CN215245509U

CN215245509U - Unmanned aerial vehicle with screw protection architecture

Info

Publication number: CN215245509U
Application number: CN202121910049.2U
Authority: CN
Inventors: 陈逸凡
Original assignee: Shanghai Hangdi Technology Co ltd
Current assignee: Shanghai Hangdi Technology Co ltd
Priority date: 2021-08-16
Filing date: 2021-08-16
Publication date: 2021-12-21
Anticipated expiration: 2031-08-16

Abstract

The utility model relates to an unmanned aerial vehicle with screw protection architecture, it includes organism and a plurality of rotor subassembly that sets up in the organism, the rotor subassembly includes the horn and sets up in the screw of horn, the horn rotates to be connected in the organism, the horn can be dismantled and be connected with the protection casing, the protection casing is tubulose and the screw is located to the cover, the organism is provided with and is used for doing the first buffering subassembly of buffering to the horn. The propeller damage probability can be reduced.

Description

Unmanned aerial vehicle with screw protection architecture

Technical Field

The application relates to the field of flight equipment, especially, relate to an unmanned aerial vehicle with screw protection architecture.

Background

An unmanned aerial vehicle is a short name of an unmanned plane and is an unmanned aerial vehicle operated by utilizing a radio remote control device and a self-contained program control device. Many rotor unmanned aerial vehicle is one of unmanned aerial vehicle, and when many rotor unmanned aerial vehicle when flying, the screw operation can produce great vibrations for unmanned aerial vehicle flight is not steady, thereby has the partial part of unmanned aerial vehicle to take place not hard up possibility, causes unmanned aerial vehicle's damage.

In order to solve the technical problems, the chinese patent with application number CN201822006045.6 in the related art discloses an unmanned aerial vehicle, which has the technical key points that: including the organism, the organism includes the cabin, installs in the flight control and the power in the cabin, and the organism is provided with a plurality of rotor subassemblies, and the rotor subassembly includes the horn and installs in the screw of horn, and the horn is installed in the cabin, and the cabin is provided with strutting arrangement, and strutting arrangement encircles the flight control setting, and the flight control is provided with one-level damping piece, and strutting arrangement is provided with second grade damping piece, and the power sets up on second grade damping piece. During flying, the possibility of vibration during flying control can be reduced through the buffering effect of the primary damping piece and the secondary damping piece, so that the flying is relatively stable, and the possibility of looseness of parts is reduced.

To the correlation technique among the above-mentioned, when unmanned aerial vehicle is flying, because receive the windage resistance or the flight orbit is improper to and because of the improper or field of vision blind area of operation easily when unmanned aerial vehicle descends, make the screw exist with the possibility that the object bumps on every side, thereby lead to the screw impaired, and then influence unmanned aerial vehicle's life.

SUMMERY OF THE UTILITY MODEL

In order to reduce the impaired possibility of screw, this application provides an unmanned aerial vehicle with screw protection architecture.

The application provides a pair of unmanned aerial vehicle with screw protection architecture adopts following technical scheme:

the utility model provides an unmanned aerial vehicle with screw protection architecture, includes organism and a plurality of rotor subassembly that sets up in the organism, the rotor subassembly includes the horn and sets up in the screw of horn, the horn rotates to be connected in the organism, the horn can be dismantled and be connected with the protection casing, the screw is located to the protection casing is tubulose and cover, the organism is provided with and is used for doing the first buffering subassembly of buffering to the horn.

By adopting the technical scheme, in flight, if the unmanned aerial vehicle is close to surrounding objects, the protective cover can isolate the propeller from the surrounding objects, so that the possibility that the propeller contacts the surrounding objects is reduced, and if the protective cover is damaged, the protective cover can be detached and replaced; simultaneously, when the protection casing struck to object around, first buffering subassembly can do the buffering to the horn to reduce the impact force that the screw received relatively, do the protection to the screw, reduce the impaired possibility of screw.

Optionally, the protective cover is provided as a mesh structure.

Through adopting above-mentioned technical scheme, when flying, network structure's protection casing can reduce the hindrance of protection casing to the air current relatively, and then reduces the interference to the propeller.

Optionally, the protection casing is provided with a plurality of mountings that are used for making the protection casing can dismantle with the horn and be connected, the mounting includes the fixed pin, the fixed pin slides and connects in the protection casing, the horn offer be used for with fixed pin complex fixed orifices.

Through adopting above-mentioned technical scheme, the fixed pin that slides and wear to locate the fixed orifices with the fixed pin to with the protection casing installation and be fixed in the horn.

