Fixed Wing Drones

HW-V230 Vertical takeoff and landing fixed-wing UAV

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Description
Specifications
1 Introduction
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 The System Composition and Technical Indicators

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


Graph 2-1 UAV System Composition

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.

Graph 2-2 The Appearance of the Aircraft Platform

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).

Graph 2-3 UAV Airborne Equipment Layout

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


Graph 2-4 UAV Structural Design Drawing

2.2.3 Control System
The UAV control system mainly includes autopilot, GPS antenna, dual antenna navigation equipment and so on. Among them, GPS antenna is multi-mode antenna with strong anti-interference ability.
2.2.3.1 Main Technical Features
  The control system has the following features:
➢ Intelligent flight control mode: precise vertical take-off and landing control, support for off-site landing, freely switch flight control modes such as full autonomy, stabilization and remote control, and the UAV can work independently;
➢ High-precision motion measurement: measure the position, speed and attitude information of the UAV during flight;
➢ High integration design: highly integration, small size and low power consumption;
➢ Harsh environment adaptability and reliability: -40~60 degrees Celsius, stable operation under 95% humidity environment;
➢ Complete emergency response: Lose stars normally hover and land to ensure maximum flight safety.
2.2.3.2 Main Performance Indicators

The main performance indicators of the flight control system are shown in Table 2-1.
Table 2-1 The Main Indicators of the Flight Control System

Name Indicator
Satellite Navigation GPS/MINS Integrated Navigation
Accuracy of Position
Measurement ±10m RMS
Accuracy of Height
Measurement ±15m RMS
Heading Accuracy ±0.2° RMS(1σ,Double antenna)
Attitude Accuracy ±1° RMS(1σ)

2.2.3.3 Flight Control Mode

The UVA flight control system has two flight control modes: Program Control and Manual Control.

Program Control Mode:

Before take-off, the predetermined flight track data will be bound to the UAV flight control equipment, and flight track flight control will be carried out according to the bound flight track, so as to realize the reconnaissance of the designated target area or target point. The flight path can be changed by uploading and changing the flight path in real time. After completing the task, the UAV will be guided to the recovery area according to the predetermined track to complete autonomous recovery.

Manual Control Mode:

When the measurement and control data link is effective, the UAV can be remotely flown through the ground station. Through the "man-in-loop" control mode, the ground observation and control station sends remote control commands and controls the UAV to execute relevant commands.

2.2.4 Propulsion System

   The power system is divided into two parts: motor system and oil engine system. The motor system provides lift during the vertical take-off and landing phase of the UAV, while the oil engine system provides forward thrust during the flight.

  Among them, the motor system is composed of four electric motors and electric harmonic propeller. The oil engine system USES a 4kW two-cylinder gasoline piston engine as the cruise power, and can also be replaced with the same type of heavy oil piston engine, which is suitable for use on the ship and in the forest area. The oil engine system is mainly composed of engine, ECU, propeller, oil tank, oil road and so on.

2.2.5 Electric System

   The onboard electrical system has the functions of power supply and distribution, electrical control and electrical connection to ensure the normal use of electricity of each subsystem, and connect each subsystem into an organic whole to work together. Airborne electrical equipment mainly includes power battery, equipment battery, generator, power supply and distribution equipment and airborne cable network.
   The electricity consumption statistics of airborne equipment are shown in table 2-2.
   Table 2-2 The Electricity Consumption Statistics of Airborne Equipment

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