CN213649894U

CN213649894U - Thrust vector tail sitting type vertical take-off and landing unmanned aerial vehicle

Info

Publication number: CN213649894U
Application number: CN202021217305.5U
Authority: CN
Inventors: 刘艳军; 吴海杰; 林玉祥; 罗竑; 梁斌
Original assignee: Universal Star Suzhou Co ltd
Current assignee: Universal Star Suzhou Co ltd
Priority date: 2020-06-28
Filing date: 2020-06-28
Publication date: 2021-07-09
Anticipated expiration: 2030-06-28

Abstract

The invention relates to the field of general aviation, in particular to a thrust vector tail-sitting type vertical take-off and landing unmanned aerial vehicle. Comprises a fuselage, a front wing, a rear wing outer wing, a vertical fin, a rear wing inner wing, a stay bar, a vector power device and a fixed power device; the front wing is horizontally and symmetrically arranged at the front part of the fuselage to form a left front wing and a right front wing, the rear wing inner wing is horizontally and symmetrically arranged at the tail part of the fuselage to form a left rear wing inner wing and a right rear wing inner wing, the left and right tips of the front wing and the rear wing inner wing are respectively and vertically connected through the stay bars to form left and right stay bars, and the rear wing outer wing is horizontally and symmetrically arranged at the left and right sides and is connected with the left and right stay bars to form a left and right rear wing outer wing; the vector power device is installed at the front end of the left stay bar and the right stay bar, the vertical tails are installed at the rear ends of the left stay bar and the right stay bar to form a left vertical tail and a right vertical tail, and the fixed power devices are symmetrically arranged on the front edges of the left rear wing outer. The unmanned aerial vehicle has the advantages of strong unmanned aerial vehicle control capability, higher reaction speed, higher load specific gravity and high machine body strength.

Description

Thrust vector tail sitting type vertical take-off and landing unmanned aerial vehicle

Technical Field

The invention relates to the field of general aviation, in particular to a thrust vector tail-sitting type vertical take-off and landing unmanned aerial vehicle.

Background

In the vertical take-off and landing unmanned aerial vehicle, the tail sitting type unmanned aerial vehicle is continuously developed in the market due to the characteristics of less dead weight and good flight performance, generally, four-rotor tail sitting type unmanned aerial vehicles are more, but wind resistance is resisted by changing the posture by increasing the rotating speed through the rotor, and power is consumed very much, so that an aircraft hovering accelerator is not too high, the take-off weight of the aircraft cannot be too large, a thrust-weight ratio of 1.5-2 needs to be ensured, and the load capacity is limited; in addition, during cruising, the propellers at the belly and the back cannot generate favorable slipstream to the wings, and are often required to be turned off, so that the propellers become waste; because the propeller rotation center of belly and back needs to have enough distance with the focus, will need thick big vertical fin, increase weight and resistance, big vertical fin also leads to forming strong door plant effect when meeting the crosswind moreover, and the aircraft need consume more energy and resist wind and keep the gesture.

Disclosure of Invention

The invention solves the technical problem of providing the thrust vector tail-sitting type vertical take-off and landing unmanned aerial vehicle which can improve the control surface efficiency and the cruising efficiency and has higher load proportion.

The technical scheme adopted by the invention for solving the technical problems is as follows:

a thrust vector tail sitting type vertical take-off and landing unmanned aerial vehicle comprises a body, a front wing, a rear wing outer wing, a vertical tail, a rear wing inner wing, a supporting rod, a vector power device and a fixed power device, wherein a flight control system, an electromechanical system and an aeronautical system are integrated in the body; the front wing is horizontally and symmetrically arranged at the front part of the fuselage to form a left front wing and a right front wing, the rear wing inner wing is horizontally and symmetrically arranged at the tail part of the fuselage to form a left rear wing inner wing and a right rear wing inner wing, the left and right tips of the front wing and the rear wing inner wing are respectively and vertically connected through the stay bars to form left and right stay bars, and the rear wing outer wing is horizontally and symmetrically arranged left and right and is connected with the left and right stay bars to form a left and right rear wing outer wing; the vector power device is installed at the front end of the left stay bar and the right stay bar, the vertical tails are installed at the rear ends of the left stay bar and the right stay bar to form a left vertical tail and a right vertical tail, and the fixed power devices are symmetrically arranged on the front edges of the left rear wing outer.