Optionally, the fixing member further includes a first elastic member for driving the fixing pin to slide toward the fixing hole, and the first elastic member is fixedly connected to the fixing pin and the protective cover.

Through adopting above-mentioned technical scheme, the elastic component can order about the fixed pin and slide towards the fixed orifices to make the fixed pin can keep with fixed orifices matched with state, thereby reduce the possibility that the protection casing drops in the horn when flight.

Optionally, the first buffer assembly includes a first sleeve, a second elastic element and a first slide bar penetrating through and slidably connected to the first sleeve, the second elastic element is fixedly connected to the first sleeve and the first slide bar, the first sleeve is hinged to the machine body, and the first slide bar is hinged to the machine arm.

Through adopting above-mentioned technical scheme, when unmanned aerial vehicle and object striking around, receive the effect of second elastic component, first slide bar can slowly slide by first sleeve relatively to play the effect of buffering to the horn, reduce the impact force that the screw received relatively.

Optionally, the first slide bar is detachably connected with a blasting assembly for limiting the first slide bar to slide relative to the first sleeve, the blasting assembly comprises a breaking piece, the breaking piece comprises a fixed pipe and a plurality of breaking columns fixedly connected to the fixed pipe, the breaking columns are made of brittle materials, the fixed pipe is in threaded connection with the first slide bar, and the breaking columns are connected to the first sleeve.

By adopting the technical scheme, the blasting assembly limits the first sliding rod to slide relative to the first sleeve, so that the possibility of swinging between the horn and the machine body is reduced during flying; when the horn receives the striking, the fracture post receives the impact and breaks to remove the restriction that slides first slide bar relative first sleeve pipe, make first slide bar can be under the support of second elastic component, slowly slide relative first sleeve pipe, and then reduce the impact force that the screw received.

Optionally, the blasting assembly further includes a limiting ring detachably connected to the first sleeve, the limiting ring is provided with a clamping groove, the fracture column is clamped in the clamping groove, and the limiting ring is in threaded connection with the first sleeve.

Through adopting above-mentioned technical scheme, the draw-in groove can be fixed with the post that splits for the post that splits can be dismantled with first sleeve pipe through the retaining ring and be connected, and after receiving striking and the fracture post fracture, the retaining ring is dismantled to the accessible and the piece that splits is changed.

Optionally, the protection casing is provided with a plurality of collision boards, the protection casing is provided with a plurality of second buffer assembly that are used for doing the buffering to collision board.

Through adopting above-mentioned technical scheme, when unmanned aerial vehicle collided to object around, collision board and second buffering subassembly can reduce the impact that the protection casing received, further reduce the impact that unmanned aerial vehicle received simultaneously to further reduce the impaired possibility of screw.

Optionally, the second bolster includes second sleeve pipe, third elastic component and wears to establish and slide and connect in the second sheathed tube second slide bar, third elastic component fixed connection is in second sleeve pipe and second slide bar, second sleeve pipe fixed connection is in the protection casing, second slide bar fixed connection is in collision board.

Through adopting above-mentioned technical scheme, when unmanned aerial vehicle and object striking around, receive the effect of third elastic component, the second slide bar can slowly slide relative to the second sleeve pipe to reduce the striking degree to the protection casing, reduce the impaired possibility of screw.

In summary, the present application includes at least one of the following beneficial technical effects:

1. in flight, the protective cover can isolate the propeller from surrounding objects, reduce the possibility that the propeller contacts the surrounding objects, and can be detached and replaced according to requirements; when the protective cover impacts surrounding objects, the first buffer assembly can relatively reduce impact force on the propeller so as to protect the propeller and reduce the possibility of damage of the propeller;

2. the blasting assembly limits the first sliding rod to slide relative to the first sleeve, so that the possibility of swinging between the horn and the machine body is reduced during flying; when the horn receives the striking, the post that breaks receives the impact and breaks for first slide bar can slide slowly relative first sleeve under the support of second elastic component, and then reduces the impact force that the screw received.

Drawings

FIG. 1 is a schematic structural diagram of an embodiment of the present application;

FIG. 2 is a schematic cross-sectional view of a horn and shield according to an embodiment of the present disclosure;

FIG. 3 is an enlarged schematic view of portion A of FIG. 2;

FIG. 4 is an exploded view of a first cushioning assembly according to an embodiment of the present application;

FIG. 5 is an exploded view of a second cushioning assembly according to an embodiment of the present application;

fig. 6 is an enlarged structural view of a portion B in fig. 5.

