CN111452577A

CN111452577A - Triphibian carrying aircraft

Info

Publication number: CN111452577A
Application number: CN202010413637.9A
Authority: CN
Inventors: 李东; 宋晶; 张贝贝; 姬庆玲; 沙莉; 李明聪; 王海伟
Original assignee: Wuhan City Vocational College
Current assignee: Wuhan City Vocational College
Priority date: 2020-05-15
Filing date: 2020-05-15
Publication date: 2020-07-28

Abstract

The invention relates to the field of unmanned aerial vehicles, in particular to a land, water and air triphibian carrier aircraft, which comprises an unmanned aerial vehicle, an outer shell, an automatic inflation separation mechanism, an automatic contraction lifting mechanism and an automatic rotation driving mechanism, wherein the automatic rotation driving mechanism is arranged inside the outer shell, the automatic inflation separation mechanism comprises a round sleeve, an inflation motor and two separation motors, output shafts of the two separation motors are respectively connected with a threaded rod, a separation sheet is arranged on the threaded rod, inflation heads are respectively arranged at the lower ends of the separation sheets, two micro gas cylinders are arranged inside the round sleeve, one-way ventilation mechanisms are arranged in bottle mouths of the micro gas cylinders, and air bags are respectively arranged at the other ends of the two inflation heads Search for and rescue multi-functional operation ability such as, abandoned the comparatively single disadvantage of traditional unmanned aerial vehicle function, accord with the demand in market.

Description

Triphibian carrying aircraft

Technical Field

The invention relates to the field of unmanned aerial vehicles, in particular to a triphibian carrying aircraft.

Background

An unmanned aircraft, abbreviated as "drone", and abbreviated in english as "UAV", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer.

Drones tend to be more suitable for tasks that are too "fool, dirty, or dangerous" than are manned aircraft. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle + the industry application is really just needed by the unmanned aerial vehicle; at present, the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand industrial application and develop unmanned aerial vehicle technology. Search for and rescue unmanned aerial vehicle is the collective term of unmanned vehicles in fact, can divide into from the technical perspective: unmanned fixed wing aircraft, unmanned VTOL aircraft, unmanned airship, unmanned helicopter, unmanned multi-rotor aircraft, unmanned paravane, etc.

Add the search and rescue function in unmanned aerial vehicle, can shorten the rescue time, loss is retrieved to the at utmost, and traditional unmanned aerial vehicle can only be in aerial operation, has very big limitation to land or operation on water, in order to realize that unmanned aerial vehicle can carry out tasks such as search and rescue, delivery in water, land and sky homoenergetic, we have designed an amphibious carrying aircraft.

Disclosure of Invention

The invention aims to solve the technical problem of providing a triphibian water, land and air carrying aircraft, which realizes the triphibian operation function on water, land and air, integrates the multifunctional operation capabilities of carrying, search and rescue and the like, and eliminates the defect that the traditional unmanned aerial vehicle has single function.

In order to solve the technical problems, the invention provides the following technical scheme:

the utility model provides a triphibian air vehicle, including unmanned aerial vehicle, the shell body, automatic inflation separating mechanism, automatic contraction elevating system and automatic rotation driving mechanism, the shell body is fixed to be set up at unmanned aerial vehicle's bottom, automatic inflation separating mechanism level sets up in the inside of shell body, automatic contraction elevating system sets up in unmanned aerial vehicle's bottom, and automatic contraction elevating system sets up the side at the shell body, automatic rotation driving mechanism sets up the one end in the shell body, automatic inflation separating mechanism includes the round sleeve, inflation motor and two separation motors, the round sleeve level rotatable setting is in the inside of shell body, inflation motor and two separation motors all set up directly over the round sleeve, the output shaft of inflation motor is connected with the round sleeve transmission, two separation motors are respectively symmetrical setting at the both ends of shell body inside, and the output shaft of two separation motors is respectively the horizontal connection threaded rod, the threaded rod is vertically provided with a separation sheet in threaded fit with the threaded rod, the lower end of the separation sheet is provided with detachable inflation heads, the inside of the round sleeve is symmetrically provided with two rotatable micro gas cylinders, one-way ventilation mechanisms are arranged in the cylinder mouths of the micro gas cylinders, one ends of the two inflation heads are in threaded fit with the cylinder mouths of the two micro gas cylinders respectively, the other ends of the two inflation heads are provided with air bags respectively, and the two air bags are arranged on two sides of the outer shell.

