CN211033014U

CN211033014U - Tilting type vertical take-off and landing unmanned aerial vehicle with five sets of propellers

Info

Publication number: CN211033014U
Application number: CN201921894695.7U
Authority: CN
Inventors: 钱永贵; 田正冲; 李旭
Original assignee: Nanjing Youyi Aviation Technology Co ltd
Current assignee: Nanjing Youyi Aviation Technology Co ltd
Priority date: 2019-11-06
Filing date: 2019-11-06
Publication date: 2020-07-17
Anticipated expiration: 2029-11-06

Abstract

A tilting type vertical take-off and landing unmanned aerial vehicle with five sets of propellers comprises a fuselage (4) and is characterized in that a front left wing (2) and a front right wing (5) are symmetrically arranged at the front part of the fuselage, a rear left wing (10) and a rear right wing (8) are arranged at the rear part of the fuselage, a vertical tail wing (9) is arranged at the tail part of the fuselage, a set of propeller mechanisms are respectively arranged on the front left wing (2), the front right wing (5), the rear left wing (10) and the rear right wing (8), and a fixed forward-pulling propeller (3) is arranged at the foremost end of the fuselage (4); the utility model discloses when promoting unmanned aerial vehicle speed of cruising by a wide margin, compare in the model cost reduction 3/5 above that all adopt four sets of helicopter mechanisms as power. The utility model adopts a propeller mechanism with relatively low price, thereby greatly reducing the cost; the propeller mechanism is simple to control and reliable in structure; after all the forward tension is converted, the cruising speed is greatly improved.

Description

Tilting type vertical take-off and landing unmanned aerial vehicle with five sets of propellers

Technical Field

The utility model relates to an unmanned aerial vehicle, it is a fixed wing unmanned aerial vehicle, specifically speaking is a formula of verting VTOL unmanned aerial vehicle of five sets of screws.

Background

At present, in order to increase the application occasions and cruising power of unmanned aerial vehicles, people begin to adopt composite wing structures. However, after the unmanned aerial vehicle takes off and flies flatly, part of the power devices become cumbersome, and even drag the cruising speed and flexibility of the unmanned aerial vehicle.

The composite wing type unmanned aerial vehicle is a relatively common unmanned aerial vehicle, and the most common method for the unmanned aerial vehicle in the process of converting forward flight during vertical lifting is that part of propellers generates forward flight power, and part of propellers still keep a vertical state and do not provide power any more. A solution must therefore be sought to make it possible to work several power plants in stages, all the less so as to make available power, even less superfluous or cumbersome. For this reason, there is currently no other solution than the american osprey.

SUMMERY OF THE UTILITY MODEL

The utility model aims at having the composite wing formula of current rise perpendicularly that unmanned aerial vehicle fixed wing mode flies the problem that rear portion transfer power device is out of work or even unnecessary, designs a formula of verting VTOL unmanned aerial vehicle of five sets of screws.

The technical scheme of the utility model is that:

a vertical take-off and landing unmanned aerial vehicle with five sets of propellers comprises a fuselage 4 and is characterized in that the front part of the fuselage is symmetrically provided with a front left wing 2 and a front right wing 5, the rear part of the fuselage is provided with a rear left wing 10 and a rear right wing 8, the tail part of the fuselage is provided with a vertical tail wing 9, the front left wing 2, the front right wing 5, the rear left wing 10 and the rear right wing 8 are respectively provided with a set of propeller mechanisms, and the foremost end of the fuselage 4 is provided with a fixed front pull propeller 3; when the unmanned aerial vehicle takes off, the four sets of propeller mechanisms provide vertical lift force, namely, the four sets of propeller mechanisms take off in a four-rotor mode, the front fixed forward pulling propeller (3) does not work temporarily, after the fixed forward pulling propeller (3) rises to a certain height, the fixed forward pulling propeller (3) starts to work, after the unmanned aerial vehicle has a certain forward flying speed in a fixed wing mode, the four sets of vertical propeller mechanisms start to slowly tilt forwards, and finally, the five sets of propeller mechanisms provide forward pulling force together, so that higher forward flying cruising speed is obtained; when the aircraft descends, the rear four sets of propeller mechanisms are switched to a vertical four-rotor mode, and the fixed forward-pulling propeller (3) stops working.

The propeller mechanisms are respectively a left front propeller mechanism and a tilting mechanism 1, a front right propeller mechanism and a tilting mechanism 6, a rear right propeller mechanism and a tilting mechanism 7, and a rear right propeller mechanism and a tilting mechanism 11 which are symmetrically arranged at the outermost ends of opposite wings.

The front left wing 2, the front right wing 5, the rear left wing 10 and the rear right wing 8 are all provided with ailerons.