Description of reference numerals: 1. a body; 2. a rotor assembly; 21. a horn; 211. a fixing hole; 22. a propeller; 3. a protective cover; 31. mounting grooves; 4. a first buffer assembly; 41. a first sleeve; 42. a second elastic member; 43. a first slide bar; 5. a fixing member; 51. a fixing pin; 511. a control lever; 52. a first elastic member; 6. a blasting assembly; 61. a breaking member; 611. a fixed tube; 612. breaking the column; 62. a confinement ring; 621. a card slot; 7. a collision plate; 8. a second buffer assembly; 81. a second sleeve; 82. a third elastic member; 83. a second slide bar.

Detailed Description

The present application is described in further detail below with reference to figures 1-6.

The embodiment of the application discloses unmanned aerial vehicle with screw protection architecture. Referring to fig. 1, the drone includes a body 1 and a plurality of rotor assemblies 2 mounted to the body 1, the rotor assemblies 2 including a horn 21 and a propeller 22 mounted to the horn 21.

The horn 21 is provided with the protection casing 3, and the protection casing 3 is tubulose and is network structure, and screw 22 is located to the cover 3 cover.

Referring to fig. 2 and 3, the protection cover 3 is provided with a plurality of fixing parts 5, so that the protection cover 3 is detachably connected to the horn 21 through the fixing parts 5, the installation groove 31 is formed in the protection cover 3, so that the horn 21 can be clamped in the installation groove 31, in this embodiment, the fixing parts 5 are provided in two numbers, each fixing part 5 comprises a fixing pin 51 and two first elastic pieces 52, the fixing pin 51 is inserted into and slidably connected to the side wall of the installation groove 31, and the horn 21 is provided with a fixing hole 211 for being matched with the fixing pin 51. The first elastic member 52 is configured as a spring, however, the first elastic member 52 may also be configured as an elastic shifting piece, and the first elastic member 52 is fixedly connected to the fixing pin 51 and the protection cover 3. The fixing pin 51 is fixedly connected with a control rod 511, the control rod 511 is arranged through the protection cover 3 in a penetrating and sliding mode, and the control rod 511 penetrates out of the protection cover 3.

In other embodiments, the protection cover 3 may be provided with one, three or another number of fixing members 5, and meanwhile, the fixing members 5 may be provided as bolts, so that the protection cover 3 is detachably connected with the horn 21 by the bolts.

Before the flight, wear to locate in the mounting groove 31 on the protection casing 3 with the horn 21 to make the fixed pin 51 can penetrate the fixed orifices 211, thereby install the protection casing 3 in the horn 21, first elastic component 52 can order about the fixed pin 51 and keep cooperating with the fixed orifices 211 this moment, makes when the flight, can reduce the protection casing 3 and the possibility that the horn 21 drops mutually.

In the flight in-process, when unmanned aerial vehicle was close to the object on every side, protection casing 3 can be isolated with screw 22 and object on every side, reduces the possibility that screw 22 contacted to the object on every side, when protection casing 3 damaged, accessible slide control lever 511 to control fixed pin 51 and slide towards the direction of keeping away from fixed orifices 211, thereby remove the restriction of fixed orifices 211 to protection casing 3, and then dismantle and change protection casing 3.

In order to reduce the impact force on the propeller 22 when the unmanned aerial vehicle strikes against the surrounding objects, the horn 21 is rotatably connected to the machine body 1, and the rotation axis of the horn 21 is horizontal.

Referring to fig. 4, the machine body 1 is provided with a first buffer assembly 4, the first buffer assembly 4 includes a first sleeve 41, a second elastic member 42 and a first slide bar 43, the first slide bar 43 coaxially penetrates and is slidably connected to the first sleeve 41, the second elastic member 42 is a spring, the second elastic member 42 is fixedly connected to the first sleeve 41 and the first slide bar 43, the first sleeve 41 is hinged to the machine body 1, the first slide bar 43 is hinged to the machine arm 21, and the rotation axes of the first sleeve 41 and the first slide bar 43 are both parallel to the rotation axis of the machine arm 21.

In other embodiments, the second elastic element 42 may be configured as an elastic pick, and of course, the first sleeve 41 may be hinged to the machine arm 21, and the first sliding rod 43 may be hinged to the machine body 1.