As an optimal selection scheme of the triphibian air vehicle, the one-way ventilation mechanism comprises a spring, an airtight cap, a touch ring and a supporting seat, a fixing clamp of the touch ring is arranged at the mouth end of the miniature air cylinder, the airtight cap is of a cylindrical structure with an open lower end, the airtight cap is sleeved outside the spring, the top of the airtight cap is in touch with the top of the spring, the edge of the top of the airtight cap is in touch with the bottom of the touch ring, the bottom of the spring is sleeved on the supporting seat and in touch with the supporting seat, the supporting seat is communicated with the inner cavity of the miniature air cylinder, the inflation head is of a cylindrical structure with an open end, and the non-open end of the inflation head is connected with an air needle for communicating the air.

As an optimal selection scheme of land, water and air triphibian carrier aircraft, the outside cover of miniature gas cylinder is equipped with the bottle cover, the symmetry is provided with two draw runners on the outer wall of bottle cover, the length direction of draw runner is on a parallel with the axial of bottle cover, be provided with two spouts that are used for holding the draw runner on the telescopic inner wall of circle, the fixed cover in middle part of the telescopic outer wall of circle is equipped with a first follow driving wheel, fixedly connected with a first action wheel on the output shaft of inflation motor, first action wheel and first follow driving wheel are connected through first synchronous belt.

As an optimal selection scheme of a amphibious carrier aircraft, automatic rotation actuating mechanism includes the interior casing, first servo motor, second servo motor and screw propeller blade, first servo motor passes through the fixed inside that sets up at the outer casing of T word board, the rotatable lower extreme that sets up at the T word board of interior casing, the second servo motor is fixed to be set up on the inner casing, and the inside of interior casing is worn into to the output shaft end fixing of second servo motor, the fixed first bevel gear that is provided with of output shaft end of second servo motor, screw propeller blade's middle part fixedly connected with first transmission shaft, it is used for with the driven second bevel gear of first bevel gear to keep away from one of screw propeller blade to serve the fixed second bevel gear that is provided with of first transmission shaft, the interior casing is worn into perpendicularly to the axis of first transmission shaft and second servo motor output shaft sets up perpendicularly.

As an optimal scheme of a triphibian carrier aircraft of land, water and air, the symmetry is fixed on an end face of T word board and is provided with two first pin joints, the symmetry is fixed on an end face of interior casing neighbour second servo motor and is provided with two and be used for with two first pin joint articulated second pin joints, two first pin joints and two second pin joints pass through the second transmission shaft and rotate the connection, the fixed third bevel gear that is provided with on the second transmission shaft, T word board is passed through to first servo motor's output shaft to the fixed fourth bevel gear that is used for with third bevel gear transmission that is provided with of output shaft end of first servo motor.

As an optimal selection scheme of a land, water and air triphibian carrier aircraft, automatic shrink elevating system includes drive assembly and four automatic shrink elevating system of group, automatic shrink elevating system includes electric putter, pneumatic cylinder and rotor plate, electric putter's one end is rotated and is set up in unmanned aerial vehicle's bottom, the preceding tip and the pneumatic cylinder of electric putter's output shaft rotate to be connected, the pneumatic cylinder rotates to be set up on the shell body, the middle part of rotor plate is connected with the preceding tip rotation of the output shaft of pneumatic cylinder, the one end of rotor plate is passed through the connecting rod and is connected with the pneumatic cylinder rotation, drive assembly installs on two sets of automatic shrink elevating system.

As an optimal selection scheme of land, water and air triphibian carrier aircraft, the unmanned aerial vehicle bottom is provided with a plurality of riser, electric putter's the fixed first fulcrum that is provided with of tail end symmetry, two first fulcrums rotate to set up between two risers, one of pneumatic cylinder is served and is provided with the fixed plate, connecting portion and second fulcrum, be provided with on the shell body be used for with fixed plate normal running fit's third fulcrum, connecting portion are connected with the preceding tip rotation of electric putter's output shaft, the one end and the second fulcrum fixed connection of connecting rod, the preceding tip of the output shaft of pneumatic cylinder is connected through the middle part rotation of fourth fulcrum and rotor plate.

