CN115610643A - Unmanned aerial vehicle undercarriage that takes precautions against earthquakes - Google Patents
Unmanned aerial vehicle undercarriage that takes precautions against earthquakes Download PDFInfo
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- CN115610643A CN115610643A CN202211388776.6A CN202211388776A CN115610643A CN 115610643 A CN115610643 A CN 115610643A CN 202211388776 A CN202211388776 A CN 202211388776A CN 115610643 A CN115610643 A CN 115610643A
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- unmanned aerial
- aerial vehicle
- plate
- connecting plate
- fixedly connected
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
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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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- 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
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Dampers (AREA)
Abstract
The invention discloses an unmanned aerial vehicle shockproof undercarriage, wherein a shock absorption supporting leg is rotatably connected below a fixed frame, a mounting box is fixedly connected in the middle part below the fixed frame, a shockproof mechanism is movably connected in the mounting box, the top of the shockproof mechanism penetrates through the fixed frame and is fixedly connected with a connecting plate, and a mounting plate is elastically connected above the connecting plate; the shockproof mechanism comprises a pressing component and a speed reducing component. When the unmanned aerial vehicle falls, the downward moving speed of the connecting plate can be slowed down, and the push rod can not push the spiral rotating plate to rotate any more due to the reduction of the downward pressure of the unmanned aerial vehicle, so that the unmanned aerial vehicle can land; and during the ejector pin on the spacing rack can stretch into the circular slot this moment, it is spacing to carry out the locking to undercarriage whole, and the cooperation of each structure of undercarriage can realize multistage buffering, stability when improving the descending of unmanned aerial vehicle main part.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle shockproof undercarriage.
Background
The unmanned aerial vehicle is an aircraft which does not require a driver to board the aircraft to carry out any manual driving operation and can automatically complete all flight processes under the monitoring of electronic equipment, and the appearance of the unmanned aerial vehicle enables the research of various countries on the aircraft to enter a brand-new era. The unmanned aerial vehicle has the advantages of strong survival ability, high flexibility, good maneuverability and very convenient use. The micro rotor unmanned aerial vehicle is an integrated product of a micro electro mechanical system, and becomes the key point of many laboratory researches at home and abroad due to the advantages of capability of vertical take-off and landing, free hovering, flexible control, strong capability of adapting to various environments and the like. The system research of the micro rotor unmanned aerial vehicle mainly aims at a ground control system and an airborne measurement and control communication system, wherein the ground control system can monitor and command control the flight attitude of the unmanned aerial vehicle; the airborne measurement and control communication system mainly acquires data of an inertial sensor, an ultrasonic distance meter and the like in the flight state of the unmanned aerial vehicle and transmits the data to the ground control system. Be equipped with the undercarriage on the rotor unmanned aerial vehicle for take-off or descending in-process support rotor unmanned aerial vehicle, rotor unmanned aerial vehicle is at the in-process of descending, can produce great impact force, current rotor unmanned aerial vehicle undercarriage generally adopts spring structure to cushion this impact force, in order to protect rotor unmanned aerial vehicle, however, the mode of spring buffering can make unmanned aerial vehicle rock from top to bottom when descending, bounce the whereabouts after impacting with ground even repeatedly, stability when leading to unmanned aerial vehicle to descend is not high. Therefore, there is a need for a shock resistant landing gear for unmanned aerial vehicles.
Disclosure of Invention
The invention aims to provide an unmanned aerial vehicle shockproof undercarriage, which aims to solve the problems in the prior art.
In order to achieve the purpose, the invention provides the following scheme: the invention provides an unmanned aerial vehicle shockproof undercarriage which comprises a fixed frame, wherein a shock absorption supporting leg is rotatably connected below the fixed frame, a mounting box is fixedly connected in the middle below the fixed frame, a shockproof mechanism is movably connected inside the mounting box, the top of the shockproof mechanism penetrates through the fixed frame and is fixedly connected with a connecting plate, and a mounting plate is elastically connected above the connecting plate; the shockproof mechanism comprises a pressing component and a speed reducing component, the pressing component comprises a pressing rack, the pressing rack is meshed with a gear, the gear is rotatably connected with the mounting box, the gear is meshed with a limiting rack, and the limiting rack is detachably connected with the connecting plate; the speed reduction assembly comprises a spiral rotation plate, the spiral rotation plate is rotatably connected with the inside of the mounting box, a push rod is slidably connected onto the spiral rotation plate, and one end, far away from the spiral rotation plate, of the push rod is fixedly connected with the bottom of the connecting plate.