Referring to fig. 4, the first sliding rod 43 is provided with the blasting assembly 6, the blasting assembly 6 includes a breaking component 61 and a limiting ring 62, the breaking component 61 includes a fixing tube 611 and a plurality of breaking columns 612 fixedly connected to the fixing tube 611, the fixing tube 611 is coaxially sleeved on the first sliding rod 43, the fixing tube 611 is screwed to the first sliding rod 43, and the limit load borne by the plurality of breaking columns 612 when broken due to impact is 1-1.3 times of the gravity of the drone, in this embodiment, the number of the breaking columns 612 is four, and the four breaking columns 612 are arranged around the axis of the fixing tube 611, of course, the number of the breaking columns 612 may be two, three or other numbers, and the breaking columns 612 may also be arranged in a ring structure.

Referring to fig. 4, the limit ring 62 is sleeved on the fixed pipe 611, and the limit ring 62 is sleeved on and screwed to the first sleeve 41; the limiting ring 62 is provided with a clamping groove 621, the clamping groove 621 extends around the axis of the fixing pipe 611, and the breaking column 612 is clamped in the clamping groove 621, so that when the fixing pipe 611 is mounted on the first sliding rod 43 through threads, the breaking column 612 can rotate around the first sliding rod 43 in the clamping groove 621, and therefore the possibility that the breaking column 612 interferes with the mounting of the limiting ring 62 is reduced.

The blasting assembly 6 limits the first slide bar 43 to slide relative to the first sleeve 41, so that the possibility of swinging between the horn 21 and the machine body 1 is reduced during flight; when the horn 21 is impacted, the breaking column 612 is impacted and broken, so that the limitation of the sliding of the first sliding rod 43 relative to the first sleeve 41 is removed, the first sliding rod 43 can slowly slide relative to the first sleeve 41 under the support of the second elastic piece 42, the impact force on the propeller 22 is reduced, the propeller 22 is protected, and the possibility of damage to the propeller 22 is reduced.

When the breaking column 612 is broken, the limiting ring 62 and the breaking piece 61 are replaced by only detaching the limiting ring 62 and the breaking piece 61.

Referring to fig. 5 and 6, protection casing 3 is provided with a plurality of collision boards 7 and a plurality of second buffering subassembly 8, and collision board 7 can be to the protection casing 3 with around do the shelves that separate between the object for unmanned aerial vehicle can preferentially touch to collision board 7 when taking place the striking, receives the effect of second buffering subassembly 8 this moment, can reduce the impact that protection casing 3 received, further reduces the impact that unmanned aerial vehicle received simultaneously, thereby further reduces the impaired possibility of screw 22.

In this embodiment, the protection casing 3 is provided with two, and collision board 7 sets up in the one side that organism 1 was kept away from to protection casing 3, and collision board 7 is the arc and extends along 3 circumferences of protection casings. The protection casing 3 is provided with two second buffer 8, and two second buffer 8 set up respectively in two collision boards 7 one-to-one. The second buffer assembly 8 includes a second sleeve 81, a third elastic member 82 and a second slide bar 83, the second slide bar 83 is inserted into and slidably connected to the second sleeve 81, the second slide bar 83 is in a prism structure, the third elastic member 82 is a spring, the third elastic member 82 is fixedly connected to the second sleeve 81 and the second slide bar 83, the second sleeve 81 is fixedly connected to the collision plate 7, and the second slide bar 83 is fixedly connected to the protection cover 3.

In other embodiments, the impact plates 7 may also be provided in one, three or other number, and the second cushion assembly 8 may be provided in other number corresponding to the impact plates 7; the third elastic member 82 may be provided as an elastic pick; at the same time, it is also possible to fixedly connect the second sleeve 81 to the shield 3 and the second slide bar 83 to the impact plate 7.

The utility model provides an unmanned aerial vehicle's implementation principle with screw protection architecture does: before flying, the horn 21 is arranged in the mounting groove 31 of the shield 3 in a penetrating way, so that the fixing pin 51 can be driven by the first elastic piece 52 to penetrate into and be fixed in the fixing hole 211, and the shield 3 is mounted on the horn 21; the protection casing 3 can be isolated the screw 22 with the object around, reduces the possibility that the screw 22 contacted to the object around, if the protection casing 3 damages, only need slide the control lever 511 to the control fixed pin 51 slides towards the direction of keeping away from the fixed orifices 211, thereby removes the restriction of fixed orifices 211 to the protection casing 3, and then dismantles and changes the protection casing 3.

