CN220743370U - Combined type vertical take-off and landing unmanned aerial vehicle - Google Patents

Abstract

The utility model provides a combined type vertical take-off and landing unmanned aerial vehicle, which can fold the unmanned aerial vehicle into a stable state with small volume and small hindered area as far as possible, reduce dead weight and resistance and flexibly adjust the positions and the number of rotary wings in the unmanned aerial vehicle. It comprises the following steps: positioning the moving member; a linking member comprising: the two wings are symmetrically arranged on the left side and the right side of the machine body respectively; a plurality of rotors detachably mounted on the front ends of the two wings in a horizontally unfolded state; the rotary folding mechanism is arranged in the machine body and is used for connecting the two wings with the machine body in a turnover folding manner; comprising: positioning moving component, linkage component and two turnover components; the positioning moving member can move back and forth and position along the length direction of the machine body, the inner end of the linkage member is connected with the positioning moving member, and the outer end of the linkage member is connected with the wing; the two overturning members are symmetrically arranged at the left and right sides of the machine body.

Description

Combined type vertical take-off and landing unmanned aerial vehicle

Technical Field

The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to a combined type vertical take-off and landing unmanned aerial vehicle.

Background

Conventional unmanned aerial vehicles fall into two categories: the fixed wing unmanned plane has the advantages of high speed and large task radius. But cannot be lifted vertically, so that the device is difficult to be deployed in places with limited space on a lifting field; the other type is an unmanned helicopter which can flexibly take off and land on a narrow field and hover over a target for a long time, but also has the inherent disadvantages of a helicopter, namely slow flying speed and small task radius. The vertical take-off and landing unmanned aerial vehicle has the advantages of the first two unmanned aerial vehicles: the device can vertically take off and land in a limited place without long-distance runway; the device can quickly fly to the upper part of the target to perform fixed-point hovering operation; meanwhile, the device also has the advantages of long voyage and long endurance time.

In the current vertical take-off and landing unmanned aerial vehicle, two types of unmanned aerial vehicles are mainly divided: one is that the wing is still a fixed wing structure, the wing is in an unfolding state when taking off and landing, has larger space requirement, can cause the increase of the taking off and landing resistance, and needs more power sources to overcome the resistance, thereby affecting the flying speed and the duration; another is a structure in which the wing is partially or wholly rotatable (foldable), for example, the main body of the wing is fixedly connected with the fuselage and is not rotatable, but the outer end (the extension length is 1/2 or 1/3 of the whole wing) can be rotated by 90 degrees and is fixedly provided with a rotor wing, the thrust direction of the rotor wing is adjusted by rotating the outer end, but the wing is still in a horizontally unfolded state when taking off and landing, and the space requirement and resistance are reduced to a limited extent. While the wing is entirely rotatable or foldable, the structure is typically rotatable in only one direction, e.g., horizontal or vertical. After the horizontal direction rotates, the unfolding degree of the wings can be reduced, so that the resistance is reduced, but the left wing and the right wing are in a left-right asymmetric state which are stacked up and down, so that a certain height difference is caused, the flight performance of the unmanned aerial vehicle is affected, and the stability of the parking state of the unmanned aerial vehicle is affected. The thrust direction of the rotor cannot be changed by rotating in the vertical direction, and a plurality of power mechanisms in directions are required to be arranged, so that the dead weight is increased. But the mechanism which can rotate in the horizontal direction and fold in the vertical direction is complex in structure, complex in assembly, high in cost and large in total weight, self weight and energy consumption are increased, and flying speed and duration are influenced. In addition, unmanned aerial vehicles generally cannot flexibly adjust the positions and the number of the rotor wings according to the flight purpose, and the adjustability and the maneuverability of the unmanned aerial vehicle are reduced.

Disclosure of Invention

The present utility model has been made to solve the above-mentioned problems, and an object of the present utility model is to provide a composite vertical take-off and landing unmanned aerial vehicle, which can fold the unmanned aerial vehicle into a stable state with a small volume and a small blocking area as much as possible, reduce the dead weight and the resistance, and flexibly adjust the positions and the number of the rotor wings in the unmanned aerial vehicle.