Preferably, the shock attenuation landing leg is provided with four, every the shock attenuation landing leg includes branch and fixed plate, the one end of branch with the corner of mount is rotated and is connected, the fixed plate rotates and is connected with the telescopic link, the telescopic link is kept away from the one end of fixed plate with the pole body of branch is rotated and is connected.
Preferably, the connecting plate is provided with a plurality of grooves, and springs are fixedly connected inside the grooves; the mounting plate is fixedly provided with a plurality of sliding rods towards the connecting plate, and the plurality of sliding rods and the plurality of grooves are respectively in one-to-one correspondence; the sliding rod is connected with the groove in a sliding mode, a baffle is fixedly arranged on a rod body of the sliding rod, one end of the spring is fixedly connected with the bottom of the groove, and the other end of the spring is fixedly connected with the baffle; one side of the groove is provided with a clamping component, and the clamping component is detachably connected with the baffle.
Preferably, a circular groove is formed in the connecting plate and is close to the groove, a through hole is formed in the side wall between the circular groove and the groove, the clamping assembly is located inside the through hole and comprises a clamping block in sliding connection with the inner wall of the through hole, a tension spring is fixedly connected between the top surface of the clamping block and the inner wall of the through hole, the length of the clamping block is larger than that of the through hole, and the end face, located at one end of the circular groove, of the clamping block is an inclined plane inclined downwards.
Preferably, two opposite side surfaces of the pressing rack are provided with teeth, the middle parts of the other two side surfaces of the pressing rack are fixedly connected with sliding strips, and the two sliding strips are both in sliding connection with the fixing frame; the top of the pressing rack is fixedly connected with the connecting plate.
Preferably, two limiting racks are arranged, the two limiting racks are symmetrically arranged relative to the lower pressing rack, and one side, far away from the lower pressing rack, of each limiting rack is connected with the inner wall of the mounting box in a sliding mode; the top of the limiting rack is fixedly connected with an ejector rod, the ejector rod is in sliding connection with the circular groove, and the ejector rod is detachably connected with the clamping block.
Preferably, the bottom of the fixing frame is fixedly connected with a cross rod, and the cross rod penetrates through two opposite side walls of the mounting box and is fixedly connected with the mounting box; the gear is rotationally connected with the cross rod.
Preferably, two push rods are arranged, each push rod is L-shaped, one end of each push rod, close to the spiral rotating plate, is rotatably connected with a round ball, and the round ball is rotatably connected with the spiral rotating plate; the spiral rotor plate comprises a rotating shaft and a spiral plate, the rotating shaft is vertically arranged inside the mounting box, the rotating shaft is rotatably connected with the inside of the mounting box, and the rotating shaft is fixedly connected with the spiral plate.
Preferably, the bottom of the mounting box is provided with a support leg, and a rubber block is fixedly arranged between the support leg and the mounting box.
Preferably, a plurality of connecting rods are arranged between the connecting plate and the fixing frame, one end of each connecting rod is connected with the connecting plate in a rotating mode, and the other end of each connecting plate is connected with the top face of the fixing frame in a rotating mode.
The invention discloses the following technical effects: according to the invention, the lower pressing assembly and the speed reducing assembly are arranged below the fixing frame, and both the lower pressing assembly and the speed reducing assembly do not adopt an elastic structure, when the unmanned aerial vehicle falls, the connecting plate moves downwards to extrude the lower pressing rack, the lower pressing rack can drive the limiting rack to move upwards, at the moment, the push rod is matched with the spiral rotating plate, the downward movement speed of the connecting plate can be reduced, and the push rod can not push the spiral rotating plate to rotate any more due to the reduction of the downward pressure of the unmanned aerial vehicle, so that the unmanned aerial vehicle can land; and during the ejector pin on the spacing rack can stretch into the circular slot this moment, it is spacing to wholly carry out the locking to the undercarriage, and multistage buffering can be realized in the cooperation of each structure of undercarriage, stability when improving the unmanned aerial vehicle main part and descending.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without inventive exercise.
FIG. 1 is a schematic view of the internal structure of the shock resistant landing gear of the present invention;
FIG. 2 is an enlarged view of a portion of FIG. 1;
FIG. 3 is a side view of the shock resistant landing gear of the present invention;
FIG. 4 is a partial enlarged view of B in FIG. 3;
FIG. 5 is a schematic view of a latch assembly of the present invention.
