CN220349975U

CN220349975U - Portable aircraft's collapsible hoist mechanism

Info

Publication number: CN220349975U
Application number: CN202322103562.6U
Authority: CN
Inventors: 唐云野; 金海玲; 韦炜
Original assignee: Shenzhen Zero Infinite Technology Co ltd
Current assignee: Shenzhen Zero Infinite Technology Co ltd
Priority date: 2023-08-04
Filing date: 2023-08-04
Publication date: 2024-01-16
Anticipated expiration: 2033-08-04

Abstract

The utility model discloses a foldable lifting mechanism of a portable aircraft, which comprises a horn and a rotor wing assembly, wherein one end of the horn is provided with a hinged sleeve, and the rotor wing assembly is arranged at the other end of the horn; the horn is of a round rod-shaped structure penetrating through the hollow inner cavity, and the hollow inner cavity of the horn forms a laying channel of the electrical connecting wire; the rotor assembly is hinged with one or more blades capable of being folded and contained, and a rotor motor; the rotor wing assembly is fixedly connected to the horn through the support frame seat; the support frame seat comprises a cylindrical sleeve which can be matched with the horn, and a mounting seat, wherein the mounting seat is provided with a support surface which can support and mount the rotor assembly and a wiring hole which can be connected with a rotor motor through a power supply connecting wire; the horn and the paddle are folded or unfolded doubly, the area of the paddle after being unfolded is large, the structure is simple and compact, the operation of unfolding, folding, containing and carrying is convenient, the occupied space after being folded is small, and the laying space requirement of an electrical connecting wire is met.

Description

Portable aircraft's collapsible hoist mechanism

Technical Field

The utility model belongs to the technical field of portable unmanned aerial vehicle manufacturing, and particularly relates to a foldable lifting mechanism of a portable aircraft.

Background

The portable unmanned aerial vehicle generally enables the unmanned aerial vehicle body to be integrated and contracted into a contracted body with smaller volume and more regular outline after the wings are folded and stored, so that the aims of folding, contracting, carrying and expanding and flying are achieved; in the wing structure capable of being folded and stored in the prior art, only the blades can be folded and stored or rotated and stored generally, the whole blade mounting mechanism cannot be folded and stored, and the area of the unfolded blades is limited; or the blades are arranged through a complex supporting arm folding structure, and the volume shrinkage after folding and storage is limited; for example, the patent number is CN202222728541.9, the patent name is a foldable four-rotor miniature unmanned aerial vehicle, the supporting arm structure is complex, the production process is complex, and the volume of the unmanned aerial vehicle after folding and storage is still larger. The prior art lacks one kind and can swiftly fold or expand, and occupation space is few after folding, and the folding elevating system of unmanned aerial vehicle that the paddle area is big after expanding still need consider the problem that electrical connection line laid when folding accomodate.

Disclosure of Invention

In order to solve the problems in the prior art, the utility model aims to provide a foldable lifting mechanism of a portable aircraft, which is convenient to unfold, fold, store and carry, simple and compact in structure, small in occupied space after folding and large in blade area after unfolding, and meets the laying space requirement of an electrical connecting wire.

The technical scheme adopted by the utility model is as follows:

the foldable lifting mechanism of the portable aircraft comprises an organic arm and a rotor wing assembly, wherein one end of the organic arm is provided with a hinged sleeve, and the rotor wing assembly is arranged at the other end of the organic arm;

the horn is of a round rod-shaped structure penetrating through the hollow inner cavity, and the hollow inner cavity of the horn forms a laying channel of the electrical connecting wire;

the rotor assembly is hinged with one or more blades capable of being folded and contained, and a rotor motor;

the rotor wing assembly is fixedly connected to the horn through a supporting frame seat;

the support frame seat comprises a cylinder sleeve which can be matched with the horn, and a mounting seat, wherein the mounting seat is provided with a support surface which can support and mount the rotor assembly and a wiring hole which can be connected to a rotor motor through a power supply connecting wire.