When the horn 21 is impacted, the breaking column 612 is impacted and broken, so that the limitation of the sliding of the first sliding rod 43 relative to the first sleeve 41 is removed, the first sliding rod 43 can slowly slide relative to the first sleeve 41 under the support of the second elastic piece 42, the impact force on the propeller 22 is reduced, the propeller 22 is protected, and the possibility of damage to the propeller 22 is reduced.

Simultaneously, collision board 7 can be to the protection casing 3 with around between the object do the shelves that separate for unmanned aerial vehicle can preferentially touch to collision board 7 when taking place the striking, receives the effect of second buffering subassembly 8 this moment, can reduce the impact that protection casing 3 received, further reduces the impact that unmanned aerial vehicle received simultaneously, thereby further reduces the impaired possibility of screw 22.

The above embodiments are preferred embodiments of the present application, and the protection scope of the present application is not limited by the above embodiments, so: all equivalent changes made according to the structure, shape and principle of the present application shall be covered by the protection scope of the present application.

Claims

1. The utility model provides an unmanned aerial vehicle with screw protection architecture, includes organism (1) and a plurality of rotor subassembly (2) that set up in organism (1), rotor subassembly (2) include horn (21) and set up in screw (22) of horn (21), its characterized in that: the aircraft engine is characterized in that the machine arm (21) is rotatably connected to the engine body (1), the machine arm (21) is detachably connected with the protective cover (3), the protective cover (3) is tubular and is sleeved on the propeller (22), and the engine body (1) is provided with a first buffer assembly (4) which is used for buffering the machine arm (21).

2. The unmanned aerial vehicle with propeller protection structure of claim 1, wherein: the protective cover (3) is of a net structure.

3. The unmanned aerial vehicle with propeller protection structure of claim 1, wherein: the protection casing (3) are provided with a plurality of mounting (5) that are used for making protection casing (3) can dismantle with horn (21) and be connected, mounting (5) are including fixed pin (51), fixed pin (51) slide and connect in protection casing (3), horn (21) are offered and are used for with fixed pin (51) complex fixed orifices (211).

4. The unmanned aerial vehicle with propeller protection structure of claim 3, wherein: the fixing piece (5) further comprises a first elastic piece (52) used for driving the fixing pin (51) to slide towards the fixing hole (211), and the first elastic piece (52) is fixedly connected with the fixing pin (51) and the protective cover (3).

5. The unmanned aerial vehicle with propeller protection structure of claim 1, wherein: the first buffer assembly (4) comprises a first sleeve (41), a second elastic piece (42) and a first sliding rod (43) which penetrates through the first sleeve (41) and is connected to the first sleeve (41) in a sliding mode, the second elastic piece (42) is fixedly connected to the first sleeve (41) and the first sliding rod (43), the first sleeve (41) is hinged to the machine body (1), and the first sliding rod (43) is hinged to the machine arm (21).

6. The unmanned aerial vehicle with propeller protection structure of claim 5, wherein: the first sliding rod (43) is detachably connected with a blasting assembly (6) used for limiting the first sliding rod (43) to slide relative to the first sleeve (41), the blasting assembly (6) comprises a breaking piece (61), the breaking piece (61) comprises a fixed pipe (611) and a plurality of breaking columns (612) fixedly connected to the fixed pipe (611), the breaking columns (612) are impacted, the limit load borne by the breaking columns (612) is 1-1.3 times of the gravity of the unmanned aerial vehicle, the fixed pipe (611) is in threaded connection with the first sliding rod (43), and the breaking columns (612) are connected to the first sleeve (41).

7. The unmanned aerial vehicle with propeller protection structure of claim 6, wherein: the blasting assembly (6) further comprises a limiting ring (62) detachably connected to the first sleeve (41), a clamping groove (621) is formed in the limiting ring (62), the breaking column (612) is clamped in the clamping groove (621), and the limiting ring (62) is connected to the first sleeve (41) in a threaded mode.

8. The unmanned aerial vehicle with propeller protection structure of claim 1, wherein: the protection casing (3) are provided with a plurality of collision boards (7), the protection casing (3) are provided with a plurality of second buffer components (8) that are used for buffering collision boards (7).

9. The unmanned aerial vehicle with propeller protection structure of claim 8, wherein: the second buffer assembly (8) comprises a second sleeve (81), a third elastic piece (82) and a second sliding rod (83) penetrating through and connected to the second sleeve (81) in a sliding mode, the third elastic piece (82) is fixedly connected to the second sleeve (81) and the second sliding rod (83), the second sleeve (81) is fixedly connected to the protective cover (3), and the second sliding rod (83) is fixedly connected to the collision plate (7).