CN107697281A - A kind of culvert vertical take-off and landing unmanned aerial vehicle - Google Patents

Abstract

The present invention relates to the technical field of unmanned aerial vehicles, in particular to a ducted vertical take-off and landing unmanned aerial vehicle. The vector duct nozzle; the aircraft nose and the aircraft tail are provided with aircraft tires; the aircraft tail is provided with an aircraft empennage; the movable duct device is arranged on the described machine arm. The unmanned aerial vehicle provided by the invention not only has multi-functionality, but also has higher safety performance. The design of the movable duct device adds a protective frame to the high-speed rotating movable blades, which reduces the contact area between the movable blades and foreign objects, and improves the safety performance and anti-interference ability.

Description

A ducted vertical take-off and landing unmanned aerial vehicle

technical field

The invention relates to an unmanned aerial vehicle, in particular to a ducted vertical take-off and landing unmanned aerial vehicle.

Background technique

In modern times, drones have gradually entered the lives of most people. Whether it is group activities or personal life, we can see drones everywhere. While drones are convenient for people's lives, they also increase Some interesting, especially for unmanned helicopters, whose vertical take-off and landing features are still the choice of most people. At present, most unmanned helicopters adopt the rotor design. The high-speed rotating rotor can provide the helicopter with lift and is the main power source of the aircraft. However, the high-speed rotating rotor has certain dangers, so most unmanned helicopters need to fly with each other when flying. Keep a certain distance between the obstacle and the human body.

Most of the unmanned aerial vehicles in the prior art are divided into two types, one is a fixed-wing unmanned aerial vehicle, and the other is an unmanned rotor helicopter. These two unmanned aerial vehicles have their own advantages and disadvantages. For example, fixed-wing drones have the characteristics of fast flight speed, but high take-off and landing conditions; unmanned rotor helicopters are slower than fixed-wing helicopters, but they have the characteristics of vertical take-off and landing. Therefore, along with the development of technology, people more and more hope to have a kind of aircraft that can have above-mentioned two common characteristics simultaneously.

Contents of the invention

In order to make up for the deficiencies of the prior art, the present invention provides a ducted vertical take-off and landing unmanned aerial vehicle, which adopts a movable duct design so that it has the characteristics of convenience, safety and multi-function.

The technical scheme of the present invention is as follows: a ducted vertical take-off and landing unmanned aircraft, comprising an aircraft body, the aircraft body comprising an aircraft nose, an arm, an aircraft tail, and a vector duct nozzle; the aircraft nose 1. The tail of the aircraft is equipped with aircraft tires; the tail of the aircraft is provided with an empennage; the arm of the aircraft is provided with a movable duct device;

The movable duct device includes a steering gear I, a transmission shaft, a steering gear fixing frame, a pull rod I, a bearing and a brushless ducted motor I, and the steering gear I is fixed on the machine arm through the steering gear fixing frame, and the steering gear The steering gear swing arm I is installed on the machine I, and the steering gear swing arm I is connected with the transmission shaft swing arm through the pull rod I; the transmission shaft is fixed on the machine arm through the bearing, and the brushless ducted motor I swings with the transmission shaft through the motor fixing frame. The arm connection is fixed;

The vector duct nozzle is fixed at the tail of the aircraft, and the vector duct nozzle includes steering gear II, pull rod II, loose leaf, model aircraft rudder angle, movable blades, brushless duct motor II, and air flow channel. The steering gear II and the brushless ducted motor II are fixed in the airflow channel, the steering gear II is equipped with a steering gear swing arm II, the tail of the airflow channel is connected to the movable blade through a loose leaf, and the movable blade is passed through the aircraft model rudder Angle and pull rod II are connected with steering gear swing arm II; there are two vector duct nozzles, symmetrically distributed on both sides of the aircraft body; there are two movable duct devices, symmetrically distributed on both sides of the aircraft body; Described aircraft empennage is double vertical empennage.

Further, the aircraft body is also provided with a battery, an electric regulator, a signal receiver and an aircraft model gyroscope.

Further, it also includes the use of the remote control of the model airplane.