In order to achieve the above object, the present utility model adopts the following scheme:

the utility model provides a composite type vertical take-off and landing unmanned aerial vehicle, which is characterized by comprising the following components: a body;

the two wings are symmetrically arranged on the left side and the right side of the machine body respectively;

a plurality of rotors detachably mounted on the front ends of the two wings in a horizontally unfolded state;

the rotary folding mechanism is arranged in the machine body and is used for connecting the two wings with the machine body in a turnover folding manner; comprising: positioning moving component, linkage component and two turnover components; the positioning moving member can move back and forth and position along the length direction of the machine body, the inner end of the linkage member is connected with the positioning moving member, and the outer end of the linkage member is connected with the wing; the two overturning members are symmetrically arranged at the left side part and the right side part of the machine body;

wherein each of the flipping members includes: the device comprises a supporting unit, a turnover unit and a rotary connecting piece; the support unit has: a first splicing end which is of an inclined hemispherical structure and has a hemispherical cut side as a splicing surface, and a first link which extends from a spherical surface of the first splicing end to a side portion of the fuselage; the flipping unit has: the second splicing end is in an inclined hemispherical structure, the hemispherical notch side is used as a splicing surface to be matched and spliced with the first splicing end to form a sphere, and the second connecting rod extends outwards from the second splicing end to be connected with the wing; the connecting piece is rotated, the first splicing end and the second splicing end are coaxially connected along the diameter direction of the sphere, and the second splicing end can rotate back and forth relative to the first splicing end, so that the wing is driven to be converted between a horizontal unfolding state with the lower surface facing the bottom of the machine body and a vertical folding state with the lower surface facing the side part of the machine body.

Preferably, the composite vertical take-off and landing unmanned aerial vehicle according to the present utility model may further have the following features: two side fixing plates are arranged on the left side and the right side of the upper part of the main body of the machine body, and the side fixing plates are used as a part of the machine body for installing the overturning member; the lateral fixing plate extends sideways by a length exceeding the body of the fuselage by no more than 1/2 of the width of the fuselage. The wing and the overturning component are fixed with the main body of the fuselage more firmly through the structure.

Preferably, the composite vertical take-off and landing unmanned aerial vehicle according to the present utility model may further have the following features: the shape of the side fixing plate is as follows: the end parts are all any one of arc chamfer angles, right-angle triangles with the hypotenuse being concave arc shapes, rectangles and sectors.

Preferably, the composite vertical take-off and landing unmanned aerial vehicle according to the present utility model may further include: the telescopic mechanism comprises a plurality of telescopic units with adjustable telescopic capacity, the telescopic units are symmetrically arranged at the front ends of two wings, the front end of each telescopic unit is connected with the rotor wing, and the rear end of each telescopic unit is connected with the wing. The structure enables the extension of the rotor wing to be flexibly adjusted, so that the rotor wing is suitable for wings with different front end shapes, for example, the front end is inclined, and the length of the rotor wing extending out of the front end of the wing can be adjusted through the telescopic unit, so that all the rotor wings are positioned on the same plane, and stable thrust is provided.

Preferably, the composite vertical take-off and landing unmanned aerial vehicle according to the present utility model may further have the following features: the front ends of the two wings are symmetrically provided with mounting holes for mounting the rotor wings, and hole covers matched with the mounting holes for sealing the mounting holes when the rotor wings are not mounted.

Preferably, the composite vertical take-off and landing unmanned aerial vehicle according to the present utility model may further have the following features: positioning a moving member, comprising: the device comprises a T-shaped fixing frame provided with a transverse rod and two vertical rods which are arranged in parallel and are spaced from each other and extend backwards from the middle of the transverse rod to form a middle installation position, a screw rod which is arranged in the middle installation position and the front end of which is rotatably fixed at the middle of the transverse rod, a moving part which is connected with the screw rod in a threaded manner and moves back and forth along the axial direction of the screw rod along with the rotation of the screw rod, and a limiting part which limits the moving part to move only within a certain range in the axial direction of the screw rod.