Furthermore, the vector power device comprises a propeller, a motor mounting seat and a steering engine, wherein the propeller is connected with a rotating shaft of the motor through a nut, the motor is mounted on the motor mounting seat, a U-shaped opening is formed in the front end of the stay bar, the motor mounting seat is mounted in the U-shaped opening through a vector power shaft, and the motor mounting seat can rotate around the vector power shaft; a steering engine groove is formed in the supporting rod at the rear end of the U-shaped opening, the steering engine is installed in the steering engine groove, a steering engine rocker arm is arranged on the steering engine, and the steering engine drives the steering engine rocker arm to rotate; a connecting shaft is fixed on the outer edge of the motor mounting seat, and the steering engine rocker arm is connected with the connecting shaft through a steering engine pull rod; the steering engine drives the steering engine rocker arm to rotate, the connecting shaft is driven to move through the steering engine pull rod, so that the motor mounting seat is driven to rotate around the vector power shaft, and the direction of the motor and the direction of the propeller are adjusted.

Furthermore, elevators are symmetrically arranged on the rear edges of the left front wing and the right front wing, the elevators are mechanically connected with steering gears through pull rods, signal lines of the steering gears are connected with the flight control system, and the flight control system sends instructions to control the elevators to deflect so as to realize pitching operation of the unmanned aerial vehicle.

Furthermore, the rear edges of the left rear wing outer wing and the right rear wing outer wing are symmetrically provided with ailerons, the ailerons are mechanically connected with a steering engine through a pull rod, a signal line of the steering engine is connected with a flight control system, and the flight control system sends an instruction to control deflection of the ailerons so as to realize rolling operation of the unmanned aerial vehicle.

Furthermore, rudders are symmetrically arranged on the rear edges of the left vertical tail and the right vertical tail and are mechanically connected with steering engines through pull rods, signal lines of the steering engines are connected with the flight control system, and the flight control system sends instructions to control the deflection of the rudders so as to realize the yaw operation of the unmanned aerial vehicle.

Further, the vertical fin may act as a landing gear.

Preferably, the fuselage is a streamlined fuselage.

The invention has the beneficial effects that:

the thrust vector power device at the front part of the stay bar can deflect in the same direction or in a differential mode, the attitude control capability is stronger than that of a four-rotor tail sitting type unmanned aerial vehicle, and the response is faster; distributed power can generate favorable interference on wings, and the control surface efficiency and the cruising efficiency are improved; has higher load specific gravity, and can be improved by 30 percent or higher compared with a four-rotor tail-sitting type unmanned aerial vehicle. The wind resistance is stronger: when the aircraft is suspended, the vector power deflects when strong wind is applied to the back or the abdomen, so that the attitude of the aircraft is stable; when the wind is in the front side wind, only two powers can be used for resisting wind in the four-axis layout, the pressure of the motor is high, the four rotors of the wind-resistant wind-.

Drawings

FIG. 1 is a perspective view of the present invention;

FIG. 2 is a block diagram of the vector power machine labeled 7 in FIG. 1;

labeled as:

1. fuselage, 2, front wing, 3, rear wing outer wing, 4, vertical fin, 5, rear wing inner wing, 6, vaulting pole, 7, vector power device, 8, fixed power device, 21, elevator, 31, aileron, 41, rudder, 701, screw, 702, motor, 703, motor mount pad, 704, steering wheel, 705, steering wheel rocking arm, 706, steering wheel pull rod, 707, vector power shaft, 708, connecting shaft.

Detailed Description

In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein.

It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present.

Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.

