CN114030593B - Vertical take-off and landing unmanned aerial vehicle - Google Patents
Vertical take-off and landing unmanned aerial vehicle Download PDFInfo
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- CN114030593B CN114030593B CN202111293957.6A CN202111293957A CN114030593B CN 114030593 B CN114030593 B CN 114030593B CN 202111293957 A CN202111293957 A CN 202111293957A CN 114030593 B CN114030593 B CN 114030593B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
- B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/10—Technologies relating to charging of electric vehicles
- Y02T90/14—Plug-in electric vehicles
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- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Forklifts And Lifting Vehicles (AREA)
- Toys (AREA)
Abstract
The invention discloses a vertical take-off and landing unmanned aerial vehicle, which relates to the technical field of unmanned aerial vehicles and comprises a main body, wherein the bottom of the main body is fixedly connected with an underframe, a lifting block is slidably connected at the central position inside the underframe, and the top of the lifting block is fixedly connected with a fixed block. The ejector rods push the fixing blocks to ascend, the ascending fixing blocks drive the four groups of racks to ascend, and meanwhile, the reset springs are compressed, so that the soft landing of the whole aircraft main body is realized, the first gear and the second gear are meshed outside each group of racks in sequence, the third gear drives the turnover shaft and the supporting legs to be opened in the direction away from the bottom frame under the action of the synchronous belt between the second gear and the third gear, the multiple groups of supporting legs are completely opened and are in contact with the ground, the whole landing contact area is increased in the whole landing process of the main body, the landing process of the aircraft main body is more stable, and the damage to the whole main body caused by hard landing is effectively avoided.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a vertical take-off and landing unmanned aerial vehicle.
Background
An unmanned aerial vehicle is an unmanned aircraft that is operated using a radio remote control device and self-contained program control means, or is operated autonomously, either completely or intermittently, by an on-board computer.
The unmanned aerial vehicle also belongs to one of the unmanned aerial vehicles, wherein the unmanned aerial vehicle often adopts a vertical take-off and landing technology, wherein the vertical take-off and landing technology reduces or basically gets rid of the dependence on a runway, and can be pulled up and landed vertically only by a small flat land.
Unmanned vehicles takes photo by plane among the prior art is when descending, often the undercarriage all is direct and ground rigid contact, wherein the hard landing of undercarriage can produce certain vibrations to the unmanned vehicles body that takes photo by plane, can make the aircraft take place certain damage when serious, and when the aircraft takes off, the undercarriage need initiatively contract it through the remote controller and fold to it, thereby lead to needing extra controlgear to control the undercarriage, the holistic gravity of aircraft body has not only been increased, and can consume the electric energy of certain degree.
Disclosure of Invention
Based on the above, the invention aims to provide a vertical take-off and landing unmanned aerial vehicle, so as to solve the technical problems that in the prior art, the hard landing of the undercarriage can generate certain vibration on the body of the aerial unmanned aerial vehicle, and the undercarriage needs to be actively contracted and folded through a remote controller, so that extra control equipment is needed to control the undercarriage.
In order to achieve the purpose, the invention provides the following technical scheme: a vertical take-off and landing unmanned aerial vehicle comprises a main body, wherein the bottom of the main body is fixedly connected with an underframe, a lifting block is slidably connected at the center position inside the underframe, and a fixed block is fixedly connected at the top of the lifting block;
the four corners of the outer wall of the underframe are rotatably connected with supporting legs, four groups of supporting legs and the underframe are rotatably connected through turnover shafts, third gears are fixed on the outer sides of the turnover shafts, racks are fixed on the four corners of the outer side of the fixing block, supporting frames are fixed on the four corners of the inner part of the underframe, one side of the inner part of each group of supporting frames is rotatably connected with a first gear meshed with the racks, the other side of the inner part of each group of supporting frames is rotatably connected with a second gear meshed with the first gear, and the second gears and the third gears are connected through synchronous belts;
the lifting device is characterized in that a cavity matched with the lifting block, the fixing block and four groups of racks is formed in the center of the inner portion of the bottom frame, a reset spring is fixed between the top of the fixing block and the bottom frame, a top rod penetrates through the bottom frame and is arranged at the bottom of the lifting block, and a top plate is fixed at the bottom of the top rod.