Preferably, the composite vertical take-off and landing unmanned aerial vehicle according to the present utility model may further have the following features: a linking member comprising: the middle part of the axial linkage rod is fixedly connected with the moving part, and the two push-pull linkage rods are respectively connected with the two ends of the axial linkage rod; the rear end of the push-pull linkage rod is connected with the outer end of the axial linkage rod, and the front end of the push-pull linkage rod is used for being connected with the wing of the unmanned aerial vehicle.

Preferably, the composite vertical take-off and landing unmanned aerial vehicle according to the present utility model may further have the following features: the rotary connecting piece comprises a bolt, a bearing and a gasket, wherein the bolt coaxially connects the first splicing end and the second splicing end along the diameter direction of the sphere; the bearing is arranged in the ball body and is coaxial with the bolt, the inner ring of the bearing is connected with the rod part of the bolt, and the outer ring of the bearing is connected with the second splicing end; the gasket is disposed between the head of the bolt and the outer surface of the ball.

Preferably, the composite vertical take-off and landing unmanned aerial vehicle according to the present utility model may further have the following features: when the first connecting rod and the second connecting rod are in a parallel unfolding state, the first connecting rod and the second connecting rod are parallel to each other, and the included angle is 180 degrees; in the vertical folding state, the first connecting rod and the second connecting rod are mutually perpendicular, and the included angle is 90 degrees.

Preferably, the composite vertical take-off and landing unmanned aerial vehicle according to the present utility model may further have the following features: the axial linkage rod is connected with the push-pull linkage rod through a spherical hinge, and the push-pull linkage rod is connected with the wing through a spherical hinge.

Preferably, the composite vertical take-off and landing unmanned aerial vehicle according to the present utility model may further have the following features: the second connecting rod is connected with the front end of the inner side end surface of the wing in the parallel unfolding state, and the front end of the push-pull linkage rod is connected with the rear end of the inner side end surface of the wing in the parallel unfolding state.

Preferably, the composite vertical take-off and landing unmanned aerial vehicle according to the present utility model may further have the following features: the overturning component further comprises an auxiliary connecting piece, the shape of the auxiliary connecting piece corresponds to that of the inner side end face of the wing, and the second connecting rod is detachably and firmly connected with the inner side end face of the wing.

Preferably, the composite vertical take-off and landing unmanned aerial vehicle according to the present utility model may further have the following features: the positioning moving member further comprises a motor which is connected with the rear end of the screw rod and drives the screw rod to rotate back and forth.

Preferably, the composite vertical take-off and landing unmanned aerial vehicle according to the present utility model may further have the following features: the splicing surface forms a rotating surface of the sphere, and the rotating surface forms an included angle of 80-100 degrees with the axis of the bolt.

Preferably, the composite vertical take-off and landing unmanned aerial vehicle according to the present utility model may further have the following features: the rotating surface forms an included angle of 90 degrees with the axis of the bolt.

Preferably, the composite vertical take-off and landing unmanned aerial vehicle according to the present utility model may further have the following features: the area on the outer surface of the sphere corresponding to the head of the bolt is a plane corresponding to the gasket and the bolt.