Wherein: 1. mounting a plate; 2. a connecting plate; 3. a top rod; 4. a clamping block; 5. a telescopic rod; 6. a strut; 7. mounting a box; 8. a support leg; 9. a rubber block; 10. a limit rack; 11. a gear; 12. a slide bar; 13. pressing the rack downwards; 14. a fixing plate; 15. a fixed mount; 16. a cross bar; 17. a circular groove; 18. a connecting rod; 19. a push rod; 20. a spiral plate; 21. a rotating shaft; 22. a ball; 23. a spring; 24. a through hole; 25. a tension spring; 26. a baffle plate; 27. a slide bar; 28. and (4) a groove.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
In order to make the aforementioned objects, features and advantages of the present invention more comprehensible, the present invention is described in detail with reference to the accompanying drawings and the detailed description thereof.
Referring to fig. 1-5, the invention provides an unmanned aerial vehicle shockproof undercarriage, which comprises a fixed frame 15, wherein a shock absorption supporting leg is rotatably connected below the fixed frame 15, a mounting box 7 is fixedly connected in the middle below the fixed frame 15, a shockproof mechanism is movably connected inside the mounting box 7, the top of the shockproof mechanism penetrates through the fixed frame 15 and is fixedly connected with a connecting plate 2, and a mounting plate 1 is elastically connected above the connecting plate 2; the shockproof mechanism comprises a pressing component and a speed reducing component, the pressing component comprises a pressing rack 13, the pressing rack 13 is meshed with a gear 11, the gear 11 is rotatably connected with the mounting box 7, the gear 11 is meshed with a limiting rack 10, and the limiting rack 10 is detachably connected with the connecting plate 2; the speed reduction assembly comprises a spiral rotating plate, the spiral rotating plate is rotatably connected with the inside of the mounting box 7, a push rod 19 is slidably connected onto the spiral rotating plate, and one end, far away from the spiral rotating plate, of the push rod 19 is fixedly connected with the bottom of the connecting plate 2. According to the invention, the lower pressing assembly and the speed reducing assembly are arranged below the fixing frame 15, the lower pressing assembly and the speed reducing assembly do not adopt elastic structures, when the unmanned aerial vehicle falls, the connecting plate 2 moves downwards to extrude the lower pressing rack 13, the lower pressing rack 13 can drive the limiting rack 10 to move upwards, at the moment, the push rod 19 is matched with the spiral rotating plate, the downward movement speed of the connecting plate 2 can be reduced, and the push rod 19 can not push the spiral rotating plate to rotate any more due to the reduction of the downward pressure of the unmanned aerial vehicle, so that the unmanned aerial vehicle can fall; and during the ejector pin 3 on the spacing rack 10 can stretch into circular slot 17 this moment, wholly carry out the locking spacing to the undercarriage, the cooperation of each structure of undercarriage can realize multistage buffering, stability when improving the descending of unmanned aerial vehicle main part.
Four damping support legs are arranged, each damping support leg comprises a supporting rod 6 and a fixing plate 14, one end of each supporting rod 6 is rotatably connected with a corner of the fixing frame 15, the fixing plate 14 is rotatably connected with a telescopic rod 5, and one end, far away from the fixing plate 14, of each telescopic rod 5 is rotatably connected with a rod body of each supporting rod 6; the shock absorption supporting leg can rotate outwards when being subjected to downward pressure, and the telescopic rod 5 can play a role in buffering, so that the phenomenon that the landing gear inclines due to the fact that the deflection angle of the shock absorption supporting leg is too large is avoided; the telescopic rod 5 is a hydraulic rod.
A plurality of grooves 28 are formed in the connecting plate 2, and springs 23 are fixedly connected inside the grooves 28; the mounting plate 1 is fixedly provided with a plurality of sliding rods 27 towards the connecting plate 2, and the sliding rods 27 are respectively in one-to-one correspondence with the grooves 28; the sliding rod 27 is connected with the groove 28 in a sliding mode, a baffle 26 is fixedly arranged on the rod body of the sliding rod 27, one end of the spring 23 is fixedly connected with the bottom of the groove 28, and the other end of the spring 23 is fixedly connected with the baffle 26; one side of the groove 28 is provided with a clamping assembly which is detachably connected with the baffle 26. The mounting plate 1 is used for being fixedly mounted with the unmanned aerial vehicle, so that the unmanned aerial vehicle and the undercarriage are integrally formed into an organic whole; a limiting ring is arranged at the opening of the groove 28 on the connecting plate 2 and is fixedly connected with the opening of the groove 28, and the limiting ring is used for limiting the baffle 26 and preventing the sliding rod 27 from slipping off the groove 28.