As an optimal selection scheme of a amphibious carrier aircraft, transmission assembly includes third servo motor and third transmission shaft, the fixed inside that sets up at the shell body of third servo motor, the both ends of third transmission shaft are rotated respectively and are set up one of two rotor plates and serve, and on the both ends of third transmission shaft respectively fixedly connected with a drive wheel, it is provided with a drive wheel to rotate respectively on one of two rotor plates of keeping away from the third transmission shaft on the rotor plate, the fixed cover in middle part of third transmission shaft is equipped with a second from the driving wheel, a second action wheel of fixedly connected with on the output shaft of third servo motor, second action wheel and second are followed the driving wheel and are connected through the second hold-in range.

As a preferable scheme of the water, land and air triphibian carrier vehicle, two arc-shaped openings for storing the third transmission shaft are symmetrically arranged at one end of the inner shell, which is close to the third transmission shaft.

Compared with the prior art, the invention has the beneficial effects that: the triphibian air vehicle for carrying water, land and air disclosed by the invention is skillfully designed, so that the air vehicle realizes the function of triphibian operation on water, land and air, integrates the multifunctional operation capabilities of carrying, search and rescue and the like, abandons the defect that the traditional unmanned aerial vehicle has single function, and meets the market requirement.

Drawings

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

FIG. 2 is a schematic perspective view of the present invention;

fig. 3 is a schematic perspective view of the drone of the present invention;

FIG. 4 is a schematic perspective view of the automatic inflation separation mechanism of the present invention;

FIG. 5 is an exploded perspective view of the automatic inflation release mechanism of the present invention;

FIG. 6 is a schematic view, partially in section, of the automatic pneumatic detachment mechanism of the present invention;

FIG. 7 is an enlarged view of a portion of FIG. 6 at A;

FIG. 8 is an exploded perspective view of the unidirectional venting mechanism of the present invention;

FIG. 9 is a schematic perspective view of the automatic rotary drive mechanism of the present invention;

FIG. 10 is an exploded perspective view of the automatic rotary drive mechanism of the present invention;

FIG. 11 is a schematic perspective view of the automatic retracting and raising mechanism of the present invention;

FIG. 12 is a schematic perspective view of the self-retracting lifting assembly of the present invention;

FIG. 13 is an exploded perspective view of the auto-retracting lift assembly of the present invention;

fig. 14 is a perspective view of the transmission assembly of the present invention.

The reference numbers in the figures are: an unmanned aerial vehicle 1; an outer shell 2; a circular sleeve 3; an air-charging motor 4; a separation motor 5; a threaded rod 6; a separator sheet 7; an inflation head 8; a miniature gas cylinder 9; an air bag 10; a spring 11; a closing cap 12; a contact ring 13; a support base 14; an air needle 15; a vial cover 16; a slide bar 17; a chute 18; a first driven pulley 19; a first capstan 20; a first timing belt 21; an inner housing 22; a first servo motor 23; a second servo motor 24; the propeller blades 25; a T-shaped plate 26; a first bevel gear 27; a first drive shaft 28; a second bevel gear 29; a first hinge point 30; a second hinge point 31; a second transmission shaft 32; a third bevel gear 33; a fourth bevel gear 34; an electric push rod 35; a hydraulic cylinder 36; a rotating plate 37; a connecting rod 38; a riser 39; a first fulcrum 40; a fixed plate 41; a connecting portion 42; a second fulcrum 43; a fourth fulcrum 45; a third servo motor 46; a third transmission shaft 47; a drive wheel 48; a second driven pulley 49; a second drive pulley 50; a second timing belt 51; an arcuate opening 52; an automatic inflation separating mechanism 53; the automatic retraction lifting assembly 54; the driving mechanism 55 is automatically rotated.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "front", "rear", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