Effects and effects of the utility model

On one hand, the multiple rotors are detachably arranged at the front ends of the two wings in a horizontal unfolding state, so that more rotors can be arranged according to flight requirements, for example, more thrust is needed; if the flight distance is short or the thrust requirement is low, the next part of the rotor wing can be disassembled, so that the dead weight is reduced, and the energy consumption and the abrasion are reduced; the position of a rotor wing in the unmanned aerial vehicle can be flexibly adjusted so as to adapt to different flight requirements; on the other hand, in the rotary folding mechanism, the positioning moving member can move and position back and forth along the length direction of the machine body, the inner end of the linkage member is connected with the positioning moving member, the outer end of the linkage member is connected with the wing, and the overturning members are symmetrically arranged at the left side part and the right side part of the machine body; in the upset component, owing to have supporting element, upset unit, rotate the connecting piece, the second concatenation end of two upset units can be rotated for the first concatenation end round trip of supporting element to drive two wings and together symmetrically change between the horizontal expansion state that the lower surface was unanimous with fuselage bottom orientation and the vertical folding state that the lower surface was opposite to with the fuselage lateral part, under this kind of circumstances, the wing is hindered the area minimum, consequently, when taking off and landing, can fold unmanned aerial vehicle into little volume, little hindered area and stable state as far as possible, reduce occupation space and resistance of taking off and landing. The utility model has simple structure, thereby effectively reducing dead weight.

Drawings

Fig. 1 is a schematic structural view of a composite vertical take-off and landing unmanned aerial vehicle according to an embodiment of the present utility model when a four-rotor wing is installed in a horizontally unfolded state;

fig. 2 is a schematic structural view of a rotor and a telescopic unit of the composite vertical lift unmanned aerial vehicle according to an embodiment of the present utility model;

fig. 3 is a schematic structural view of a composite vertical take-off and landing unmanned aerial vehicle according to an embodiment of the present utility model when six rotors are installed in a horizontally unfolded state;

FIG. 4 is a schematic view of a rotary folding mechanism according to an embodiment of the present utility model in a horizontally unfolded state; a portion of the wing structure is shown in order to illustrate the connection diagram;

FIG. 5 is a schematic view of the structure of the flip member according to the embodiment of the present utility model in a parallel deployment state; corresponds to the area indicated by the dashed box in fig. 4;

FIG. 6 is an exploded view of FIG. 5;

FIG. 7 is a schematic view of the structure of the invert member in an intermediate transition state according to an embodiment of the present utility model;

FIG. 8 is a schematic view of a rotary folding mechanism and a partial airfoil according to an embodiment of the present utility model in an intermediate transition state;

fig. 9 is a schematic structural diagram of a composite vertical take-off and landing unmanned aerial vehicle in an intermediate transition state according to an embodiment of the present utility model;

fig. 10 is a schematic structural view of a composite vertical take-off and landing unmanned aerial vehicle according to an embodiment of the present utility model in a vertically folded state;

FIG. 11 is a schematic view of a rotary folding mechanism and a partial airfoil according to an embodiment of the present utility model in a vertically folded configuration;

fig. 12 is a schematic structural view of a composite vertical lift unmanned aerial vehicle according to an embodiment of the present utility model in a vertically folded state.

Detailed Description

The composite type vertical take-off and landing unmanned aerial vehicle related to the utility model is described in detail below with reference to the accompanying drawings.

< example >

As shown in fig. 1 to 4, the hybrid vertical lift unmanned aerial vehicle 10 includes a fuselage 20, two wings 30, a tail wing 40, a plurality of rotors 50, a telescopic mechanism 60, and a rotary folding mechanism 70.

Two side fixing plates 21 are provided on both left and right sides of the upper portion of the main body of the body 20, and the side fixing plates 21 are used as a part of the body 20 for mounting the turnover member. The side fixing plates 21 extend sideways by a length not exceeding 1/2 of the body width of the body 20 or not exceeding the body width at all. In this embodiment, the side fixing plate 21 is shaped like a right triangle with arc chamfer at the end and concave arc bevel.

The two wings 30 are symmetrically arranged at the left and right sides of the fuselage 20 respectively, and the shape of the inner end part of the wings 30 is matched and corresponds to the shape of the side fixing plate 21. The front end of the wing 30 (front edge, upper part or bottom, as long as the rear rotor 50 is mounted to face forward) is provided with mounting holes for mounting the rotor 50, and a hole cover for plugging the mounting holes when the rotor 50 is not mounted is also provided to match the mounting holes. The mounting holes on the two wings 30 are symmetrically arranged with respect to each other with the axial direction of the fuselage as the central axis. The hole cover is connected with the hole by screw threads. The number of mounting holes on each wing 30 is set to 3 to 4.