Offer circular slot 17 on connecting plate 2, circular slot 17 is close to recess 28 and arranges, has offered through-hole 24 on the lateral wall between circular slot 17 and the recess 28, and the joint subassembly is located inside through-hole 24, and the joint subassembly includes fixture block 4 with 24 inner walls sliding connection of through-hole, fixedly connected with extension spring 25 between 4 top surfaces of fixture block and the 24 inner walls of through-hole, and the length of fixture block 4 is greater than the length of through-hole 24, and the terminal surface that fixture block 4 is located circular slot 17 one end is the inclined plane of downward sloping. There is the clearance between connecting plate 2 and the mounting panel 1 for realize the buffering when unmanned aerial vehicle descends, in order to prevent the 23 bounce-backs of spring, when fixture block 4 moves down at baffle 26, during ejector pin 3 entered into circular slot 17, ejector pin 3 can promote the translation of fixture block 4, realizes blockking baffle 26, forms the locking.
Two opposite side surfaces of the lower pressing rack 13 are provided with teeth, the middle parts of the other two side surfaces of the lower pressing rack 13 are fixedly connected with sliding strips 12, and the two sliding strips 12 are both connected with a fixed frame 15 in a sliding manner; the top of the pressing rack 13 is fixedly connected with the connecting plate 2.
Two limiting racks 10 are arranged, the two limiting racks 10 are symmetrically arranged relative to the pressing rack 13, and one side, far away from the pressing rack 13, of each limiting rack 10 is connected with the inner wall of the mounting box 7 in a sliding mode; the top of the limiting rack 10 is fixedly connected with an ejector rod 3, the ejector rod 3 is in sliding connection with the circular groove 17, and the ejector rod 3 is detachably connected with the clamping block 4. The ejector rod 3 enters the circular groove 17 to push the fixture block 4, and the limiting rack 10 and the pressing rack 13 are matched with each other at the moment, so that a multi-rod supporting fixing mode can be realized, and the whole landing gear is more stable.
The bottom of the fixed frame 15 is fixedly connected with a cross rod 16, and the cross rod 16 penetrates through two opposite side walls of the mounting box 7 and is fixedly connected with the mounting box 7; the gear wheel 11 is rotatably connected to a cross bar 16.
Two push rods 19 are arranged, each push rod 19 is L-shaped, one end of each push rod 19, which is close to the spiral rotating plate, is rotatably connected with a round ball 22, and the round balls 22 are rotatably connected with the spiral rotating plate; spiral rotor includes pivot 21 and spiral plate 20, and pivot 21 vertical arrangement is inside mounting box 7, and pivot 21 is connected with the inside rotation of mounting box 7, pivot 21 and spiral plate 20 fixed connection. The box body is arranged at the position where the bottom of the rotating shaft 21 is connected with the mounting box 7, the clockwork spring is arranged in the box body and connected with the rotating shaft 21, and when the rotating shaft 21 rotates, the clockwork spring is continuously tightened, so that the rotating shaft 21 can rotate only by larger force, and therefore the process that the push rod 19 downwards extrudes the spiral plate 20 is a gradual speed reduction process, and the stability of the unmanned aerial vehicle can be constantly ensured; when the top rod 3 of the limit rack 10 enters the circular groove 17, the rotating shaft 21 does not move any more, and the clockwork spring is in a tightened state; when the unmanned aerial vehicle takes off, the components in all the positions of the undercarriage can automatically return to the initial positions under the action of the clockwork spring.
The bottom of the mounting box 7 is provided with a support leg 8, and a rubber block 9 is fixedly arranged between the support leg 8 and the mounting box 7.
A plurality of connecting rods 18 are arranged between the connecting plate 2 and the fixing frame, one end of each connecting rod 18 is rotatably connected with the connecting plate 2, and the other end of each connecting plate 2 is rotatably connected with the top surface of the fixing frame 15.