Referring to fig. 1 to 14, a triphibian air vehicle for water, land and air comprises an unmanned aerial vehicle 1, an outer shell 2, an automatic inflation separating mechanism 53, an automatic retraction lifting mechanism 54 and an automatic rotation driving mechanism 55, wherein the outer shell 2 is fixedly arranged at the bottom end of the unmanned aerial vehicle 1, the automatic inflation separating mechanism 53 is horizontally arranged inside the outer shell 2, the automatic retraction lifting mechanism 54 is arranged at the bottom end of the unmanned aerial vehicle 1, the automatic retraction lifting mechanism 54 is arranged at the side of the outer shell 2, the automatic rotation driving mechanism 55 is arranged at one end inside the outer shell 2, the automatic inflation separating mechanism 53 comprises a round sleeve 3, an inflation motor 4 and two separation motors 5, the round sleeve 3 is horizontally and rotatably arranged inside the outer shell 2, the inflation motor 4 and the two separation motors 5 are both arranged right above the round sleeve 3, and an output shaft of the inflation motor 4 is in transmission connection with the round sleeve 3, two separation motors 5 symmetry respectively set up the both ends in outer casing 2 inside, and the output shaft of two separation motors 5 horizontally connect respectively has threaded rod 6, equal vertical separation piece 7 with it screw-thread fit that is provided with on threaded rod 6, the lower extreme of separation piece 7 all is provided with detachable inflation head 8, the inside symmetry of round sleeve 3 is provided with two rotatable miniature gas cylinders 9, be provided with one-way air-breather in the bottle neck of miniature gas cylinder 9, the one end of two inflation heads 8 respectively with the bottle neck screw-thread fit of two miniature gas cylinders 9, the other end of two inflation heads 8 is provided with gasbag 10 respectively, two gasbags 10 set up the both sides at outer casing 2. The inflating motor 4 and the separating motor 5 are controlled by a control system of the unmanned aerial vehicle 1, when the aircraft flies in the air, the automatic inflating separating mechanism 53, the automatic retracting lifting mechanism 54 and the automatic rotating driving mechanism 55 do not work, only the unmanned aerial vehicle 1 works in the air, when the aircraft runs on land, the unmanned aerial vehicle 1, the automatic inflating separating mechanism 53 and the automatic rotating driving mechanism 55 do not work, only the automatic retracting lifting mechanism 54 works, so that the aircraft runs on land, when the aircraft runs on water, the unmanned aerial vehicle 1 and the automatic retracting lifting mechanism 54 do not work, the automatic inflating separating mechanism 53 and the automatic rotating driving mechanism 55 work, firstly, the inflating motor 4 runs to drive the circular sleeve 3 to rotate, the circular sleeve 3 drives the micro gas cylinder 9 to rotate, the bottle nozzle of the micro gas cylinder 9 slowly rotates into the inflating head 8, then, one-way ventilation mechanism is opened passively, make the compressed air source of miniature gas cylinder 9 rush into in the gasbag 10, make gasbag 10 aerify and become the air cushion, thereby make this aircraft float on the surface of water, gasbag 10 is disposable, need change after the use, at this moment, separation motor 5 starts, drives threaded rod 6 and rotates, and threaded rod 6 drives release sheet 7 and rotates, and release sheet 7 pushes away the air cushion from inflation head 8 afterwards, and finally, operating personnel alright go with installing new gasbag 10.

One-way ventilation mechanism includes spring 11, airtight cap 12, conflict ring 13 and supporting seat 14, conflict ring 13 fixing clip establishes at the bottle mouth port department of miniature gas cylinder, airtight cap 12 is lower extreme open-ended cylinder type structure, airtight cap 12 cover is established outside spring 11 and the inboard top of airtight cap 12 is contradicted with spring 11's top, the top edge of airtight cap 12 is contradicted with conflict ring 13's bottom, spring 11's bottom cover is established on supporting seat 14 and is contradicted with supporting seat 14, supporting seat 14 communicates with miniature gas cylinder's inner chamber, the inflation head is one end open-ended cylinder type structure, the non-open end of inflation head is connected with a gas needle 15 that is used for communicating gasbag and miniature gas cylinder. Firstly, spring 11, airtight cap 12, conflict ring 13 and supporting seat 14's cooperation setting for one-way ventilation mechanism becomes more sensitive, when miniature gas cylinder 9 need inflate gasbag 10, just can be fast, reliable aerify, and the setting of gas needle 15 is favorable to inflating head 8 with the effectual intercommunication of miniature gas cylinder 9 and gasbag 10.