The tail wing 40 is installed at the rear end of the fuselage 20, and includes a vertical tail wing and a horizontal tail wing, the horizontal tail wing providing a balance of pitch direction while cruising, and the vertical tail wing providing a balance of heading.

A plurality of rotors 50 are detachably mounted on the front ends of the two wings 30 in a horizontally deployed state. Rotor 50 should be even and symmetrically distributed when installed to provide symmetrical thrust. Specifically, rotor 50 is coupled to left and right wings 30 via telescoping mechanism 60 and extends toward the forward end of wings 30. As shown in fig. 1, 2 sets of 4 rotors 50 can be arranged in a general working mode, when the flight needs to transport heavier goods or the thrust lifting cruising speed or the working condition needs to be increased, more rotors 50 can be arranged on the wing 30, and as shown in fig. 3, 3 sets of 6 rotors 50 are arranged. While for short range low energy flight purposes, the number of rotors 30 may be reduced, for example, only 1 set of 2 rotors 50 may be provided. The rotor is self-contained, which is known in the art.

The telescopic mechanism 60 comprises a plurality of telescopic units 61 with adjustable telescopic amount, the number of the telescopic units corresponds to that of the rotary wings 50, the telescopic units are symmetrically arranged on the front ends of the two wings 30, the front end of each telescopic unit 61 is connected with the rotary wing 50, and the rear end of each telescopic unit is connected with the wing 30. The length of the rotor 30 extending out of the front end of the wing 30 can be adjusted by the telescopic unit 61, so that the rotor 30 is suitable for wings 30 with different front end shapes. In this embodiment, the front end of the wing 30 is inclined, and after the rotor 50 is installed, the extension length of each rotor 50 is adjusted by the telescopic mechanism 60, so that the blades of all the rotors 50 are at the same horizontal position.

As shown in fig. 4 to 6, a rotary folding mechanism 70 is installed in the fuselage 20 to connect the two wings 30 to the fuselage 20 in a flip-fold manner. The rotary folding mechanism 70 includes a positioning moving member 71, a linking member 72, and two flipping members 73.

The positioning moving member 71 can move and position back and forth along the length direction of the body 20. The positioning moving member 71 includes a T-shaped fixing frame 711, a screw 712, a moving piece 713, a stopper 714, and a motor 715. The T-shaped fixing frame 711 has a lateral bar 711a and two vertical bars 711b. Two vertical bars 711b extend rearward from the middle of the lateral bar 711a and are disposed in parallel with each other at intervals forming a middle mounting location. The lead screw 712 is installed in the middle installation position, and the front end is rotatably fixed in the middle of the lateral lever 711 a. The moving member 713 is screwed with the screw 712, and moves back and forth along the screw 712 in the axial direction as the screw 712 rotates; in this embodiment, the moving member 713 is a moving nut. The limiting member 714 limits the movement member 713 to move axially along the screw 712 only within a certain range I to II of the axial direction of the screw 712; in this embodiment, the limiting members 714 are two limiting members, which are respectively disposed at a position I and a position II in the axial direction of the screw 712. The motor 715 is connected with the rear end of the screw 712 and can drive the screw 712 to rotate forwards or reversely, so that the moving part 713 is driven to move back and forth between the position I and the position II; in this embodiment, the motor 715 is a small stepper motor, and the motor can drive the screw rod to rotate and fold the left and right wings 30 synchronously.

The inner end of the interlocking member 72 is connected to the positioning moving member 71, and the outer end is connected to the wing 30. The interlocking member 72 includes an axial interlocking lever 721 and two push-pull interlocking levers 722. The middle part of the axial linking lever 721 is fixedly connected to the moving member 713, and can move along with the movement of the moving member 713. Two push-pull links 722 are connected to both ends of the axial link 721, respectively. The rear end of the push-pull link 722 is connected to the outer end of the axial link 721 and the front end is adapted to be connected to the wing 30 of the unmanned aerial vehicle. In this embodiment, the rear end of the axial link 721 is connected to the outer end of the push-pull link 722 by a ball joint, and the front end of the push-pull link 722 is connected to the rear end of the inner end surface of the wing 30 in a parallel deployment state by a ball joint.