By adopting the technical scheme, in the whole flight process, four groups of supporting legs are tightly attached to the outer wall of the bottom frame and are in a contraction state, when the aircraft main body descends, the top plate firstly contacts the ground, under the action of the gravity of the whole aircraft main body, the top plate and the ejector rods move towards the inside of the bottom frame under the action of the gravity, the ejector rods push the fixing blocks to ascend, the ascending fixing blocks drive the four groups of racks to ascend, and simultaneously compress the return springs, soft landing of the whole aircraft main body is realized under the action of the return springs, and because the outer sides of each group of racks are sequentially engaged with the first gear and the second gear, and further under the action of the synchronous belt between the second gear and the third gear, the third gear drives the turnover shaft and the supporting legs to open towards the direction far away from the bottom frame, when the top plate completely contracts, the groups of supporting legs are completely opened and are in contact with the ground, and then increase holistic landing area of contact to the whole landing in-process of main part, make aircraft main part landing process more stable, the effectual damage that causes the main part is whole to hard landing has been avoided.
The invention is further arranged in such a way that a connecting rod which penetrates through the underframe and extends into the main body is arranged at the top of the fixing block in the reset spring, a sliding rod is fixed at the top of the connecting rod, and protection cylinders positioned on the outer side of the main body are fixed at two sides of the sliding rod.
Through adopting above-mentioned technical scheme, through there being a protection section of thick bamboo at main part outside sliding connection, when the roof under the effect of gravity and ground contact, the roof promotes the connecting rod through ejector pin and fixed block and rises, and then the connecting rod rises through slide bar and protection section of thick bamboo, and then a protection section of thick bamboo breaks away from the restriction to the multiunit supporting leg, and when the aircraft takes off, because the holistic gravity of main part is offset by the rotatory lift that produces of helical blade, and then reset spring resets, not only make four groups of supporting legs shrink, and make a protection section of thick bamboo descend to the outside of four groups of supporting legs and protect it, avoid flying in-process external object to its influence and destruction.
The invention is further arranged in such a way that a sliding groove matched with the sliding rod is arranged in the middle position of the bottom end in the main body, and a matching groove matched with the protection cylinder is arranged on the outer wall of the main body.
Through adopting above-mentioned technical scheme, the spout plays the limiting displacement to the slide bar, and is convenient for the slide bar to slide inside the spout.
The invention is further provided that four corners of the top of the outer side of the main body are rotatably connected with supporting arms, mounting cylinders are fixed at the tops of the tail ends of the four groups of supporting arms, motors with upward output ends are mounted in the mounting cylinders, and helical blades are arranged at the output ends of the motors.
By adopting the technical scheme, the supporting arms can be folded and unfolded, and the whole aircraft can take off by generating the lifting force through the rotation of the helical blades.
The invention is further provided that four corners of the top of the outer side of the main body are all fixed with connectors, and one ends of the four groups of support arms far away from the motor are all provided with rotating shafts matched with the connectors.
Through adopting above-mentioned technical scheme, under the effect of connector and axis of rotation, be convenient for rotate between support arm and the main part, the convenience is folded the expansion to the support arm.
The invention is further provided that a fixing ring is fixed inside the underframe and above the fixing block, and limiting holes matched with the fixing block and the four groups of racks are formed inside the fixing ring.
Through adopting above-mentioned technical scheme, the inside spacing hole of solid fixed ring plays the spacing effect of slip to fixed block and multiunit rack, and fixed block and multiunit rack are convenient for carry out spacing slip in spacing downthehole portion.
The invention is further provided that the four corners inside the main body are all provided with first vent holes, and the four corners inside the underframe are all provided with second vent holes communicated with the first vent holes.
By adopting the technical scheme, the arrangement of the first vent hole and the second vent hole not only reduces the flight load of the whole body of the main body and the underframe, but also effectively reduces the resistance influence on the air flow above the first vent hole and the second vent hole in the vertical takeoff process, so that the whole body of the vertical takeoff aircraft is stable in the vertical takeoff process and has higher vertical takeoff speed.