The outside cover of miniature gas cylinder 9 is equipped with bottle cover 16, the symmetry is provided with two draw runners 17 on the outer wall of bottle cover 16, the length direction of draw runner 17 is on a parallel with the axial of bottle cover 16, be provided with two spout 18 that are used for holding draw runner 17 on the inner wall of circle sleeve 3, the fixed cover in middle part of the outer wall of circle sleeve 3 is equipped with one and is first from driving wheel 19, aerify first action wheel 20 of fixedly connected with on the output shaft of motor 4, first action wheel 20 and first from driving wheel 19 and connect through first hold-in range 21. Firstly, when the inflation motor 4 operates, the first driving wheel 20 is driven to rotate, the first driving wheel 20 drives the first driven wheel 19 to rotate through the first synchronous belt 21, the first driven wheel 19 drives the bottle sleeve 16 and the micro gas bottle 9 to rotate, and the arrangement of the sliding strip 17 and the sliding groove 18 is beneficial to the bottle sleeve 16 to slide in the circular sleeve 3.

The automatic rotation driving mechanism 55 comprises an inner shell 22, a first servo motor 23, a second servo motor 24 and a screw blade 25, the first servo motor 23 is fixedly arranged inside the outer shell 2 through a T-shaped plate 26, the inner shell 22 is rotatably arranged at the lower end of the T-shaped plate 26, the second servo motor 24 is fixedly arranged on the inner shell 22, an output shaft of the second servo motor 24 penetrates into the inner shell 22, a first bevel gear 27 is fixedly arranged at the end part of the output shaft of the second servo motor 24, a first transmission shaft 28 is fixedly connected to the middle part of the screw blade 25, one end, far away from the screw blade 25, of the first transmission shaft 28 is fixedly provided with a second bevel gear 29 which is used for transmitting with the first bevel gear 27, the first transmission shaft 28 penetrates into the inner shell 22 vertically, and the first transmission shaft 28 is arranged vertically to the axis of the output shaft of the second servo motor. The first servo motor 23 and the second servo motor 24 are controlled by the control system of the unmanned aerial vehicle 1, firstly, when the unmanned aerial vehicle runs on water, the airbag 10 is opened, at this time, the first servo motor 23 drives the inner shell 22 to rotate, the inner shell 22 is rotated to the water, then, the second servo motor 24 operates, the first bevel gear 27 is driven to operate, the first bevel gear 27 drives the second bevel gear 29 to rotate, the second bevel gear 29 drives the first transmission shaft 28 and the propeller blades 25 to rotate, and the propeller blades 25 operate under the water to provide power.

Two first hinge points 30 are symmetrically and fixedly arranged on one end face of the T-shaped plate 26, two second hinge points 31 which are used for being hinged with the two first hinge points 30 are symmetrically and fixedly arranged on one end face of the inner shell 22 close to the second servo motor 24, the two first hinge points 30 and the two second hinge points 31 are rotatably connected through a second transmission shaft 32, a third bevel gear 33 is fixedly arranged on the second transmission shaft 32, an output shaft of the first servo motor 23 penetrates through the T-shaped plate 26, and a fourth bevel gear 34 which is used for being driven by the third bevel gear 33 is fixedly arranged at the end part of the output shaft of the first servo motor 23. First, first servo motor 23 starts, drives fourth bevel gear 34 and rotates, and fourth bevel gear 34 drives third bevel gear 33 and rotates, and third bevel gear 33 drives second transmission shaft 32 and rotates, and first transmission shaft 28 drives interior casing 22 and rotates, and the setting of first pin joint 30 and second pin joint 31 is favorable to interior casing 22 and T board 26 better rotation to be connected.