Two flipping members 73 are symmetrically installed at both left and right sides of the body 20. In this embodiment, two overturning members 73 are symmetrically disposed on two outer ends of the transverse bar 711a, and are located at the same height, and the outer ends are respectively connected with the wings 30 on the left and right sides of the unmanned aerial vehicle, so as to drive the wings 30 on the two sides to perform symmetrical overturning, folding and unfolding in three-dimensional space. As shown in fig. 5 to 7, each of the flipping members 73 includes a supporting unit 731 flipping unit 732, a rotating connector 733.

The supporting unit 731 has a first spliced end 731a and a first link 731b. The first spliced end 731a has an inclined hemispherical structure, and a hemispherical cut side is a spliced surface 731c. The first link 731b extends from the spherical surface of the first spliced end 731a to be connected to the outer end of the lateral bar 711 a.

The flipping unit 732 has a second splice end 732a and a second link 732b. The second splice end 732a is in an inclined hemispherical structure, and the hemispherical cut side as the splice face 42c is matched with the first splice end 731a to form a complete sphere Q. Second link 732b extends outwardly from second splice end 732a to connect with wing 30. In this embodiment, the second link 732b is connected to the front end of the inner end surface of the wing 30 in the parallel deployment state; the first link 731b and the second link 732b are coaxial, and the axes pass through the center of the sphere Q.

The rotational connector 733 coaxially connects the first and second splice ends 731a and 732a along the diameter of the sphere Q, and enables the second splice end 732a to rotate back and forth about the rotational connector 733 relative to the first splice end 731 a. In this embodiment, the axis of the rotation connector 733 is perpendicular to the splicing faces 731c and 42c, and passes through the center of the sphere Q. The mating surfaces 731c and 42c form a spherical surface of revolution that makes an angle of 80-100 with the axis of the bolt 733a, in this embodiment, 90 with the axis of the bolt 733 a.

The rotation connector 733 includes a bolt 733a, a bearing 43b, and a washer 733c. The bolt 733a coaxially connects the first and second splice ends 731a and 732a along the diameter direction of the sphere. The bearing 733b is provided in the ball coaxially with the bolt 733a, and an inner ring of the bearing 733b is connected to a stem portion of the bolt 733a and an outer ring is connected to the second splice end 732 a. The region on the outer surface of the sphere Q corresponding to the head of the bolt 733a is a plane corresponding to the washer 733c and the bolt 733 a. The spacer 733c is provided between the head of the bolt 733a and the outer surface plane area of the ball Q for increasing the contact area, reducing the pressure, and preventing loosening.

As shown in fig. 4 to 6, when the movable member 713 is at the position I, the wing 30 is in the parallel-extended state, the lower surface of the wing 30 (hereinafter, the lower surface of the wing in this state is all used) is oriented in line with the bottom of the body 20, and in this state, the first link 731b and the second link 732b are parallel to each other at an angle of 180 °; the corresponding composite vertical take-off and landing unmanned aerial vehicle 10 has a posture as shown in fig. 1, the unmanned aerial vehicle enters a cruising condition, and the rotor wings 50 are symmetrically distributed in front of the wings 30 to provide thrust in the horizontal direction. As shown in fig. 7 to 8, when the moving member 713 moves from the position I to the position II, the second link 732b rotates around the bolt 733a, the second link 732b forms an angle with the first link 731b of more than 90 ° and less than 180 °, and in this case, the wing 30 rotates from the parallel unfolded state along the splicing surface to an intermediate transition state in which the lower surface of the wing 30 forms a certain inclination angle with respect to both the bottom surface and the side surface of the T-shaped fixing frame 711; the pose of the corresponding composite vertical lift unmanned aerial vehicle 10 is shown in fig. 9. As shown in fig. 10 to 11, when the movable member 713 moves to the position II, the second link 732b rotates to be perpendicular to the first link 731b, the angle is 90 °, the wing 30 is folded vertically, the wing 30 is folded and turned to face the lower surface of the wing 30 to the side of the fuselage 20 (parallel to the axial direction of the fuselage 20), and the wing 30 is perpendicular to the ground, and the blocking area of the wing 30 is minimal; the corresponding composite vertical take-off and landing unmanned aerial vehicle 10 has a posture as shown in fig. 12, the unmanned aerial vehicle enters a vertical take-off and landing working condition, and the rotor wings 50 are symmetrically distributed above the wings 30 to provide thrust in the vertical direction.