The beneficial effects of the present invention are as follows:

(1) The present invention is designed with a movable duct device, which can control the tilting direction of the brushless ducted motor. Depending on the tilting direction of the brushless ducted motor, the aircraft can choose a vertical take-off and landing flight mode or a horizontal flight mode, Therefore the present invention has multifunctionality, and the user can select the flight mode according to his own preference. Due to the design of the movable duct device, the aircraft not only has multi-functionality, but also has high safety. The design of the movable duct device adds a protective frame to the high-speed rotating movable blades, which reduces the contact area between the rotating movable blades and foreign objects, and improves the safety performance and anti-interference ability.

(2) Both sides of the body of the present invention are also designed with vector duct nozzles and brushless duct motors. The brushless duct motors on both sides can not only improve the power of the aircraft, but the vector duct nozzles can also increase the maneuverability of the aircraft.

(3) The present invention has the characteristics of fast flight speed of fixed-wing aircraft, and the characteristics of vertical take-off and landing of vertical take-off and landing aircraft.

Description of drawings

Fig. 1 is a top view of the aircraft of the present invention;

Fig. 2 is the right side view of the aircraft of the present invention;

Fig. 3 is the front view of the aircraft of the present invention;

Fig. 4 is a top view of the movable duct device;

Fig. 5 is the right side view of movable duct device;

Fig. 6 is the front view of movable duct device;

Fig. 7 is a top view of the vector ducted spout;

Fig. 8 is the right view of the vector ducted spout;

Fig. 9 is the front view of the vector ducted spout;

Among them: 1. Aircraft body, 2. Aircraft nose, 3. Aircraft tires, 4. Arm, 5. Movable duct device, 6. Brushless ducted motor Ⅰ, 7. Aircraft tail, 8. Aircraft tail, 9. Vector duct nozzle, 5A, steering gear Ⅰ, 5B, transmission shaft, 5C, steering gear fixing frame, 5D, steering gear swing arm Ⅰ, 5E, pull rod Ⅰ, 5F, bearing, 5G, drive shaft swing arm, 5H , Motor fixing frame, 9A, steering gear II, 9B, steering gear swing arm II, 9C, pull rod II, 9D, loose-leaf, 9E, aircraft model rudder angle, 9F, movable blade, 9G, brushless ducted motor II, 9H, Airflow channel.

detailed description

Below in conjunction with accompanying drawing 1-9, the present invention is further explained:

A kind of ducted VTOL unmanned aerial vehicle, comprises aircraft body 1, and described aircraft body 1 comprises aircraft nose 2, machine arm 4, aircraft tail 7, vector duct nozzle 9; Described aircraft nose 2 , the aircraft tail 7 is provided with aircraft tires 3; the aircraft tail 7 is provided with an aircraft empennage 8; the movable duct device 5 is set on the described machine arm 4; the described movable duct device 5 comprises a steering gear I5A, transmission shaft 5B, steering gear fixing frame 5C, pull rod I5E, bearing 5F and brushless ducted motor I6, the steering gear I5A is fixed on the machine arm 4 through the steering gear fixing frame 5C, and the steering gear I5A is provided with The steering gear swing arm I5D, the steering gear swing arm I5D is connected with the transmission shaft swing arm 5G through the pull rod I5E; the transmission shaft 5B is fixed on the machine arm 4 through the bearing 5F, and the brushless ducted motor I6 is connected to the transmission shaft swing arm through the motor fixing frame 5H. The arm 5G is connected and fixed; the vector duct nozzle 9 is fixed on the aircraft tail 7, and the vector duct nozzle 9 includes steering gear II 9A, pull rod II 9C, loose leaf 9D, aircraft model rudder angle 9E, movable blade 9F, brushless Ducted motor II 9G, air flow channel 9H, the steering gear II 9A, brushless ducted motor II 9G are fixed in the air flow channel 9H, the steering gear II 9A is provided with a steering gear swing arm II 9B, and the tail of the air flow channel 9H The movable blade 9F is connected through the hinge 9D, and the movable blade 9F is connected with the steering gear swing arm II 9B through the model rudder angle 9E and the pull rod II 9C. There are two vector duct nozzles 9, symmetrically distributed on both sides of the aircraft body 1. There are two movable duct devices 5, symmetrically distributed on both sides of the aircraft body 1. The aircraft body 1 is also provided with a battery, an electric regulator, a signal receiver and an aircraft model gyroscope. Described aircraft empennage 8 is double vertical empennage. It also includes the use of the remote control of the model aircraft.