Automatic shrink elevating system 54 includes drive assembly and four automatic shrink elevating assembly of group, automatic shrink elevating assembly includes electric putter 35, pneumatic cylinder 36 and rotor plate 37, electric putter 35's one end is rotated and is set up the bottom at unmanned aerial vehicle 1, the preceding tip and the pneumatic cylinder 36 of electric putter 35's output shaft rotate and be connected, pneumatic cylinder 36 rotates and sets up on outer casing 2, the middle part of rotor plate 37 rotates with the preceding tip of the output shaft of pneumatic cylinder 36 to be connected, connecting rod 38 is passed through to the one end of rotor plate 37 and pneumatic cylinder 36 rotates to be connected, drive assembly installs on two sets of automatic shrink elevating assembly. The electric push rod 35 and the hydraulic cylinder 36 are controlled by a control system of the unmanned aerial vehicle 1, firstly, when the aircraft runs on land, the electric push rod 35 is started to drive the hydraulic cylinder 36 to rotate, meanwhile, the hydraulic cylinder 36 is started to drive the transmission assembly and the rotating plate 37 to rotate, the rotating plate 37 and the transmission assembly are unfolded and put down, and when the aircraft flies, the aircraft can be retracted in the same steps as the steps.

The bottom of unmanned aerial vehicle 1 is provided with a plurality of riser 39, the fixed first fulcrum 40 that is provided with of tail end symmetry of electric putter 35, two first fulcrums 40 rotate and set up between two risers 39, one of pneumatic cylinder 36 is served and is provided with fixed plate 41, connecting portion 42 and second fulcrum 43, be provided with on the shell body 2 and be used for with the third fulcrum of fixed plate 41 normal running fit, connecting portion 42 rotates with the preceding tip of the output shaft of electric putter 35 and is connected, the one end and the second fulcrum 43 fixed connection of connecting rod 38, the preceding tip of the output shaft of pneumatic cylinder 36 rotates through the middle part of fourth fulcrum 45 and rotor plate 37 and is connected. The vertical plate 39, the first fulcrum 40, the fixing plate 41, the connecting part 42, the second fulcrum 43, the third fulcrum and the fourth fulcrum 45 are arranged to enable the automatic retraction lifting mechanism 54 to operate normally and stably, so that the aircraft can operate stably on the land.

The transmission assembly comprises a third servo motor 46 and a third transmission shaft 47, the third servo motor 46 is fixedly arranged inside the outer shell 2, two ends of the third transmission shaft 47 are respectively rotatably arranged at one end of the two rotating plates 37, the two ends of the third transmission shaft 47 are respectively fixedly connected with a driving wheel 48, one end of each rotating plate 37 far away from the third transmission shaft 47 on each rotating plate 37 is respectively rotatably provided with a driving wheel 48, a second driven wheel 49 is fixedly sleeved at the middle part of the third transmission shaft 47, a second driving wheel 50 is fixedly connected onto an output shaft of the third servo motor 46, and the second driving wheel 50 and the second driven wheel 49 are connected through a second synchronous belt 51. The third servo motor 46 is controlled by the control system of the unmanned aerial vehicle 1, first, the third servo motor 46 operates to drive the second driving wheel 50 to operate, the second driving wheel 50 drives the second driven wheel 49 to rotate through the second synchronous belt 51, the second driven wheel 49 drives the third transmission shaft 47 to operate, the third transmission shaft 47 drives the two driving wheels 48 to rotate, and the other two driving wheels 48 rotate along with the rotation.

Two arc-shaped openings 52 for storing the third transmission shaft 47 are symmetrically arranged at one end of the inner housing 22 adjacent to the third transmission shaft 47. The arc-shaped opening 52 is beneficial to retracting the third transmission shaft 47 into the arc-shaped opening 52 after the operation of the automatic retracting and lifting mechanism 54 is finished, so that the automatic retracting and lifting mechanism 54 does not influence the operation of other mechanisms.

The working principle is as follows: when the aircraft flies in the air, the automatic inflation separating mechanism 53, the automatic contraction lifting mechanism 54 and the automatic rotation driving mechanism 55 do not work, the unmanned aerial vehicle 1 works in the air, when the aircraft runs on the land, the unmanned aerial vehicle 1, the automatic inflation separating mechanism 53 and the automatic rotation driving mechanism 55 do not work, the automatic contraction lifting mechanism 54 works, the driving wheel 48 is descended to ensure that the aircraft runs on the land, the driving wheel 48 is retracted after the running is finished, when the aircraft runs on the water, the unmanned aerial vehicle 1 and the automatic contraction lifting mechanism 54 do not work, the automatic inflation separating mechanism 53 and the automatic rotation driving mechanism 55 work, the automatic inflation separating mechanism 53 works, the gas in a micro gas source is flushed into the air bag 10 to become an air cushion, and simultaneously the automatic rotation driving mechanism 55 works to rotate the screw blade 25 to the water surface to provide a power source for the aircraft, the air cushion is pushed away after the operation is finished, so that the air vehicle can finish triphibious carrying operation on water, land and air.

