller, link equipment and navigation equipment are installed in the middle wing, which can realize rapid disassembly (simultaneous disassembly of electrical and structural components).


2.2.2 Airframe
The structure of UAV mainly includes fuselage, wing, tail strut and tail (as shown in graph 2-4), all of which are made of lightweight composite materials.
The main shape parameters are as follows：
➢ Length： 2.2m
➢ Height： 0.6m
➢ Wing Span： 4.0m