Aircraft body 1 of the present invention is made of plastic material and filled with foam material. It can be processed by injection molding and cutting. The outlet of airflow channel 9H is rectangular. There are three movable blades 9F, each corresponding to a steering gear II 9A. When the rotor of the brushless ducted motor II9G rotates at high speed, an airflow ejected to the tail is formed in the airflow channel 9H, and three movable blades 9F are arranged at the nozzle, and each movable blade 9F is connected to a steering gear II9A, which can be controlled by moving The vane 9F is used to change the direction of the jet airflow. That is, the movable vanes 9F of the spout can rotate in different directions to generate accelerations in different directions.

The present invention is an active duct aircraft. When a user uses it, the active duct device 5 and the vector duct nozzle 9 on the aircraft can be controlled by a remote controller. When the movable duct device 5 is working, the brushless duct motor Ⅰ6 can be tilted forward and backward. When tilting forward, the power direction of brushless duct motor Ⅰ6 is forward. The power direction of the motor I6 is backward, and the power direction of the brushless ducted motor I6 is vertically upward. The vector duct nozzle 9 is arranged on both sides of the aircraft body, and the movable vanes 9F of the nozzle can rotate in different directions to produce accelerations in different directions during its operation. When the upper and lower two movable blades 9F deflect upwards simultaneously, the aircraft tail 7 produces downward acceleration, and when the aircraft tail 7 deflects downwards simultaneously, the aircraft tail 7 produces an upward acceleration, and when the left and right two movable blades 9F deflect to the left simultaneously, the aircraft tail 7 produces rightward acceleration, and aircraft tail 7 produces leftward acceleration when deflecting to the right simultaneously. When the aircraft needs to hover, the brushless duct motor I6 of the movable duct device 5 can be controlled to tilt backward to offset the thrust from the brushless duct motor II9G of the vector duct nozzle 9.

Claims (3)

1. a ducted VTOL unmanned aerial vehicle, is characterized in that, comprises aircraft body (1), and described aircraft body (1) comprises aircraft nose (2), machine arm (4), aircraft tail ( 7), vector ducted nozzle (9); described aircraft nose (2), aircraft tail (7) are all provided with aircraft tires (3); described aircraft tail (7) is provided with aircraft empennage ( 8); The movable duct device (5) is set on the described machine arm (4); The movable duct device (5) includes a steering gear I (5A), a transmission shaft (5B), a steering gear fixing frame (5C), a pull rod I (5E), a bearing (5F) and a brushless ducted motor I ( 6), the steering gear I (5A) is fixed on the arm (4) through the steering gear fixing frame (5C), the steering gear I (5A) is provided with a steering gear swing arm I (5D), and the steering gear swings The arm I (5D) is connected with the transmission shaft swing arm (5G) through the pull rod I (5E); the transmission shaft (5B) is fixed on the machine arm (4) through the bearing (5F), and the brushless ducted motor I (6) passes through The motor fixing frame (5H) is connected and fixed with the transmission shaft swing arm (5G); The vector duct nozzle (9) is fixed on the aircraft tail (7), and the vector duct nozzle (9) includes steering gear II (9A), pull rod II (9C), loose leaf (9D), aircraft model rudder Angle (9E), movable vane (9F), brushless ducted motor II (9G), airflow passage (9H), the described steering gear II (9A), brushless ducted motor II (9G) are fixed on the airflow passage (9H), the steering gear II (9A) is provided with a steering gear swing arm II (9B), and the tail of the air flow channel (9H) is connected to the movable blade (9F) through a hinge (9D), and the movable The blade (9F) is connected with the steering gear swing arm II (9B) through the model rudder angle (9E) and the pull rod II (9C); the vector duct nozzles (9) are two, symmetrically distributed on the aircraft body (1) On both sides; there are two movable duct devices (5), which are symmetrically distributed on both sides of the aircraft body (1); the aircraft empennage (8) is a double vertical empennage. 2. The ducted vertical take-off and landing unmanned aerial vehicle as claimed in claim 1, wherein a battery, an electric regulator, a signal receiver and an aeromodelling gyroscope are also provided in the described aircraft body (1). 3. The ducted vertical take-off and landing unmanned aerial vehicle as claimed in claim 1, further comprising a remote control of a model aircraft.