CN218751375U - Unmanned aerial vehicle shock attenuation formula support - Google Patents

Abstract

The utility model discloses an unmanned aerial vehicle shock attenuation formula support relates to unmanned air vehicle technical field, this unmanned aerial vehicle shock attenuation formula support, the reciprocating impact tunnel drilling machine comprises a machine body, the equal fixedly connected with in both sides of fuselage goes up the swash plate, go up the bottom of swash plate and seted up the circular slot, the inner wall sliding connection of circular slot has the cylindric lock, the top fixedly connected with damping spring of cylindric lock. The utility model discloses a set up the swash plate, the cylindric lock, damping spring, three hornblocks and rubber dish, when using, unmanned aerial vehicle's fuselage falls subaerially, rubber dish on the hollow rod at first with the ground contact, rubber dish deformation carries out the shock attenuation, lower swash plate upwards rotates afterwards and drives three hornblocks extrusion connecting strip, damping spring deformation further subtracts the shock attenuation, mutually support through damping spring and rubber dish, change traditional support into shock attenuation formula support, the effect that improves support shock absorption ability has been reached, the vibration that receives when reducing the fuselage descending, reduce the influence that the vibration caused to unmanned aerial vehicle upper part when descending.

Description

Unmanned aerial vehicle shock attenuation formula support

Technical Field

The utility model relates to an unmanned air vehicle technique field specifically is an unmanned aerial vehicle shock attenuation formula support.

Background

Unmanned aerial vehicle is unmanned aerial vehicle's abbreviation, mainly be divided into fixed wing unmanned aerial vehicle and rotor unmanned aerial vehicle etc., wherein rotor unmanned aerial vehicle is comparatively common, common rotor unmanned aerial vehicle has four rotors or six rotor unmanned aerial vehicle, rotor unmanned aerial vehicle mainly by the fuselage, the rotor, support and power are constituteed, a plurality of rotors are located same altitude plane, a plurality of rotors are fixed in the fuselage side, the power is installed in the fuselage, the support is fixed in the bottom of fuselage, support unmanned aerial vehicle subaerial through the support, and play the effect of supporting the fuselage when descending to subaerial.

Common rotor unmanned aerial vehicle support supports unmanned aerial vehicle's fuselage through the support when using, plays the effect of supporting the fuselage when rotor unmanned aerial vehicle descends to subaerial, nevertheless rotor unmanned aerial vehicle carries out rigid buffering by the support when descending to subaerial, and rotor unmanned aerial vehicle's fuselage can vibrate, and the shock-absorbing capacity of support remains to improve.

SUMMERY OF THE UTILITY MODEL

The utility model provides an unmanned aerial vehicle shock attenuation formula support possesses the advantage that improves support shock-absorbing capacity to solve the problem that proposes in the background art.

For the purpose that realizes improving support shock-absorbing capacity, the utility model provides a following technical scheme: the utility model provides an unmanned aerial vehicle shock attenuation formula support, includes the fuselage, the equal fixedly connected with in both sides of fuselage goes up the swash plate, the circular slot has been seted up to the bottom of going up the swash plate, the inner wall sliding connection of circular slot has the cylindric lock, the top fixedly connected with damping spring of cylindric lock, damping spring's top and the top fixed connection of circular slot inner wall, the tip fixedly connected with connecting strip of cylindric lock, the side fixedly connected with connecting seat of going up the swash plate, L shape connecting block has been cup jointed in connecting seat inner wall fixed connection's pivot surface activity, swash plate under the side fixedly connected with of L shape connecting block, the top fixedly connected with three hornblocks of swash plate down, the top of three hornblocks and the bottom swing joint of connecting strip, the bottom fixedly connected with bottom buffer beam of swash plate down.

As an optimal technical scheme of the utility model, the bottom of connecting strip is the curved surface, the top of three hornblocks is the inclined plane, the curved surface of connecting strip bottom and the inclined plane laminating at three hornblock tops.