Based on the above structure, the specific working process of the composite vertical take-off and landing unmanned aerial vehicle 10 provided in this embodiment is as follows:

when the hybrid vertical lift unmanned aerial vehicle 10 needs to enter the vertical lift working condition shown in fig. 12 from the cruising working condition shown in fig. 1, the motor 715 is adopted to drive the screw 712 to rotate in the preset direction a for a preset number of turns, so that the moving member 713 moves from the position I to the position II; in this process, the moving member 713 drives the second link 732b, the second link 732b drives the wing 30 to fold and turn over spatially, the wing 30 is constrained by the second link 732b to rotate relative to the first link 731b, the lower surface of the wing 30 has an inclination angle larger and larger relative to the bottom surface of the fuselage 20, when the motor 715 rotates for a predetermined number of turns, the moving member 713 moves from the position I to the position II, at this time, the second link 732b rotates to be perpendicular to the first link 731b, the wing 30 folds and turns over to be in a vertical folded state perpendicular to the lower surface, opposite to the side surface of the fuselage 20 and parallel to the axial direction of the fuselage 20, and enters a vertical lifting condition.

When the hybrid vertical lift unmanned aerial vehicle 10 needs to enter the cruising condition from the vertical lift condition, the motor 715 is adopted to drive the screw 712 to rotate in the opposite direction of A for a predetermined number of turns, so that the moving member 713 can move from the position II to the position I.

Through the structural design, the vertical take-off and landing on a limited field is realized. The occupied space of the whole machine is greatly reduced after the folding, and the storage and the transportation are convenient. The whole unmanned aerial vehicle does not adopt redundant mechanisms, has small dead weight and greatly reduces occupied space after being folded, and is greatly convenient for storage and transportation. The system can be applied to scenes such as emergency rescue, fire-fighting danger, material transportation, communication relay, weather forecast and the like, and can be deployed on ships and applied to military aspects.

The above is merely illustrative of the technical solution of the present utility model. The composite vertical take-off and landing unmanned aerial vehicle according to the present utility model is not limited to the structure described in the above embodiments, but is subject to the scope defined by the claims. Any modifications, additions or equivalent substitutions made by those skilled in the art based on this disclosure are within the scope of the utility model as claimed in the claims.

Claims (10)

1. Composite vertical take-off and landing unmanned aerial vehicle, its characterized in that includes:

a body;

the two wings are symmetrically arranged on the left side and the right side of the machine body respectively;

a plurality of rotors detachably mounted on the front ends of the two wings in a horizontally unfolded state;

the rotary folding mechanism is arranged in the machine body and is used for connecting the two wings with the machine body in a turnover folding manner; comprising: positioning moving component, linkage component and two turnover components; the positioning moving member can move back and forth and position along the length direction of the machine body, the inner end of the linkage member is connected with the positioning moving member, and the outer end of the linkage member is connected with the wing; the two overturning members are symmetrically arranged at the left side part and the right side part of the machine body;

wherein each of the flipping members includes: the device comprises a supporting unit, a turnover unit and a rotary connecting piece; the support unit has: a first splicing end having an inclined hemispherical structure with a hemispherical cut side as a splicing surface, and a first link extending from a spherical surface of the first splicing end to a side portion connected to the fuselage; the flipping unit has: the second splicing end is of an inclined hemispherical structure, the hemispherical notch side is used as a splicing surface to be matched and spliced with the first splicing end to form a sphere, and the second connecting rod extends outwards from the second splicing end to be connected with the wing; the connecting piece is rotated to enable the first splicing end and the second splicing end to be coaxially connected along the diameter direction of the sphere, and the second splicing end can rotate back and forth relative to the first splicing end, so that the wing is driven to be converted between a horizontal unfolding state in which the lower surface and the bottom of the wing face towards the same direction and a vertical folding state in which the lower surface and the side of the wing face each other.