The working process is as follows: when the unmanned aerial vehicle is in actual use, the unmanned aerial vehicle is arranged on the mounting plate 1, when the unmanned aerial vehicle wants to land, the damping supporting legs firstly touch the ground, and when the unmanned aerial vehicle continues to land, the damping supporting legs can be extruded to the outer side, and at the moment, the telescopic rods 5 can play a role in buffering the damping supporting legs; meanwhile, when the unmanned aerial vehicle is pressed downwards, the pressing rack 13 moves downwards, the pressing rack 13 drives the gear 11 to rotate, the gear 11 drives the limiting rack 10 to move upwards, when the ejector rod 3 on the limiting rack 10 moves upwards into the circular groove 17, the ejector rod 3 can push the clamping block 4 to move towards one side of the groove 28, at the moment, the sliding rod 27 in the groove 28 is pressed by the unmanned aerial vehicle to be in contact with the bottom, so that the baffle 26 is positioned below the clamping block 4, and the clamping block 4 can limit the baffle 26; meanwhile, when the connecting plate 2 moves downwards, the push rod 19 can extrude the spiral plate, and the spiral plate can play a role in reducing the speed of the push rod 19 because the spiral plate is connected with the spiral spring below the rotating shaft 21 of the spiral plate; when the ejector pin 3 is located inside the circular groove 17, the unmanned aerial vehicle is landed and completed.
In the description of the present invention, it is to be understood that the terms "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, are merely for convenience of description of the present invention, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.
The above-described embodiments are merely illustrative of the preferred embodiments of the present invention, and do not limit the scope of the present invention, and various modifications and improvements of the technical solutions of the present invention can be made by those skilled in the art without departing from the spirit of the present invention, and the technical solutions of the present invention are within the scope of the present invention defined by the claims.
Claims (10)
1. The utility model provides an unmanned aerial vehicle undercarriage that takes precautions against earthquakes which characterized in that: the shock absorption support leg structure comprises a fixed frame (15), a shock absorption support leg is rotatably connected below the fixed frame (15), a mounting box (7) is fixedly connected to the middle part below the fixed frame (15), a shock absorption mechanism is movably connected inside the mounting box (7), the top of the shock absorption mechanism penetrates through the fixed frame (15) and is fixedly connected with a connecting plate (2), and a mounting plate (1) is elastically connected above the connecting plate (2); the shockproof mechanism comprises a pressing component and a speed reducing component, the pressing component comprises a pressing rack (13), the pressing rack (13) is meshed with a gear (11), the gear (11) is rotatably connected with the mounting box (7), the gear (11) is meshed with a limiting rack (10), and the limiting rack (10) is detachably connected with the connecting plate (2); the speed reduction assembly comprises a spiral rotation plate, the spiral rotation plate is rotatably connected with the inside of the mounting box (7), a push rod (19) is connected to the spiral rotation plate in a sliding mode, and one end, far away from the spiral rotation plate, of the push rod (19) is fixedly connected with the bottom of the connecting plate (2).
2. The shockproof undercarriage for unmanned aerial vehicle of claim 1, wherein: the shock attenuation landing leg is provided with four, every the shock attenuation landing leg includes branch (6) and fixed plate (14), the one end of branch (6) with the corner of mount (15) is rotated and is connected, fixed plate (14) are rotated and are connected with telescopic link (5), keep away from telescopic link (5 the one end of fixed plate (14) with the pole body of branch (6) is rotated and is connected.
3. The shockproof undercarriage for unmanned aerial vehicle of claim 1, wherein: a plurality of grooves (28) are formed in the connecting plate (2), and springs (23) are fixedly connected inside the grooves (28); a plurality of sliding rods (27) are fixedly arranged on the mounting plate (1) towards the connecting plate (2), and the sliding rods (27) are respectively in one-to-one correspondence with the grooves (28); the sliding rod (27) is connected with the groove (28) in a sliding mode, a baffle (26) is fixedly arranged on the rod body of the sliding rod (27), one end of the spring (23) is fixedly connected with the bottom of the groove (28), and the other end of the spring (23) is fixedly connected with the baffle (26); a clamping assembly is arranged on one side of the groove (28), and the clamping assembly is detachably connected with the baffle (26).