Further, the mounting seat comprises a seat body with a rectangular frame-shaped structure and a top plate fixedly arranged on the upper surface of the seat body, and the upper surface of the top plate forms a supporting surface capable of supporting and mounting the rotor wing assembly.

Further, the seat body is arranged along the horizontal direction, the inner end of the seat body is fixedly connected to the middle part of the cylindrical sleeve, and the space enclosed by the top plate and the seat body forms an electrical connection wire laying space; the top plate is provided with a waist round hole, and the waist round hole is used for enabling a power supply connecting wire to extend upwards from an electrical connecting wire laying space and be connected to the rotor motor; the kidney-shaped holes form wiring holes.

Further, the height of the seat body is larger than 1/4 of the outer diameter of the cylindrical sleeve and smaller than 1/2 of the outer diameter of the cylindrical sleeve.

Still further, one end of the hinge sleeve is fixedly sleeved on the horn through an elastic sleeve structure, the other end of the hinge sleeve is a hinge connection end, and the hinge connection end is used for rotatably connecting the horn to the body of the portable aircraft.

Still further, one end of the hinge sleeve is provided with an axial open slot, so that the part of the hinge sleeve corresponding to the open slot forms an elastic sleeve structure capable of being spread or contracted.

Still further, a pair of clamping blocks are arranged on the outer surface of the hinge sleeve at positions close to two sides of the opening notch part, and the clamping blocks are used for adjusting the width of the opening notch part.

Still further, the articulated connection end of the articulated sleeve is provided with a pair of step surfaces along the vertical direction, and the step surfaces are penetrated and provided with a hinge hole, and the hinge hole is used for the horn to be rotatably connected to the body of the portable aircraft through the hinge shaft.

Still further, the end face of the articulated housing corresponding to the articulated connection end is provided with a first inclined end face and a second inclined end face.

Finally, the lower surface of the base body is also provided with a bottom plate, so that the base body forms a U-shaped groove box-shaped structure with one end open.

The beneficial effects of the utility model are as follows:

a foldable lifting mechanism of a portable aircraft comprises a horn and a rotor wing assembly, wherein one end of the horn is provided with a hinged sleeve, and the rotor wing assembly is arranged at the other end of the horn; the horn is of a round rod-shaped structure penetrating through the hollow inner cavity, and the hollow inner cavity of the horn forms a laying channel of the electrical connecting wire; the rotor assembly is hinged with one or more blades capable of being folded and contained, and a rotor motor; the rotor wing assembly is fixedly connected to the horn through the support frame seat; the support frame seat comprises a cylindrical sleeve which can be matched with the horn, and a mounting seat, wherein the mounting seat is provided with a support surface which can support and mount the rotor assembly and a wiring hole which can be connected with a rotor motor through a power supply connecting wire; the horn and the paddle are folded or unfolded doubly, the area of the paddle after being unfolded is large, the structure is simple and compact, the operation of unfolding, folding, containing and carrying is convenient, the occupied space after being folded is small, and the laying space requirement of an electrical connecting wire is met.

Drawings

FIG. 1 is a schematic perspective view of a foldable lifting mechanism of a portable aircraft in an extended flight state according to an embodiment of the present utility model;

FIG. 2 is a schematic view of an exploded view of a foldable lifting mechanism of a portable aircraft in an extended flight configuration according to an embodiment of the present utility model;

fig. 3 to 4 are schematic perspective views of a horn of a foldable lifting mechanism of a portable aircraft according to an embodiment of the present utility model;

FIG. 5 is an enlarged schematic view of the planar configuration of a horn of a foldable lift mechanism for a portable aircraft in accordance with an embodiment of the present utility model;

fig. 6 to 7 are schematic perspective views of a foldable lifting mechanism of a portable aircraft according to an embodiment of the present utility model in a folded state;

fig. 8 is a schematic perspective view of a foldable storage and transportation unmanned aerial vehicle in a folded storage state according to the second embodiment of the present utility model;

fig. 9 is a schematic view of an explosive structure of the foldable storage and transport unmanned aerial vehicle in a flying state.