The invention is further provided that a central control module is arranged in the middle position in the main body, and a mounting groove matched with the central control module is formed in the main body.
Through adopting above-mentioned technical scheme, well accuse module plays the holistic flight control effect of main part, is convenient for carry out remote control with the handheld remote controller of staff.
The invention is further provided that four corners of the outer side of the main body are fixedly connected with clamping frames, and clamping grooves matched with the supporting arms are formed in the four groups of clamping frames.
Through adopting above-mentioned technical scheme, the block frame can play the block fixed action after folding the support arm, makes multiunit support arm folding back more stable, can not take place not hard up phenomenon.
In summary, the invention mainly has the following beneficial effects:
1. in the whole flying process of the invention, four groups of supporting legs cling to the outer wall of the underframe and are in a contraction state, when the main body of the aircraft descends, the top plate firstly contacts the ground, under the action of the gravity of the whole main body of the aircraft, the top plate and the ejector rods move towards the inside of the underframe under the action of the gravity, the ejector rods push the fixing blocks to ascend, the ascending fixing blocks drive the four groups of racks to ascend and simultaneously compress the return springs, under the action of the return springs, the whole soft landing of the main body of the aircraft is realized, and because the outer side of each group of racks is sequentially meshed with the first gear and the second gear, and further under the action of the synchronous belt between the second gear and the third gear, the third gear drives the turnover shaft and the supporting legs to open towards the direction far away from the underframe, when the top plate completely contracts, the groups of supporting legs are completely opened and contact with the ground, so as to increase the whole landing contact area of the whole main body in the whole landing process, the landing process of the aircraft main body is more stable, and the damage to the whole main body caused by hard landing is effectively avoided;
2. according to the invention, the protection barrel is connected to the outer side of the main body in a sliding manner, when the top plate is in contact with the ground under the action of gravity, the top plate pushes the connecting rod to ascend through the ejector rod and the fixing block, then the connecting rod ascends through the sliding rod and the protection barrel, further the protection barrel is separated from the limiting effect on the multiple groups of supporting legs, and when the aircraft takes off, the gravity of the whole main body is offset by the lifting force generated by the rotation of the helical blades, and then the reset spring resets, so that not only are the four groups of supporting legs contracted, but also the protection barrel descends to the outer sides of the four groups of supporting legs to protect the supporting legs, and the influence and damage of external objects on the supporting legs in the flight process are avoided.
Drawings
FIG. 1 is an exploded view of the present invention;
FIG. 2 is an enlarged view taken at A of FIG. 1 according to the present invention;
FIG. 3 is a cross-sectional view of the present invention;
FIG. 4 is an enlarged view of FIG. 3 at B according to the present invention;
FIG. 5 is a schematic view of a partially enlarged structure of the present invention;
FIG. 6 is an enlarged, partially exploded view of the present invention;
FIG. 7 is a schematic diagram of a first perspective structure according to the present invention;
FIG. 8 is a schematic diagram of a second perspective of the present invention.
In the figure: 1. a main body; 2. a chassis; 3. a lifting block; 4. a fixed block; 5. a rack; 6. a support frame; 7. a first gear; 8. a second gear; 9. a synchronous belt; 10. a turning shaft; 11. a third gear; 12. Supporting legs; 13. a top rod; 14. a top plate; 15. a fixing ring; 16. a protective barrel; 17. a connecting rod; 18. A slide bar; 19. a chute; 20. a return spring; 21. a support arm; 22. mounting the cylinder; 23. a motor; 24. a helical blade; 25. a connector; 26. a rotating shaft; 27. a first vent hole; 28. a second vent hole; 29. a clamping frame; 30. a central control module; 31. a cavity.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention.
The following describes an embodiment of the present invention based on its overall structure.