As a preferred technical scheme of the utility model, the inner wall fixedly connected with stopper of L shape connecting block, the arc wall has been seted up on the surface of pivot, the inner wall of arc wall and the surface swing joint of stopper.

As a preferred technical scheme of the utility model, the quantity of bottom buffer beam is two, two the bottom buffer beam uses the vertical face in center through the fuselage to set up as the symmetry plane symmetry.

As a preferred technical scheme of the utility model, the bottom buffer beam includes hollow pole, hollow pole fixed connection is in the bottom of swash plate down, the equal fixedly connected with rubber disc in both ends of hollow pole, the cushion chamber has been seted up to the inside of rubber disc.

As an optimal technical scheme of the utility model, go up the swash plate and be the carbon fiber board with lower swash plate, L shape connecting block is L shape carbon fiber piece.

Compared with the prior art, the utility model provides an unmanned aerial vehicle shock attenuation formula support possesses following

Has the advantages that:

1. this unmanned aerial vehicle shock attenuation formula support, through setting up the swash plate, the cylindric lock, damping spring, three hornblocks and rubber dish, when using, unmanned aerial vehicle's fuselage falls subaerially, rubber dish on the hollow rod is at first with ground contact, rubber dish deformation carries out the shock attenuation under the reaction force on ground and unmanned aerial vehicle self action of gravity, down the swash plate upwards rotates and drives three hornblocks extrusion connecting strip afterwards, make the connecting strip pass through the damping spring in the cylindric lock extrusion swash plate, damping spring deformation further carries out the shock attenuation, mutually supporting through damping spring and rubber dish, change traditional support into the shock attenuation formula support, the effect that improves support shock-absorbing capacity has been reached, the vibration that receives when reducing the fuselage descending, reduce the influence that the part caused on unmanned aerial vehicle because of when descending.

2. This unmanned aerial vehicle shock attenuation formula support, through setting up the stopper, when using, the stopper is arranged in changeing epaxial arc wall, and after unmanned aerial vehicle takes off, the stopper is laminated with the side that the arc wall inner wall is located the top department, blocks L shape connecting block to block down the swash plate, prevent down the swash plate and rotate downwards.

Drawings

Fig. 1 is a schematic view of the overall structure of the present invention;

fig. 2 is a front view of the present invention;

FIG. 3 is a front sectional view of the cylindrical pin of the present invention;

FIG. 4 is a front sectional view of the position of the limiting block of the present invention;

fig. 5 is a front sectional view of the rubber disk of the present invention.

In the figure: 1. a body; 2. an upper sloping plate; 3. a cylindrical pin; 4. a circular groove; 5. a damping spring; 6. a connecting strip; 7. a connecting seat; 8. a rotating shaft; 9. a bottom bumper bar; 901. a hollow shaft; 902. a rubber disc; 903. a buffer chamber; 10. a lower sloping plate; 11. a triangular block; 12. an L-shaped connecting block; 13. a limiting block; 14. an arc-shaped groove.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-5, the utility model discloses a shock absorption type support for unmanned aerial vehicles, which comprises a body 1, wherein two sides of the body 1 are fixedly connected with two upper inclined plates 2, the two upper inclined plates 2 are in splayed shape and fixed on two sides of the body 1, the bottom of the upper inclined plate 2 is provided with two circular grooves 4, the number of the circular grooves 4 at the same upper inclined plate 2 is two and respectively corresponds to two cylindrical pins 3, the inner wall of the circular groove 4 is slidably connected with the cylindrical pins 3, the top of the cylindrical pins 3 is fixedly connected with a shock absorption spring 5, the top of the shock absorption spring 5 is fixedly connected with the top of the inner wall of the circular groove 4, the shock absorption spring 5 is fixed in the circular groove 4 for shock absorption when the unmanned aerial vehicle descends, the end part of the cylindrical pins 3 is fixedly connected with a connecting strip 6, and the number of the connecting strip 6 is two, the quantity of 6 position cylindric locks 3 of same connecting strip is two, the side fixedly connected with connecting seat 7 of upper inclined plate 2, L shape connecting block 12 has been cup jointed in the activity of the 8 surfaces of pivot of connecting seat 7 inner wall fixed connection, the positive dissection picture of L shape connecting block 12 is L shape, swash plate 10 under the side fixedly connected with of L shape connecting block 12, the central axis of lower swash plate 10 and the central axis coincidence of upper inclined plate 2, the top fixedly connected with triangle-shaped piece 11 of lower swash plate 10, the top of triangle-shaped piece 11 and the bottom swing joint of connecting strip 6, the bottom fixedly connected with bottom buffer beam 9 of lower swash plate 10, bottom buffer beam 9 provides preliminary shock attenuation buffering when descending for unmanned aerial vehicle, constitute the shock attenuation formula support through above-mentioned structure, the vibration that produces when reducing rotor descending unmanned aerial vehicle.