Claims

1. The utility model provides a triphibian carrier vehicle of land, water and air, which is characterized in that, including unmanned aerial vehicle (1), shell body (2), automatic inflation separating mechanism (53), automatic shrink elevating system and automatic rotation actuating mechanism (55), shell body (2) are fixed to be set up in the bottom of unmanned aerial vehicle (1), automatic inflation separating mechanism (53) level sets up the inside at shell body (2), automatic shrink elevating system sets up the bottom at unmanned aerial vehicle (1), and automatic shrink elevating system sets up the side at shell body (2), automatic rotation actuating mechanism (55) set up the one end at shell body (2) inside, automatic inflation separating mechanism (53) include circle sleeve (3), inflation motor (4) and two separation motor (5), the rotatable setting of circle sleeve (3) level is in shell body (2) inside, inflation motor (4) and two separation motor (5) all set up directly over circle sleeve (3), the output shaft of gas motor (4) is connected with circle sleeve (3) transmission, two separation motor (5) symmetry respectively set up the both ends in shell (2) inside, and the output shaft of two separation motor (5) horizontally connect with threaded rod (6) respectively, equal vertical separation piece (7) with its screw-thread fit that is provided with on threaded rod (6), the lower extreme of separation piece (7) all is provided with detachable inflation head (8), the inside symmetry of circle sleeve (3) is provided with two rotatable miniature gas cylinder (9), be provided with one-way air-breather in the bottleneck of miniature gas cylinder (9), the one end of two inflation heads (8) respectively with the bottle mouth screw-thread fit of two miniature gas cylinder (9), the other end of two inflation heads (8) is provided with gasbag (10) respectively, two gasbags (10) set up the both sides of shell (2).

2. The triphibian carrier vehicle according to claim 1, characterized in that the one-way ventilation means comprise a spring (11), a closing cap (12), support ring (13) and supporting seat (14), support ring (13) fixing clip establishes at the bottle neck port department of miniature gas cylinder, airtight cap (12) are lower extreme open-ended cylinder type structure, airtight cap (12) cover is established outside spring (11) and the inboard top of airtight cap (12) is contradicted with the top of spring (11), the top edge of airtight cap (12) is contradicted with the bottom of supporting ring (13), the bottom cover of spring (11) is established on supporting seat (14) and is contradicted with supporting seat (14), supporting seat (14) and the inner chamber intercommunication of miniature gas cylinder, the inflation head is one end open-ended cylinder type structure, the non-open end of inflation head is connected with one and is used for communicating gas needle (15) of gasbag and miniature gas cylinder.

3. The triphibian air vehicle as claimed in claim 1, wherein a bottle sleeve (16) is sleeved outside the miniature air bottle (9), two sliding strips (17) are symmetrically arranged on the outer wall of the bottle sleeve (16), the length direction of each sliding strip (17) is parallel to the axial direction of the bottle sleeve (16), two sliding grooves (18) for accommodating the sliding strips (17) are formed in the inner wall of the circular sleeve (3), a first driven wheel (19) is fixedly sleeved in the middle of the outer wall of the circular sleeve (3), a first driving wheel (20) is fixedly connected to an output shaft of the inflation motor (4), and the first driving wheel (20) and the first driven wheel (19) are connected through a first synchronous belt (21).