A vertical take-off and landing unmanned aerial vehicle comprises a main body 1, wherein the bottom of the main body 1 is fixedly connected with an underframe 2, a lifting block 3 is slidably connected at the center position inside the underframe 2, and a fixed block 4 is fixedly connected at the top of the lifting block 3;
four corners of the outer wall of the chassis 2 are rotatably connected with supporting legs 12, four groups of supporting legs 12 are rotatably connected with the chassis 2 through turnover shafts 10, third gears 11 are fixed on the outer sides of the turnover shafts 10, racks 5 are fixed on the four corners of the outer side of the fixing block 4, supporting frames 6 are fixed on the four corners of the inner part of the chassis 2, one side of the inner part of each group of supporting frames 6 is rotatably connected with a first gear 7 meshed with the racks 5, the other side of the inner part of each group of supporting frames 6 is rotatably connected with a second gear 8 meshed with the first gear 7, and the second gear 8 and the third gears 11 are connected through synchronous belts 9;
a cavity 31 matched with the lifting block 3, the fixed block 4 and the four groups of racks 5 is arranged at the central position in the chassis 2, a return spring 20 is fixed between the top of the fixed block 4 and the chassis 2, an ejector rod 13 is arranged at the bottom of the lifting block 3 and penetrates through the chassis 2, a top plate 14 is fixed at the bottom of the ejector rod 13, when the main body 1 flies integrally, the four groups of supporting legs 12 cling to the outer wall of the chassis 2 and are in a contraction state, when the main body 1 of the aircraft descends, the top plate 14 firstly contacts the ground, under the action of the integral weight of the main body 1 of the aircraft, the top plate 14 and the ejector rod 13 move towards the inside of the chassis 2 under the action of gravity, further, the ejector rod 13 pushes the fixed block 4 to ascend, the four groups of racks 5 are driven by the ascending fixed block 4 to ascend, and simultaneously the return spring 20 is compressed, and in the compression process of the return spring 20, the buffer effect on the main body 1 is achieved, and further, the integral soft landing of the main body 1 of the aircraft is realized, the fixed block 4 top is located reset spring 20 inside and is provided with the connecting rod 17 that runs through chassis 2 and extend to 1 inside of main part, connecting rod 17 top is fixed with slide bar 18, slide bar 18 both sides are fixed with the protection section of thick bamboo 16 that is located the 1 outside of main part, when four group's supporting legs 12 shrink, make the protection section of thick bamboo 16 descend to the outside of four group's supporting legs 12 and protect it, avoid flying in-process external object to its influence and destruction, the intermediate position department of 1 inside bottom of main part has seted up with slide bar 18 matched with spout 19, and the outer wall of main part 1 has seted up with protection section of thick bamboo 16 matched with groove.
Referring to fig. 1, 3, 7 and 8, the four corners of the top of the outer side of the main body 1 are rotatably connected with the supporting arms 21, the supporting arms 21 can be folded and unfolded, the tops of the tail ends of the four groups of supporting arms 21 are all fixed with the mounting cylinder 22, the motor 23 with the upward output end is mounted in the mounting cylinder 22, the output end of the motor 23 is provided with the helical blade 24, the four corners of the top of the outer side of the main body 1 are all fixed with the connectors 25, and one ends of the four groups of supporting arms 21 far away from the motor 23 are all provided with the rotating shafts 26 matched with the connectors 25.
Referring to fig. 3 and 4, a fixing ring 15 is fixed inside the chassis 2 and above the fixing block 4, a limiting hole inside the fixing ring 15 plays a role in limiting the sliding of the fixing block 4 and the plurality of sets of racks 5, and a limiting hole matched with the fixing block 4 and the four sets of racks 5 is formed inside the fixing ring 15.
Referring to fig. 1, the four corners inside the main body 1 are all provided with first vent holes 27, the four corners inside the bottom frame 2 are all provided with second vent holes 28 communicated with the first vent holes 27, and when the main body 1 takes off vertically, the air flow above the main body 1 sequentially passes through the first vent holes 27 and the second vent holes 28.
Referring to fig. 1, 3, 7 and 8, a central control module 30 is disposed at a middle position inside the main body 1, a mounting groove matched with the central control module 30 is formed inside the main body 1, four corners of the outer side of the main body 1 are fixedly connected with clamping frames 29, and clamping grooves matched with the support arms 21 are formed inside the four clamping frames 29.