Detailed Description

The following description of the technical solutions in the embodiments of the present application will be made clearly and completely with reference to the accompanying drawings in the embodiments of the present application, and it is apparent that the described embodiments are only some embodiments of the present application, not all embodiments. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure.

As shown in fig. 1 to 7, the utility model provides a foldable lifting mechanism of a portable aircraft, and the overall planning scheme is as follows: the device comprises an organic arm 31 and a rotor wing assembly 32, wherein a hinge sleeve 34 is arranged at one end of the organic arm 31, and the rotor wing assembly 32 is arranged at the other end of the organic arm 31; the horn 31 can be hinged to the body of the portable aircraft by means of a hinge sleeve 34, so that the rotor assembly 32 is driven to rotate around a hinge point to be unfolded and flown or folded and stored, and the portable aircraft is formed.

The horn 31 has a circular rod-like structure penetrating through a hollow cavity provided therein, and the electrical connection wire 40 can be laid through the hollow cavity of the horn 31, thereby forming a laying passage for the electrical connection wire 40.

The rotor assembly 32 is formed by combining a rotor motor 39 and one or more paddles 33, wherein each paddle is respectively and hingedly connected to an output shaft of the rotor motor, so that each paddle can rotate around a hinge point to be opened for flying or folded and stored for portability; rotor assembly 32 is fixedly attached to horn 31 by a support frame mount 36.

The main structure of the supporting frame seat 36 is a cylindrical sleeve 361 and a mounting seat 362, the cylindrical sleeve 361 and the mounting seat 362 are integrally formed, or the cylindrical sleeve 361 and the mounting seat 362 are combined into an integral structure in a fixed connection mode; the cylinder sleeve 361 is adapted to the arm 31, so that the supporting frame seat 36 can be fixedly sleeved on the arm 31 through the cylinder sleeve 361.

Mount 362 has a support surface capable of supporting and mounting rotor assembly 32 and a wiring hole capable of connecting power feed connection wire 40 to rotor motor 39; the support frame seat realizes stable support and installation of the rotor wing assembly on the horn of the round bar structure through the cylinder sleeve and the installation seat, and has simple and compact structure, stability, reliability and convenient operation.

Further, the main structure of the mounting base 362 is a base 3621 having a rectangular frame structure, and a top plate 3622 fixedly provided on the upper surface of the base 3621, and the upper surface of the top plate 3622 forms a supporting surface capable of supporting and mounting the rotor assembly 32.

The base body 3621 with a rectangular frame-shaped structure is arranged along the horizontal direction, the inner end of the base body 3621 is fixedly connected to the middle part of the cylindrical sleeve 361, and a space surrounded by the top plate 3622 and the base body 3621 forms an electrical connection wire laying space; a waist hole is arranged on the top plate 3622, and the electric connection wire 40 can extend from the electric connection wire laying space to the upper side of the top plate to be connected to the rotor motor 39 after penetrating the top plate from the lower side to the upper side through the waist hole; the waist round hole forms a wiring hole.

And the height of the base body is larger than 1/4 of the outer diameter of the cylindrical sleeve and smaller than 1/2 of the outer diameter of the cylindrical sleeve, so that the raw material consumption is reduced as much as possible while the enough mechanical support strength is ensured, the self-load of the unmanned aerial vehicle is reduced, and the enough installation connection and electric circuit laying operation space is ensured.

Still further, one end of the hinge sleeve 34 is fixedly sleeved on the horn 31 through an elastic sleeve structure, and the other end of the hinge sleeve 34 is a hinge connection end, wherein the hinge connection end is used for rotatably connecting the horn 31 to a body of the portable aircraft.