4. The amphibious vehicle as claimed in claim 1, wherein the automatic rotation driving mechanism (55) comprises an inner shell (22), a first servo motor (23), a second servo motor (24) and a propeller blade (25), the first servo motor (23) is fixedly arranged inside the outer shell (2) through a T-shaped plate (26), the inner shell (22) is rotatably arranged at the lower end of the T-shaped plate (26), the second servo motor (24) is fixedly arranged on the inner shell (22), an output shaft of the second servo motor (24) penetrates into the inner shell (22), a first bevel gear (27) is fixedly arranged at the end of the output shaft of the second servo motor (24), a first transmission shaft (28) is fixedly connected to the middle part of the propeller blade (25), and a second bevel gear (29) for transmission with the first bevel gear (27) is fixedly arranged at one end of the first transmission shaft (28) far away from the propeller blade (25), a first transmission shaft (28) vertically penetrates the inner shell (22), and the first transmission shaft (28) is vertically arranged with the axis of the output shaft of the second servo motor (24).

5. The triphibian carrier vehicle as claimed in claim 4, wherein two first hinge points (30) are symmetrically and fixedly arranged on one end surface of the T-shaped plate (26), two second hinge points (31) for being hinged to the two first hinge points (30) are symmetrically and fixedly arranged on one end surface of the inner shell (22) close to the second servo motor (24), the two first hinge points (30) and the two second hinge points (31) are rotatably connected through a second transmission shaft (32), a third bevel gear (33) is fixedly arranged on the second transmission shaft (32), the output shaft of the first servo motor (23) penetrates through the T-shaped plate (26), and a fourth bevel gear (34) for being transmitted with the third bevel gear (33) is fixedly arranged at the end part of the output shaft of the first servo motor (23).

6. The triphibian air vehicle according to claim 1, wherein the automatic retraction lifting mechanism comprises a transmission assembly and four groups of automatic retraction lifting assemblies (54), each automatic retraction lifting assembly (54) comprises an electric push rod (35), a hydraulic cylinder (36) and a rotating plate (37), one end of each electric push rod (35) is rotatably arranged at the bottom end of the unmanned aerial vehicle (1), the front end of the output shaft of each electric push rod (35) is rotatably connected with the hydraulic cylinder (36), the hydraulic cylinder (36) is rotatably arranged on the outer shell (2), the middle of each rotating plate (37) is rotatably connected with the front end of the output shaft of the hydraulic cylinder (36), one end of each rotating plate (37) is rotatably connected with the hydraulic cylinder (36) through a connecting rod (38), and the transmission assembly is mounted on the two groups of automatic retraction lifting assemblies (54).

7. The triphibian carrier vehicle as claimed in claim 6, wherein the bottom end of the unmanned aerial vehicle (1) is provided with a plurality of vertical plates (39), the tail end of the electric push rod (35) is symmetrically and fixedly provided with first fulcrums (40), the two first fulcrums (40) are rotatably arranged between the two vertical plates (39), one end of the hydraulic cylinder (36) is provided with a fixed plate (41), a connecting part (42) and a second fulcrum (43), the outer shell (2) is provided with a third fulcrum for being rotatably matched with the fixed plate (41), the connecting part (42) is rotatably connected with the front end of the output shaft of the electric push rod (35), one end of the connecting rod (38) is fixedly connected with the second fulcrum (43), and the front end of the output shaft of the hydraulic cylinder (36) is rotatably connected with the middle part of the rotating plate (37) through the fourth fulcrum (45).

8. The triphibian carrier vehicle as claimed in claim 6, characterized in that the transmission assembly comprises a third servomotor (46) and a third transmission shaft (47), the third servomotor (46) being fixedly arranged inside the outer hull (2), both ends of the third transmission shaft (47) being rotatably arranged on one end of the two rotating plates (37) respectively, and respectively fixedly connected with a drive wheel (48) on the both ends of third transmission shaft (47), one of two rotating plate (37) of keeping away from third transmission shaft (47) on rotating plate (37) is served and is rotated respectively and be provided with a drive wheel (48), the middle part fixed cover of third transmission shaft (47) is equipped with a second and follows driving wheel (49), fixedly connected with a second action wheel (50) on the output shaft of third servo motor (46), second action wheel (50) and second follow driving wheel (49) are passed through second hold-in range (51) and are connected.

9. The triphibian carrier vehicle as claimed in claim 6, characterized in that two arc-shaped openings (52) for storing the third drive shaft (47) are symmetrically arranged on the inner hull (22) at the end adjacent to the third drive shaft (47).