Specifically, the bottom of the connecting strip 6 is a curved surface, the top of the triangular block 11 is an inclined surface, and the curved surface at the bottom of the connecting strip 6 is attached to the inclined surface at the top of the triangular block 11.

In this embodiment, the inclined plane of triangle block 11 extrudes the curved surface of connecting strip 6 to make connecting strip 6 drive cylindric lock 3 along the inner wall upward movement of circular slot 4 and extrude damping spring 5.

Specifically, the inner wall fixedly connected with stopper 13 of L shape connecting block 12, arc wall 14 has been seted up on the surface of pivot 8, the inner wall of arc wall 14 and stopper 13's surface swing joint.

In this embodiment, after unmanned aerial vehicle takes off, damping spring 5 does not receive the influence of 1 gravity of unmanned aerial vehicle fuselage, damping spring 5 extends under self elastic action, make cylindric lock 3 drive the inclined plane of connecting strip 6 extrusion triangle piece 11, make triangle piece 11 drive L nature connecting block and down the swash plate 10 use pivot 8 to rotate as the axle down, L shape connecting block 12 drives the inner wall laminating that stopper 13 and 14 inner walls of arc wall are located top department, swash plate 10 just stops the rotation down after the laminating.

Specifically, the number of the bottom buffer rods 9 is two, and the two bottom buffer rods 9 are symmetrically arranged with a central vertical plane passing through the machine body 1 as a symmetry plane.

In this embodiment, two bottom buffer beam 9 are fixed respectively in the bottom of two lower swash plates 10 for play preliminary shock attenuation cushioning effect when descending unmanned aerial vehicle.

Specifically, bottom buffer beam 9 includes hollow rod 901, and hollow rod 901 fixed connection is in the bottom of swash plate 10 down, the equal fixedly connected with rubber disc 902 in both ends of hollow rod 901, and cushion chamber 903 has been seted up to rubber disc 902's inside.

In this embodiment, the rubber disc 902 is fixed at the end of the hollow rod 901, the hollow rod 901 is used for connecting the rubber disc 902 with the lower inclined plate 10, and the buffer cavity 903 is arranged inside the rubber disc 902 to provide a space for deformation of the rubber disc 902.

Specifically, the upper inclined plate 2 and the lower inclined plate 10 are both carbon fiber plates, and the L-shaped connecting block 12 is an L-shaped carbon fiber block.

In this embodiment, the carbon fiber has light in weight and the high advantage of rigidity, reduces the weight of swash plate 2, lower swash plate 10 and L shape connecting block 12 to the resistance when reducing unmanned aerial vehicle and taking off.