A thrust vector tail sitting type vertical take-off and landing unmanned aerial vehicle is shown in figure 1 and comprises a vehicle body 1, a front wing 2, a rear wing outer wing 3, a vertical tail 4, a rear wing inner wing 5, a stay bar 6, a vector power device 7 and a fixed power device 8, wherein the vehicle body 1 is in a streamline design, and a flight control system, an electromechanical system and an aeronautical system are integrated inside the vehicle body; the front wing 2 is horizontally and symmetrically arranged at the front part of the fuselage 1 to form a left front wing and a right front wing, the rear wing inner wing 5 is horizontally and symmetrically arranged at the tail part of the fuselage 1 to form a left rear wing inner wing and a right rear wing inner wing, the left tip part and the right tip part of the front wing 2 and the left tip part and the right tip part of the rear wing inner wing 5 are respectively and vertically connected through the stay bar 6 to form a left stay bar and a right stay bar, and the stay bar 6 is connected with the front wing and the rear. The rear wing outer wings 3 are horizontally and symmetrically arranged left and right and are connected with left and right support rods 6 to form left and right rear wing outer wings, vector power devices 7 are arranged at the front ends of the left and right support rods 6, vertical tails 4 are arranged at the rear ends of the left and right support rods to form left and right vertical tails, and fixed power devices 8 are symmetrically arranged at the front edges of the left and right rear wing outer wings 3.

Left and right front wing 2 rear edge symmetric arrangement has elevator 21, and elevator 21 passes through pull rod mechanical connection with the steering wheel, and the steering wheel signal line is connected with flight control system, and flight control system sends the instruction and controls elevator 21 deflection to realize unmanned aerial vehicle's every single move operation.

The rear edges of the left and right rear wing outer wings 3 are symmetrically provided with ailerons 31, the ailerons 31 are mechanically connected with a steering engine through a pull rod, a signal line of the steering engine is connected with a flight control system, and the flight control system sends an instruction to control the deflection of the ailerons 31 so as to realize the rolling operation of the unmanned aerial vehicle.

The left vertical tail 4 and the right vertical tail 4 are symmetrically provided with rudders 41 at the rear edges, the rudders 41 are mechanically connected with steering engines through pull rods, signal lines of the steering engines are connected with a flight control system, and the flight control system sends instructions to control the rudders 41 to deflect so as to realize the yaw operation of the unmanned aerial vehicle.

The vertical fin 4 in the embodiment can be used as an undercarriage in the parking state of the unmanned aerial vehicle.

As shown in fig. 2, the vector power device of the present embodiment includes a propeller 701, a motor 702, a motor mounting base 703 and a steering engine 704, the propeller 701 is connected with a rotating shaft of the motor 702 through a nut, the motor 702 is mounted on the motor mounting base 703, a U-shaped opening is formed at the front end of a strut 6, the motor mounting base 703 is mounted in the U-shaped opening through a vector power shaft 707, and the motor mounting base 703 can rotate around the vector power shaft 707. A stay bar at the rear end of the U-shaped opening is provided with a steering engine groove, a steering engine 704 is arranged in the steering engine groove, a steering engine rocker 705 is arranged on the steering engine 704, and the steering engine 704 drives the steering engine rocker 705 to rotate. A connecting shaft 708 is fixed on the outer edge of the motor mounting seat 703, the steering engine rocker 705 is connected with the connecting shaft 708 through a steering engine pull rod 706, the steering engine pull rod 706 is sleeved on the connecting shaft 708, and the steering engine pull rod 706 is in sliding connection with the connecting shaft 708. The steering engine 704 drives a steering engine rocker 705 to rotate, and a connecting shaft 708 is driven to move through a steering engine pull rod 706 so as to drive the motor mounting base 703 to rotate around a vector power shaft 707, so that the directions of the motor 702 and the propeller 701 are adjusted.

The flight process of the unmanned aerial vehicle:

the unmanned aerial vehicle starts, and left and right vector power device 7 and left and right fixed power device 8 start simultaneously to high-speed the rotation keeps the stable rising of unmanned aerial vehicle, after reacing appointed height, control left and right vector power device 7 and deflect, and control elevator 21 and aileron 31 cooperation and keep the gesture steady, thereby change into the level and fly, realize that unmanned aerial vehicle takes off to the conversion of patrolling and flying.