Still further, one end of the hinge sleeve 34 is provided with an axial open slot 341, so that a portion of the hinge sleeve 34 corresponding to the open slot forms an elastic sleeve structure capable of being spread or contracted.

A pair of clamping blocks 342 are arranged on the outer surface of the hinge sleeve 34 at positions close to two sides of the opening notch part, and the width of the opening part of the opening groove 341 can be adjusted through the pair of clamping blocks 342, so that the hinge sleeve 34 can be fixedly connected to the arm in a fastening way or the hinge sleeve 34 can be detached from the arm; the specific width adjusting structure can directly adopt a hoop clamping adjusting structure similar to the hoop clamping adjusting structure in the prior art.

A pair of step surfaces 343 are provided in the vertical direction at the hinge connection end of the hinge bush 34, and hinge holes are provided through the step surfaces 343, through which the horn can be rotatably connected to the fuselage of the portable aircraft in a hinge connection manner by being fitted with the hinge shaft 35.

A first inclined end face 344 and a second inclined end face 345 are also provided on the end face of the hinge sleeve 34 corresponding to the hinge connection end; the first inclined end face 344 and the second inclined end face 345 can provide a rotating space for rotating, opening or folding and accommodating the horn, so that the horn is prevented from being blocked, the mechanical structure of the unmanned aerial vehicle is prevented from being damaged by friction of a sharp corner, and meanwhile, the stroke limiting purposes of rotating, opening and folding and accommodating can be further achieved by setting the inclined angles of the first inclined end face 344 and the second inclined end face 345; in this example, the space layout of the unmanned aerial vehicle body is adapted to be set as follows.

The solid part of the base body of the rectangular frame-shaped structure corresponding to the outer circumferential surface of the horn can be removed, so that the phenomenon that the solid part of the base body corresponding to the outer circumferential surface of the horn obstructs the laying operation space of the electrical connecting wire is avoided, and the laying space and the operation convenience of the electrical connecting wire are further improved.

Finally, can also set up a bottom plate again in the lower surface of pedestal for the pedestal constitutes one end open-ended U-shaped groove box-like structure, further promotes the wholeness ability of barrier propterty and outward appearance, but this scheme is operating inconveniently when wearing to dress connection electrical connection line, consequently selects the open frame structure in bottom of no bottom plate in this case, and electrical connection line's laying and motor's installation connect convenient operation.

The foldable lifting mechanism of the portable aircraft comprises a horn and a rotor wing assembly, wherein one end of the horn is provided with a hinged sleeve, and the rotor wing assembly is arranged at the other end of the horn; the horn is of a round rod-shaped structure penetrating through the hollow inner cavity, and the hollow inner cavity of the horn forms a laying channel of the electrical connecting wire; the rotor assembly is hinged with one or more blades capable of being folded and contained, and a rotor motor; the rotor wing assembly is fixedly connected to the horn through the support frame seat; the support frame seat comprises a cylindrical sleeve which can be matched with the horn, and a mounting seat, wherein the mounting seat is provided with a support surface which can support and mount the rotor assembly and a wiring hole which can be connected with a rotor motor through a power supply connecting wire; the horn and the paddle are folded or unfolded doubly, the area of the paddle after being unfolded is large, the structure is simple and compact, the operation of unfolding, folding, containing and carrying is convenient, the occupied space after being folded is small, and the laying space requirement of an electrical connecting wire is met.

The main body of each arm 31 is of a hollow round rod structure, the articulated sleeve 34 at the root of each arm 31 is of a corresponding cylindrical structure, an open slot is respectively arranged on each articulated sleeve 34, so that each articulated sleeve 34 also forms an elastic sleeve structure capable of being opened or contracted, a pair of clamping blocks are arranged on the outer surface of the articulated sleeve at positions close to the two sides of the end parts of the open slot, the width of the open slot is opened by the pair of clamping blocks, and the articulated sleeve can be easily sleeved at the root of the arm; after the articulated sleeve is sleeved at the root of the horn, the width of the opening groove is contracted by the pair of clamping blocks, so that the articulated sleeve is tightly sleeved at the root of the horn.