The utility model discloses a theory of operation and use flow: when the unmanned aerial vehicle is used, when the body 1 of the unmanned aerial vehicle descends to the ground, the rubber disc 902 on the hollow rod 901 firstly contacts with the ground, the bottom of the rubber disc 902 deforms to absorb shock under the action of the reaction force of the ground and the self gravity of the unmanned aerial vehicle, the buffer cavity 903 provides a space for the deformation of the rubber disc 902, then the hollow rod 901 drives the lower inclined plate 10 and the L-shaped connecting block 12 to rotate axially by using the rotating shaft 8 of the inner wall of the connecting seat 7, at the moment, the L-shaped connecting block 12 drives the limiting block 13 to rotate along the inner wall of the arc-shaped groove 14, the limiting block 13 is separated from the side face of the inner wall of the arc-shaped groove 14, the lower inclined plate 10 drives the inclined face of the triangular block 11 to extrude the curved face of the connecting strip 6, so that the connecting strip 6 drives the cylindrical pin 3 to move upwards along the inner wall of the circular groove 4 and extrude the damping spring 5, damping spring 5 compression deformation further carries out the shock attenuation, mutually support through damping spring 5 and rubber disc 902, dual shock attenuation when realizing that unmanned aerial vehicle descends, improve the support to unmanned aerial vehicle fuselage 1's shock-absorbing capacity, after unmanned aerial vehicle takes off, damping spring 5 and rubber disc 902 department do not receive the influence of unmanned aerial vehicle fuselage 1 gravity, damping spring 5 extends under self elastic action, make cylindric lock 3 drive the inclined plane of 6 extrusion triangle blocks 11 of connecting strip, make triangle block 11 drive L nature connecting block and down the inclined plate 10 use pivot 8 to rotate down as the axle, L shape connecting block 12 drives the inner wall laminating that stopper 13 and 14 inner walls of arc wall are located top department, the inclined plate 10 just stops the downwardly directed rotation under the laminating, rubber disc 902 resumes to normal form under self elastic action.

It should be noted that, in this document, terms such as "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising a … …" does not exclude the presence of another identical element in a process, method, article, or apparatus that comprises the element.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims (6)

1. The utility model provides an unmanned aerial vehicle shock attenuation formula support, includes fuselage (1), its characterized in that: the utility model discloses a damping mechanism for a ship, including fuselage (1), equal fixedly connected with in both sides of fuselage (1) goes up swash plate (2), circular slot (4) have been seted up to the bottom of going up swash plate (2), the inner wall sliding connection of circular slot (4) has cylindric lock (3), the top fixedly connected with damping spring (5) of cylindric lock (3), the top fixed connection of damping spring (5) and circular slot (4) inner wall, the tip fixedly connected with connecting strip (6) of cylindric lock (3), the side fixedly connected with connecting seat (7) of going up swash plate (2), L shape connecting block (12) have been cup jointed in connecting seat (7) inner wall fixed connection's pivot (8) surface activity, swash plate (10) under the side fixedly connected with of L shape connecting block (12), the top fixedly connected with triangle piece (11) of down swash plate (10), the top and the bottom swing joint of connecting strip (6) of triangle piece (11), the bottom fixedly connected with bottom buffer beam (9) of swash plate (10) down.

2. The unmanned aerial vehicle shock attenuation formula support of claim 1, its characterized in that: the bottom of connecting strip (6) is the curved surface, the top of three hornblocks (11) is the inclined plane, the curved surface of connecting strip (6) bottom and the inclined plane laminating at three hornblocks (11) top.

3. The unmanned aerial vehicle shock attenuation formula support of claim 1, its characterized in that: the inner wall fixedly connected with stopper (13) of L shape connecting block (12), arc wall (14) have been seted up on the surface of pivot (8), the inner wall of arc wall (14) and the surface swing joint of stopper (13).

4. The unmanned aerial vehicle shock attenuation formula support of claim 1, its characterized in that: the number of bottom buffer beam (9) is two, two bottom buffer beam (9) use the vertical face in center through fuselage (1) to set up as the symmetry plane symmetry.

5. The unmanned aerial vehicle shock attenuation formula support of claim 1, its characterized in that: the bottom buffer rod (9) comprises a hollow rod (901), the hollow rod (901) is fixedly connected to the bottom of the lower inclined plate (10), rubber discs (902) are fixedly connected to two ends of the hollow rod (901), and a buffer cavity (903) is formed in the rubber discs (902).

6. The unmanned aerial vehicle shock attenuation formula support of claim 1, its characterized in that: the upper inclined plate (2) and the lower inclined plate (10) are both carbon fiber plates, and the L-shaped connecting block (12) is an L-shaped carbon fiber block.

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