The utility model has the advantages that:

1. the whole propeller mechanism with relatively low price is adopted, so that the cost is greatly reduced;

2. the propeller mechanism is simple to control and reliable in structure;

3. after all the forward tension is converted, the cruising speed is greatly improved.

Drawings

Fig. 1 is the structure schematic diagram of the utility model discloses an unmanned aerial vehicle's four sets of spirals in back when will provide the lift simultaneously.

Fig. 2 is a schematic structural diagram of the five sets of propeller mechanisms of the present invention when all provide forward pulling force.

Detailed Description

The present invention will be further described with reference to the accompanying drawings and examples.

As shown in fig. 1-2.

The utility model provides a tilting type VTOL unmanned aerial vehicle of five sets of screw, it includes fuselage 4, the anterior symmetry of fuselage be equipped with preceding left wing 2 and preceding right wing 5, the rear portion of fuselage is equipped with back left wing 10 and back right wing 8, preceding left wing 2, preceding right wing 5, back left wing 10 and back right wing 8 are the fixed wing, and all install the aileron that is used for turning to, rolling, as shown in figure 1, the afterbody of fuselage is equipped with vertical fin 9, preceding left wing 2, preceding right wing 5, install left screw mechanism and tilting mechanism 1 before a left side on back left wing 10 and the back right wing 8 respectively, preceding right screw mechanism and tilting mechanism 6, back right screw mechanism and tilting mechanism 7 and back right screw mechanism and tilting mechanism 11, their symmetry sets up the outermost end at the wing to. A fixed forward-pulling propeller 3 is mounted at the foremost end of the fuselage 4. The unmanned aerial vehicle of this embodiment adopts four sets can vert and one set fixed screw power take off overall arrangement that draws before, possesses the performance that flies before VTOL, higher speed.

The working principle of the utility model is as follows: during takeoff, the four sets of propeller mechanisms provide vertical lift force, namely take-off in a four-rotor mode, the front fixed forward-pulling propeller 3 does not work temporarily, after the fixed forward-pulling propeller 3 rises to a certain height, the fixed forward-pulling propeller 3 starts to work, after the unmanned aerial vehicle has forward flight speed in a certain fixed wing mode, the four sets of vertical propeller mechanisms start to slowly tilt forwards, and finally forward pulling force is provided by the five sets of propeller mechanisms together, so that higher forward flight cruising speed is obtained; when the aircraft descends, the rear four sets of propeller mechanisms are switched to a vertical four-rotor mode, and the fixed forward-pulling propellers 3 stop working.

The utility model discloses the part is like left screw mechanism and the mechanism 1 that verts before a left side, preceding right screw mechanism and the mechanism 6 that verts, back right screw mechanism and the mechanism 7 that verts and the mechanism 11 that verts concrete structure all with prior art the same or can adopt prior art to realize.

Claims

1. A tilting type vertical take-off and landing unmanned aerial vehicle with five sets of propellers comprises a fuselage (4) and is characterized in that a front left wing (2) and a front right wing (5) are symmetrically arranged at the front part of the fuselage, a rear left wing (10) and a rear right wing (8) are arranged at the rear part of the fuselage, a vertical tail wing (9) is arranged at the tail part of the fuselage, a set of propeller mechanisms are respectively arranged on the front left wing (2), the front right wing (5), the rear left wing (10) and the rear right wing (8), and a fixed forward-pulling propeller (3) is arranged at the foremost end of the fuselage (4); when the unmanned aerial vehicle takes off, the four sets of propeller mechanisms provide vertical lift force, namely, the four sets of propeller mechanisms take off in a four-rotor mode, the front fixed forward pulling propeller (3) does not work temporarily, after the fixed forward pulling propeller (3) rises to a certain height, the fixed forward pulling propeller (3) starts to work, after the unmanned aerial vehicle has a certain forward flying speed in a fixed wing mode, the four sets of vertical propeller mechanisms start to slowly tilt forwards, and finally, the five sets of propeller mechanisms provide forward pulling force together, so that higher forward flying cruising speed is obtained; when the aircraft descends, the rear four sets of propeller mechanisms are switched to a vertical four-rotor mode, and the fixed forward-pulling propeller (3) stops working.

2. The tilting type VTOL UAV of five propellers according to claim 1, wherein the propeller mechanisms are a front left propeller mechanism and a tilting mechanism (1), a front right propeller mechanism and a tilting mechanism (6), a rear left propeller mechanism and a tilting mechanism (7) and a rear right propeller mechanism and a tilting mechanism (11), respectively, which are symmetrically disposed at the outermost ends of the pair of wings.

3. The five-propeller tilting type VTOL UAV of claim 1, wherein the front left wing (2), the front right wing (5), the rear left wing (10) and the rear right wing (8) are all provided with ailerons.