The rotor wing assembly on each horn 31 is arranged at the outer end of the horn, the concrete structure is that a support frame seat 36 with a rectangular frame structure with a cylindrical sleeve is arranged at the outer end of the horn of the hollow round rod, and the rotor wing assembly consisting of two paddles 33, a blade clamping mechanism 38 and a rotor wing motor 39 is fixedly supported and installed through the support frame seat 36.

The hollow inner cavity of the horn with the hollow round rod-shaped structure can be used as an electrical connection wire laying space similar to a wiring groove to lay an electrical connection wire 40, a threading hole is formed in the top plate of the supporting frame seat, and the electrical connection wire 40 can be connected to the rotor motor 39 from bottom to top through the threading hole so as to transmit current and control signals.

The specific detailed structural features of the rotor assembly of the present utility model may be directly described in the patent application No.: the rotor blade assembly structure in CN201980007500.9, the patent name of the "foldable rotor blade assembly and aircraft with foldable rotor blade assembly", can also be modified adaptively by referring to the rotor blade assembly structure therein, or can also be modified adaptively by directly adopting the rotor blade assembly structure of other structures in the prior art, or referring to the rotor blade assembly structure of other structures in the prior art.

Embodiment two: fig. 8-9 provide a portable unmanned aerial vehicle adopting the lifting mechanism according to the first embodiment, the specific structure is that the unmanned aerial vehicle main body 1, the lifting mechanism 3 and the load bin 4 are coaxially arranged from top to bottom in sequence, the load bin 4 is arranged below the unmanned aerial vehicle main body 1 in a hanging manner through the main shaft 2, the load can be transported through the load bin in the flying process, the gravity center position of the load is low, and compared with the prior art that the load is close to the unmanned aerial vehicle body, the portable unmanned aerial vehicle has more stable flying performance.

The foundation structure of the lifting mechanism 3 is provided with a plurality of arms 31, the root of each arm 31 is connected to the unmanned aerial vehicle main body 1 in a hinged connection mode through a hinge mechanism, so that each arm 31 can rotate around a hinge point respectively to be rotated to be opened to an extended flight state, or rotated to be folded to a position parallel to a main shaft, and each arm can be folded and stored in the extension range of the outer contour surface of the unmanned aerial vehicle main body.

A set of rotor wing assemblies 32 are respectively arranged at the outer end of each horn 31, and each set of rotor wing assemblies is respectively hinged with one or more blades 33 which can be folded and stored; when each arm rotates to open or fold and store, each blade can correspondingly rotate to open or fold and store; therefore, each horn and each blade can be rotated and opened around a hinge point, or rotated and folded to be parallel around the position of the main shaft 2 between the unmanned aerial vehicle main body 1 and the load bin 4; the device has the advantages of low gravity center position, capability of improving flight stability, convenience in unfolding, folding, storage and carrying, simple and compact structure, small volume and strong loading capacity.

The lifting mechanism 3 in this example is provided with four arms 31 in particular; a set of rotor wing assemblies are symmetrically arranged at the outer end of each horn 31, and a pair of foldable and storable paddles 33 are symmetrically arranged on each set of rotor wing assemblies 32; thereby constitute four rotor transportation unmanned aerial vehicle of collapsible accomodating.