The working principle of the invention is as follows: when the flying vehicle is used, firstly, under the action of the connector 25 and the rotating shaft 26, the supporting arm 21 is turned to a position vertical to the main body 1, so that the supporting arm 21 drives the motor 23 and the helical blade 24 to reach a horizontal position, and the helical blade 24 is manually unfolded to a relative position, and then a power supply is started, so that the main body 1 flies integrally;
when the main body 1 flies integrally, the four groups of supporting legs 12 cling to the outer wall of the bottom frame 2 and are in a contraction state, when the main body 1 of the aircraft descends, the top plate 14 firstly contacts the ground, under the action of the integral weight of the main body 1 of the aircraft, the top plate 14 and the ejector rods 13 move towards the inside of the bottom frame 2 under the action of gravity, the ejector rods 13 push the fixing blocks 4 to ascend, the ascending fixing blocks 4 drive the four groups of racks 5 to ascend, and meanwhile, the return springs 20 are compressed, and in the compression process of the return springs 20, the buffer effect on the main body 1 is achieved, so that the integral soft landing of the main body 1 of the aircraft is achieved;
the outer side of each group of racks 5 is sequentially meshed with a first gear 7 and a second gear 8, further, one side of each rack 5 is meshed with the first gear 7, one side of each first gear 7 is meshed with the second gear 8, and under the action of a synchronous belt 9, the third gear 11 drives the turnover shaft 10 and the support legs 12 to open towards the direction far away from the underframe 2, when the top plate 14 is completely lifted and contracted, the multiple groups of support legs 12 are completely opened and are in contact with the ground, so that the integral landing contact area is increased in the integral landing process of the main body 1, the landing process of the aircraft main body 1 is more stable, and the damage to the integral main body 1 caused by hard landing is effectively avoided;
secondly, a protection cylinder 16 is connected to the outer side of the main body 1 in a sliding manner, when the top plate 14 is in contact with the ground under the action of gravity, the top plate 14 pushes a connecting rod 17 to ascend through a top rod 13 and a fixing block 4, then the connecting rod 17 ascends through a sliding rod 18 and the protection cylinder 16, and then the protection cylinder 16 is separated from the limiting effect on the multiple groups of supporting legs 12;
when the aircraft main body 1 takes off again, the gravity of the whole main body 1 is offset by the lifting force generated by the rotation of the helical blades 24, and then the return spring 20 is reset, so that the four groups of supporting legs 12 are contracted, the protective barrel 16 is descended to the outer sides of the four groups of supporting legs 12 to protect the supporting legs, and the influence and the damage of an external object on the supporting legs in the flying process are avoided;
furthermore, the four corners inside the main body 1 and the underframe 2 are respectively provided with a first vent hole 27 and a second vent hole 28 which are communicated, and when the main body 1 takes off vertically, the gas flow above the main body 1 sequentially passes through the first vent hole 27 and the second vent hole 28, so that the arrangement of the first vent hole 27 and the second vent hole 28 not only reduces the flight load of the whole main body 1 and the underframe 2, but also effectively reduces the resistance influence on the gas flow above the main body in the vertical take-off process, thereby ensuring that the whole vertical take-off process is not only stable, but also has faster vertical take-off speed;
as can be seen from the above, when the main body 1 vertically descends integrally, the four groups of supporting legs 12 are automatically unfolded under the action of the gravity of the main body 1 through the linkage structure, so that the stability of the main body 1 is well improved when the main body 1 vertically descends, and in the flying process of the main body 1, the multiple groups of supporting legs 12 are automatically contracted under the action of the reset spring 20, an electric control device is not required to be additionally arranged to actively control the main body, the electric energy consumed integrally is reduced to a certain degree, and the cruising ability of the main body 1 is further improved.
Although embodiments of this invention have been shown and described, it is to be understood that such embodiments are merely illustrative of and not restrictive on the broad invention, and that any one or more of the described features, structures, materials, or characteristics may be combined in any suitable manner in any one or more embodiments or examples, and that modifications, substitutions, and variations that do not materially contribute to the novel teachings of this invention may be made by those skilled in the art after reading this disclosure without departing from the principles and spirit of this invention, but within the scope of the appended claims.