2. The composite vertical take-off and landing unmanned aerial vehicle of claim 1, wherein:

two side fixing plates are arranged on the left side and the right side of the upper part of the main body of the machine body, and are used as a part of the machine body for installing the turnover component;

the side fixing plates extend sideways by a length exceeding the body by no more than 1/2 of the body width.

3. The composite vertical take-off and landing unmanned aerial vehicle of claim 2, wherein:

wherein, the lateral fixing plate has the shape: the end parts are all any one of arc chamfer angles, right-angle triangles with the hypotenuse being concave arc shapes, rectangles and sectors.

4. The composite vertical lift unmanned aerial vehicle of claim 1, further comprising:

the telescopic mechanism comprises a plurality of telescopic units with adjustable telescopic capacity, the telescopic units are symmetrically arranged at the front ends of the two wings, the front ends of the telescopic units are connected with the rotor wings, and the rear ends of the telescopic units are connected with the wings.

5. The composite vertical take-off and landing unmanned aerial vehicle of claim 1, wherein:

the wing mounting device comprises a wing, a wing cover and a hole cover, wherein the front ends of the wing are symmetrically provided with mounting holes for mounting the rotor wing, and the hole cover is matched with the mounting holes and used for sealing the mounting holes when the rotor wing is not mounted.

6. The composite vertical take-off and landing unmanned aerial vehicle of claim 1, wherein:

wherein the positioning moving member includes: the device comprises a T-shaped fixing frame provided with a transverse rod and two vertical rods which are arranged in parallel and are spaced from each other and extend backwards from the middle of the transverse rod to form a middle installation position, a screw rod which is arranged in the middle installation position and the front end of which is rotatably fixed in the middle of the transverse rod, a moving part which is connected with the screw rod in a threaded manner and moves back and forth along the axial direction of the screw rod along with the rotation of the screw rod, and a limiting part which limits the moving part to move only within a certain range in the axial direction of the screw rod.

7. The composite vertical take-off and landing unmanned aerial vehicle of claim 6, wherein:

wherein, the interlock component includes: the middle part of the axial linkage rod is fixedly connected with the moving part, and the two push-pull linkage rods are respectively connected with the two ends of the axial linkage rod; the rear end of the push-pull linkage rod is connected with the outer end of the axial linkage rod, and the front end of the push-pull linkage rod is used for being connected with the wing of the unmanned aerial vehicle.

8. The composite vertical take-off and landing unmanned aerial vehicle of claim 1, wherein:

wherein the rotary connecting piece comprises a bolt, a bearing and a gasket;

the bolt coaxially connects the first splicing end and the second splicing end along the diameter direction of the sphere;

the bearing is arranged in the ball body and is coaxial with the bolt, the inner ring of the bearing is connected with the rod part of the bolt, and the outer ring of the bearing is connected with the second splicing end;

the gasket is arranged between the head of the bolt and the outer surface of the sphere.

9. The composite vertical take-off and landing unmanned aerial vehicle of claim 1, wherein:

when the first connecting rod and the second connecting rod are in a parallel unfolding state, the first connecting rod and the second connecting rod are parallel to each other, and an included angle is 180 degrees; in the vertical folding state, the first connecting rod and the second connecting rod are mutually perpendicular, and the included angle is 90 degrees.

10. The composite vertical take-off and landing unmanned aerial vehicle of claim 7, wherein:

the axial linkage rod is connected with the push-pull linkage rod through a spherical hinge, and the push-pull linkage rod is connected with the wing through a spherical hinge.