The unmanned aerial vehicle main body 1 is formed by combining a shell 5, a battery pack module 6, a control module 7 and a support module 8, wherein the shell 5 adopts a cylindrical structure, and the battery pack module 6 is the battery module of the utility model; the battery pack module 6 and the control module 7 are fixedly arranged in the inner cavity of the shell 5 through the supporting module 8, so that the unmanned aerial vehicle main body is of a cylindrical structure; the load compartment 4 is also of cylindrical structure, and accordingly, when each horn 31 and each blade 33 are folded around the hinge point in a rotating manner to be parallel around the position of the main shaft 2 between the unmanned aerial vehicle body 1 and the load compartment 4, each horn 31 and each rotor assembly 32 are folded and folded into an approximately cylindrical structure. Because the shell 5 and the load bin 4 of the unmanned aerial vehicle main body 1 are both cylindrical structures, in this example, each horn 31 and each rotor wing assembly 32 are folded and folded to be within the extension range of the outer cylindrical surface of the unmanned aerial vehicle main body shell, or within the extension range of the outer cylindrical surface of the load bin; in the actual operation process, the outer diameter of the shell of the unmanned aerial vehicle main body can be equal to the outer diameter of the load bin, and the outer diameter of the load bin can be slightly larger than the outer diameter of the shell of the unmanned aerial vehicle main body. Even if the edge part of the blade slightly exceeds the extension range of the outer cylindrical surface of the unmanned aerial vehicle main body shell or the extension range of the outer cylindrical surface of the load bin in the actual operation process, the blade has certain flexibility and can be easily restrained through a binding belt, a sheath or other restraining structures with certain restraining force, so that the whole structure is approximately folded into a cylindrical structure after the battery module for the cylindrical transportation unmanned aerial vehicle is folded and stored, the unfolding, folding and storing operations are further promoted, the structure is simple and compact, and the effect of small volume is achieved.

On the basis that the housing 5 of the unmanned aerial vehicle body 1 adopts a cylindrical structure, the battery module 6, the control module 7 and the support module 8 are correspondingly also of a disc-shaped structure. The four machine arms 31 are uniformly distributed along the circumferential direction of the main support module 8, and the root parts of the machine arms 31 are respectively hinged on the support module 8; the outer side surface of the supporting module 8 is fixedly connected to the side wall of the shell 5, the main structure of the control module 7 is a flight control board, and the distributor board and the flight control board of the battery pack module 6 are sequentially and fixedly connected to the supporting module 8. Thereby can realize the fixed connection between all module assemblies and the casing 5 through supporting module 8, convenient operation, the technology is simplified, and the casing appearance is clean and tidy pleasing to the eye.

The horn reset and unfolding mechanism 9 is further arranged below the supporting module 8, and auxiliary reset force can be provided through the horn reset and unfolding mechanism 9 so as to assist in pushing the horn to rotate outwards around the hinge point for opening. The arm reset deployment mechanism 9 is also fixedly connected to the support module 8.

The middle part of the main shaft 2 is also fixedly provided with a horn storage rack 10, and the horn storage rack 10 is used for assisting in clamping all the horns after folding and storage.

The support module 8, the arm resetting and unfolding mechanism 9 and the arm storage rack 10 are sleeved and fixedly connected on the main shaft 2 at the same time.

The load bin 4 is of a cylindrical structure formed by combining an inner cylinder and an outer cylinder, and the middle parts of a top plate and a bottom plate of the load bin are penetrated and sleeved and fixedly connected to the position, close to the lower end, of the main shaft, and the middle parts of the top plate and the bottom plate of the load bin can be fixedly connected to the main shaft through conventional fixed connection technology means.

The concrete structure of the load bin can directly adopt the structure of the suspended transportation bin body in the same field in the prior art, and can also adopt the structure of the similar suspended storage bin body in other fields in the prior art.

Finally, three landing gears 41 are further arranged around the bottom end of the load bin 4, the three landing gears are uniformly distributed along the circumferential direction, each landing gear 41 can be detachably connected to the outer side face of the bottom end of the load bin 4 through a detachable bolt, and the landing gears in the prior art can be folded and stored or telescopic.