4. An unmanned aerial vehicle undercarriage that takes precautions against earthquakes of claim 3, characterized in that: offer circular slot (17) on connecting plate (2), circular slot (17) are close to recess (28) are arranged, circular slot (17) with through-hole (24) have been seted up on the lateral wall between recess (28), the joint subassembly is located inside through-hole (24), the joint subassembly include with through-hole (24) inner wall sliding connection's fixture block (4), fixture block (4) top surface with fixedly connected with extension spring (25) between through-hole (24) inner wall, the length of fixture block (4) is greater than the length of through-hole (24), fixture block (4) are located the terminal surface of circular slot (17) one end is the inclined plane of downward sloping.
5. The shockproof undercarriage for unmanned aerial vehicle of claim 1, wherein: two opposite side surfaces of the lower pressing rack (13) are provided with teeth, the middle parts of the other two side surfaces of the lower pressing rack (13) are fixedly connected with sliding strips (12), and the two sliding strips (12) are connected with the fixed frame (15) in a sliding manner; the top of the pressing rack (13) is fixedly connected with the connecting plate (2).
6. The shockproof undercarriage for unmanned aerial vehicle of claim 4, wherein: two limiting racks (10) are arranged, the two limiting racks (10) are symmetrically arranged relative to the lower pressing rack (13), and one side, far away from the lower pressing rack (13), of each limiting rack (10) is connected with the inner wall of the mounting box (7) in a sliding mode; spacing rack (10) top fixedly connected with ejector pin (3), ejector pin (3) with circular slot (17) sliding connection, ejector pin (3) with fixture block (4) can dismantle the connection.
7. An unmanned aerial vehicle undercarriage that takes precautions against earthquakes of claim 1, characterized in that: the bottom of the fixed frame (15) is fixedly connected with a cross rod (16), and the cross rod (16) penetrates through two opposite side walls of the mounting box (7) and is fixedly connected with the mounting box (7); the gear (11) is rotationally connected with the cross rod (16).
8. The shockproof undercarriage for unmanned aerial vehicle of claim 1, wherein: two push rods (19) are arranged, each push rod (19) is L-shaped, one end, close to the spiral rotating plate, of each push rod (19) is rotatably connected with a round ball (22), and the round balls (22) are rotatably connected with the spiral rotating plate; the spiral rotating plate comprises a rotating shaft (21) and a spiral plate (20), wherein the rotating shaft (21) is vertically arranged inside the mounting box (7), the rotating shaft (21) is rotatably connected with the inside of the mounting box (7), and the rotating shaft (21) is fixedly connected with the spiral plate (20).
9. The shockproof undercarriage for unmanned aerial vehicle of claim 1, wherein: the bottom of the mounting box (7) is provided with a support leg (8), and a rubber block (9) is fixedly arranged between the support leg (8) and the mounting box (7).
10. An unmanned aerial vehicle undercarriage that takes precautions against earthquakes of claim 1, characterized in that: the connecting plate (2) is fixed with a plurality of connecting rods (18) arranged between the connecting plate and the fixing frame, one end of each connecting rod (18) is connected with the connecting plate (2) in a rotating mode, and the other end of each connecting plate (2) is connected with the top surface of the fixing frame (15) in a rotating mode.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211388776.6A CN115610643B (en) | 2022-11-08 | 2022-11-08 | Unmanned aerial vehicle undercarriage that takes precautions against earthquakes |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211388776.6A CN115610643B (en) | 2022-11-08 | 2022-11-08 | Unmanned aerial vehicle undercarriage that takes precautions against earthquakes |
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| CN115610643A true CN115610643A (en) | 2023-01-17 |
| CN115610643B CN115610643B (en) | 2023-07-04 |
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| CN110877716A (en) * | 2019-12-06 | 2020-03-13 | 湖南浩天翼航空技术有限公司 | Elastic support undercarriage based on rack transmission for fixed wing type unmanned aerial vehicle |
| CN211893627U (en) * | 2020-01-17 | 2020-11-10 | 丁武轩 | Plant protection unmanned aerial vehicle's integral type undercarriage |
| CN211996120U (en) * | 2020-04-08 | 2020-11-24 | 杭州明启勘测规划设计有限公司 | Four-wing unmanned aerial vehicle buffering undercarriage |
| CN214776527U (en) * | 2020-10-22 | 2021-11-19 | 陕西锐锋信息技术有限公司 | Unmanned aerial vehicle with descending shock-absorbing function |
| CN214112855U (en) * | 2020-12-31 | 2021-09-03 | 深圳市鸿辉塑胶制品有限公司 | Utilize unmanned aerial vehicle descending seismic isolation device of gear drive principle |
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