The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. The utility model provides a thrust vector tail sitting posture VTOL unmanned aerial vehicle which characterized in that: the airplane comprises an airplane body (1), a front wing (2), a rear wing outer wing (3), a vertical fin (4), a rear wing inner wing (5), a support rod (6), a vector power device (7) and a fixed power device (8), wherein a flight control system, an electromechanical system and an aeronautical system are integrated in the airplane body (1); the front wing (2) is horizontally and symmetrically arranged at the front part of the fuselage (1) to form a left front wing and a right front wing, the rear wing inner wing (5) is horizontally and symmetrically arranged at the tail part of the fuselage (1) to form a left rear wing inner wing and a right rear wing inner wing, the left and right tips of the front wing (2) and the rear wing inner wing (5) are respectively and vertically connected through the stay bar (6) to form a left stay bar and a right stay bar, and the rear wing outer wing (3) is horizontally and symmetrically arranged at the left and right sides and is connected with the left stay bar and the right stay bar (6) to form a left rear wing outer; the vector power device (7) is installed at the front end of the left stay bar (6), the vertical fin (4) is installed at the rear end of the left stay bar and the right stay bar to form a left vertical fin and a right vertical fin, and the fixed power devices (8) are symmetrically arranged on the front edges of the left rear wing outer wing.

2. The thrust vector tail-seated VTOL UAV of claim 1, wherein: the vector power device (7) comprises a propeller (701), a motor (702), a motor mounting seat (703) and a steering engine (704), wherein the propeller (701) is connected with a rotating shaft of the motor (702) through a nut, the motor (702) is mounted on the motor mounting seat (703), a U-shaped opening is formed in the front end of the stay bar (6), the motor mounting seat (703) is mounted in the U-shaped opening through a vector power shaft (707), and the motor mounting seat (703) can rotate around the vector power shaft (707); a steering engine groove is formed in the supporting rod at the rear end of the U-shaped opening, the steering engine (704) is installed in the steering engine groove, a steering engine rocker arm (705) is arranged on the steering engine (704), and the steering engine (704) drives the steering engine rocker arm (705) to rotate; a connecting shaft (708) is fixed on the outer edge of the motor mounting seat (703), the steering engine rocker arm (705) is connected with the connecting shaft (708) through a steering engine pull rod (706), the steering engine pull rod (706) is sleeved on the connecting shaft (708), and the steering engine pull rod (706) is connected with the connecting shaft (708) in a sliding mode; the steering engine (704) drives the steering engine rocker arm (705) to rotate, the connecting shaft (708) is driven to move through the steering engine pull rod (706), the motor mounting seat (703) is driven to rotate around the vector power shaft (707), and the directions of the motor (702) and the propeller (701) are adjusted.

3. The thrust vector tail-seated VTOL UAV of claim 2, wherein: left and right front wing (2) rear edge symmetrical arrangement has elevator (21), elevator (21) pass through pull rod mechanical connection with the steering wheel, the steering wheel signal line with flight control system connects, flight control system sends the instruction control elevator (21) deflect to realize unmanned aerial vehicle's every single move operation.

4. The thrust vector tail-seated VTOL UAV of claim 2, wherein: the rear edges of the left rear wing outer wing and the right rear wing outer wing (3) are symmetrically provided with ailerons (31), the ailerons (31) are mechanically connected with a steering engine through a pull rod, a signal line of the steering engine is connected with a flight control system, and the flight control system sends an instruction to control the deflection of the ailerons (31) so as to realize the rolling operation of the unmanned aerial vehicle.

5. The thrust vector tail-seated VTOL UAV of claim 2, wherein: rudders (41) are symmetrically arranged on the rear edges of the left vertical tail (4) and the right vertical tail (4), the rudders (41) are mechanically connected with steering engines through pull rods, signal lines of the steering engines are connected with a flight control system, and the flight control system sends instructions to control the deflection of the rudders (41) so as to realize the yaw operation of the unmanned aerial vehicle.

6. A thrust vector tail-seated vtol drone as claimed in any one of claims 1 to 5, characterized in that: the vertical fin (4) can be used as a landing gear.

7. The thrust vector tail-seated VTOL UAV of claim 6, wherein: the fuselage (1) is a streamlined fuselage.