The portable unmanned aerial vehicle of the second embodiment is provided with the unmanned aerial vehicle main body, the lifting mechanism and the load bin coaxially from top to bottom in sequence, the load bin is arranged below the unmanned aerial vehicle main body in a hanging manner through the main shaft, and the flying and hovering stability performance is good; the lifting mechanism comprises a plurality of horn arms, the root of each horn arm is hinged on the unmanned aerial vehicle main body, the outer end of each horn arm is respectively provided with a rotor wing assembly, and each rotor wing assembly is respectively hinged with one or more paddles capable of being folded and stored; the battery pack module is formed by combining a plurality of batteries, and has long endurance time; each horn and each blade can be rotated and opened around a hinge point, or rotated and folded to be parallel around the position of the main shaft between the unmanned aerial vehicle main body and the load bin, and the unmanned aerial vehicle can be folded in an umbrella shape or automatically unfolded, and the unfolded horn is long, the blade area is large and the unmanned aerial vehicle is provided with a carrying capacity table in a flight mode; can reach the focus position low, can promote flight stability, expand, fold and accomodate and carry convenient operation, simple structure is compact, small, the strong effect of load capacity.

The utility model is not limited to the above-described alternative embodiments, and any person who may derive other various forms of products in the light of the present utility model, however, any changes in shape or structure thereof, all falling within the technical solutions defined in the scope of the claims of the present utility model, fall within the scope of protection of the present utility model.

Claims

1. A foldable lifting mechanism for a portable aircraft, comprising: the device comprises an organic arm and a rotor wing assembly, wherein one end of the organic arm is provided with a hinged sleeve, and the rotor wing assembly is arranged at the other end of the organic arm;

2. The portable aircraft collapsible lift mechanism of claim 1, wherein: the mounting seat comprises a seat body with a rectangular frame-shaped structure and a top plate fixedly arranged on the upper surface of the seat body, and the upper surface of the top plate forms a supporting surface capable of supporting and mounting the rotor wing assembly.

3. The portable aircraft collapsible lift mechanism of claim 2, wherein: the base body is arranged along the horizontal direction, the inner end of the base body is fixedly connected to the middle part of the cylindrical sleeve, and the space enclosed by the top plate and the base body forms an electrical connection wire laying space; the top plate is provided with a waist round hole, and the waist round hole is used for enabling a power supply connecting wire to extend upwards from an electrical connecting wire laying space and be connected to the rotor motor; the kidney-shaped holes form wiring holes.

4. A portable aircraft foldable lifting mechanism according to claim 3, wherein: the height of the seat body is greater than 1/4 of the outer diameter of the cylindrical sleeve and less than 1/2 of the outer diameter of the cylindrical sleeve.

5. The portable aircraft collapsible lift mechanism of claim 4, wherein: one end of the hinge sleeve is fixedly sleeved on the horn through an elastic sleeve structure, the other end of the hinge sleeve is a hinge connection end, and the hinge connection end is used for rotatably connecting the horn to the body of the portable aircraft.

6. The portable aircraft collapsible lift mechanism of claim 5, wherein: one end of the hinge sleeve is provided with an axial open slot, so that the part of the hinge sleeve corresponding to the open slot forms an elastic sleeve structure capable of being spread or contracted.

7. The portable aircraft collapsible lift mechanism of claim 6, wherein: the outer surface of the hinge sleeve is provided with a pair of clamping blocks at positions close to two sides of the opening notch part, and the clamping blocks are used for adjusting the width of the opening notch part.

8. The portable aircraft collapsible lift mechanism of claim 6, wherein: the articulated connecting end of the articulated sleeve is provided with a pair of step surfaces along the vertical direction, the step surfaces are penetrated and provided with articulated holes, and the articulated holes are used for enabling the horn to be rotatably connected to the body of the portable aircraft through the articulated shaft.

9. The portable aircraft collapsible lift mechanism of claim 8, wherein: the end face of the hinge sleeve corresponding to the hinge connection end is provided with a first inclined end face and a second inclined end face.

10. The portable aircraft collapsible lift mechanism of claim 2, wherein: the lower surface of the base body is also provided with a bottom plate, so that the base body forms a U-shaped groove box-shaped structure with one end open.