Claims (7)
1. A VTOL unmanned aerial vehicle, includes main part (1), its characterized in that: the bottom of the main body (1) is fixedly connected with an underframe (2), a lifting block (3) is connected to the center position in the underframe (2) in a sliding manner, and a fixed block (4) is fixedly connected to the top of the lifting block (3);
the four corners of the outer wall of the chassis (2) are rotatably connected with supporting legs (12), the four groups of supporting legs (12) and the chassis (2) are rotatably connected through turnover shafts (10), third gears (11) are fixedly arranged on the outer sides of the turnover shafts (10), racks (5) are fixedly arranged on the four corners of the outer side of the fixed block (4), supporting frames (6) are fixedly arranged on the four corners of the inner part of the chassis (2), one side of the inner part of each group of supporting frames (6) is rotatably connected with a first gear (7) meshed with the racks (5), the other side of the inner part of each group of supporting frames (6) is rotatably connected with a second gear (8) meshed with the first gear (7), and the second gears (8) and the third gears (11) are connected through synchronous belts (9);
the inner center of the chassis (2) is provided with a cavity (31) matched with a lifting block (3), a fixed block (4) and four groups of racks (5), a reset spring (20) is fixed between the top of the fixed block (4) and the chassis (2), the bottom of the lifting block (3) penetrates through the chassis (2) and is provided with an ejector rod (13), the bottom of the ejector rod (13) is fixed with a top plate (14), the top of the fixed block (4) is positioned inside the reset spring (20) and is provided with a connecting rod (17) penetrating through the chassis (2) and extending to the inside of the main body (1), the top of the connecting rod (17) is fixed with a sliding rod (18), two sides of the sliding rod (18) are fixed with protective cylinders (16) positioned outside the main body (1), the middle position of the inner bottom of the main body (1) is provided with a sliding chute (19) matched with the sliding rod (18), and the outer wall of the main body (1) is provided with a matching groove matched with the protection cylinder (16).
2. The VTOL unmanned aerial vehicle of claim 1, wherein: the main part (1) outside top four corners department all rotates and is connected with support arm (21), four groups the terminal top of support arm (21) all is fixed with installation section of thick bamboo (22), installation section of thick bamboo (22) are inside all to install ascending motor of output (23), motor (23) output is provided with helical blade (24).
3. The VTOL unmanned aerial vehicle of claim 2, wherein: main part (1) outside top four corners department all is fixed with connector (25), four groups motor (23) one end is kept away from in support arm (21) all is provided with axis of rotation (26) with connector (25) matched with.
4. The VTOL unmanned aerial vehicle of claim 1, wherein: a fixing ring (15) is fixed inside the bottom frame (2) and above the fixing block (4), and limiting holes matched with the fixing block (4) and the four groups of racks (5) are formed inside the fixing ring (15).
5. The VTOL unmanned aerial vehicle of claim 1, wherein: first ventilation hole (27) have all been seted up to main part (1) inside four corners department, chassis (2) inside four corners department all sets up second ventilation hole (28) that are linked together with first ventilation hole (27).
6. The VTOL unmanned aerial vehicle of claim 1, wherein: the middle control module (30) is arranged in the middle of the inside of the main body (1), and a mounting groove matched with the middle control module (30) is formed in the main body (1).
7. The VTOL unmanned aerial vehicle of claim 2, wherein: the four corners of the outer side of the main body (1) are fixedly connected with clamping frames (29), and clamping grooves matched with the supporting arms (21) are formed in the four clamping frames (29).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111293957.6A CN114030593B (en) | 2021-11-03 | 2021-11-03 | Vertical take-off and landing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111293957.6A CN114030593B (en) | 2021-11-03 | 2021-11-03 | Vertical take-off and landing unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN114030593A CN114030593A (en) | 2022-02-11 |
| CN114030593B true CN114030593B (en) | 2022-09-13 |
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| CN202111293957.6A Active CN114030593B (en) | 2021-11-03 | 2021-11-03 | Vertical take-off and landing unmanned aerial vehicle |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN206679248U (en) * | 2017-04-27 | 2017-11-28 | 峨眉山市博派乐无人机科技有限公司 | Unmanned plane undercarriage |
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