CN213262891U

CN213262891U - Antidetonation type four shaft unmanned aerial vehicle aircraft

Info

Publication number: CN213262891U
Application number: CN202021863266.6U
Authority: CN
Inventors: 崔彩云
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-08-31
Filing date: 2020-08-31
Publication date: 2021-05-25
Anticipated expiration: 2030-08-31

Abstract

The utility model discloses an anti-seismic four-axis unmanned aerial vehicle aircraft, which comprises an aircraft main body and supporting legs arranged at the bottom end of the aircraft main body in a mirror image manner; the bottom of aircraft main part is provided with increases steady coupling mechanism, and this increases steady coupling mechanism's bottom middle part is connected with the camera, and increases steady coupling mechanism and be used for fixing a position landing leg mounted position and increase landing leg installation steadiness. The utility model can combine the landing leg with the main body of the aircraft more stably and firmly, improve the shock resistance of the whole landing leg and reduce the vibration and shake yield of the landing leg under the external wind and sand scouring collision effect; meanwhile, the contact rocking wear of the landing leg during landing of the aircraft is reduced, and the probability of breakage and breakage of the landing leg during use is reduced, so that the aircraft has the characteristic of shock resistance, the service life of the landing leg is prolonged, and the aircraft can be used for a long time.

Description

Antidetonation type four shaft unmanned aerial vehicle aircraft

Technical Field

The utility model relates to an unmanned aerial vehicle aircraft technical field specifically is an antidetonation type four-axis unmanned aerial vehicle aircraft.

Background

The four-axis aircraft is also called a four-rotor aircraft and a four-rotor helicopter, and is called four-axis and four-rotor for short; the four-axis aircraft is a multi-rotor aircraft; four propellers of the four-axis aircraft are simple mechanisms directly connected with motors, the cross-shaped layout allows the aircraft to obtain the force for rotating the aircraft body by changing the rotating speed of the motors, so that the self posture is adjusted, and the four-axis aircraft comprises an aircraft body and supporting legs connected to the bottom end of the aircraft body.

The whole shock resistance of current four shaft air vehicle is poor when using, and the landing leg produces a large amount of vibrations easily and rocks under the effect of external sand blown by the wind erodees the collision, and when the aircraft descends, the landing leg produces in a large number when contacting with ground easily and rocks and contact wear simultaneously, leads to the landing leg to take place the problem that the rupture is taken place easily when using, has influenced the life of landing leg, has influenced the holistic life of four shaft air vehicle then.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an antidetonation type four shaft unmanned aerial vehicle aircraft to the whole shock resistance of landing leg that proposes in solving above-mentioned background art is poor, and it rocks to produce a large amount of vibrations easily under the collision effect to erode at the sand blown by the wind of external world, easily takes place to break, and landing leg life is short, influences the whole life's of unmanned aerial vehicle aircraft problem.

In order to achieve the above object, the utility model provides a following technical scheme:

an anti-seismic four-axis unmanned aerial vehicle comprises an aircraft main body and supporting legs arranged at the bottom end of the aircraft main body in a mirror image manner; the bottom of the aircraft main body is provided with a stability augmentation connecting mechanism, the middle of the bottom end of the stability augmentation connecting mechanism is connected with a camera, and the stability augmentation connecting mechanism is used for positioning the mounting position of the landing leg and increasing the mounting stability of the landing leg; and the bottom of the supporting leg is provided with a damping mechanism.

Preferably, the stability augmentation connecting mechanism comprises a stability augmentation plate fixedly connected to the bottom end of the aircraft main body through a connecting piece and positioning and reinforcing parts arranged on two sides of the stability augmentation plate and used for positioning the supporting legs; the middle part of the bottom end of the stabilizing plate is connected with the top end of the camera into a whole.

Preferably, the positioning and reinforcing part comprises positioning grooves which are formed in two sides of the stability augmentation plate and used for accommodating the vertical rods, and a pressing piece which is connected to the stability augmentation plate in a sliding mode; the pressing piece is used for pressing the supporting leg on the wall of the positioning groove; the two sides of the stabilizing plate are provided with sliding grooves which are close to the positioning grooves and used for the pressing pieces to pass through, the overlooking appearance of the positioning grooves is of a U-shaped structure, the groove walls of the positioning grooves are internally bonded with antifriction pads, and the groove cavities of the positioning grooves are communicated with the groove cavities of the sliding grooves.

Preferably, the pressing piece comprises a screw rod extending into the sliding groove, a fixed nut positioned at the back of the stabilizing plate and installed at the rear end of the screw rod, and a movable nut positioned on the front side of the stabilizing plate and connected to the front end of the screw rod in a threaded manner; the outer surface of the screw rod is positioned in the positioning groove, and a top support pad in contact with the supporting leg is movably sleeved at the position.

Preferably, the right-view appearance of the supporting leg is in a U-shaped structure, and the supporting leg is composed of a vertical rod and a cross rod connected to the bottom end of the vertical rod; the damping mechanism is used for reducing vibration abrasion borne by the supporting legs, at least two groups of damping mechanisms are arranged on the damping mechanism, the damping mechanism is connected to the bottom of the cross rod, and a guide hole for mounting the damping mechanism is formed in the cross rod.

Preferably, the damping mechanism comprises a stud in threaded connection with the guide hole, a nut positioned above the cross rod and connected to the top end of the stud, a bottom block fixedly connected to the bottom end of the stud, and a spring positioned between the bottom block and the cross rod and movably sleeved on the outer surface of the stud; and the bottom end of the bottom block is bonded with a shock pad.

Compared with the prior art, the beneficial effects of the utility model are that:

the utility model discloses can let landing leg and aircraft main part combine more stably firm, improved the holistic shock resistance of landing leg, greatly reduced this unmanned aerial vehicle aircraft use the landing leg shake the output under the effect of external sand storm scouring collision; simultaneously this aircraft landing leg produces elastic deformation with ground contact time spring to this reduces the aircraft and rocks wearing and tearing to the produced contact of landing leg when descending, thereby has further improved the shock resistance of landing leg, takes place the fracture probability when reducing the landing leg and use, makes this aircraft wholly have the characteristics of shock resistance, has prolonged the life of landing leg, lets this aircraft whole body use for a long time then.

Drawings

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

FIG. 2 is a top view of the stabilizing plate of the present invention;

FIG. 3 is a perspective view of the structure of the stability-enhancing connecting mechanism of the present invention;

fig. 4 is a schematic structural view of the compressing member of the present invention;

fig. 5 is a schematic structural diagram of the damping mechanism of the present invention.

In the figure: the aircraft comprises an aircraft body 1, supporting legs 2, vertical rods 21, cross rods 22, a stability-increasing connecting mechanism 3, a stability-increasing plate 31, a sliding groove 311, a connecting piece 32, a positioning groove 33, a wear-reducing pad 331, a pressing piece 34, a screw 341, a fixed screw cap 342, a jacking pad 343, a movable screw cap 344, a camera 4, a damping mechanism 5, a bottom block 51, a damping pad 52, a stud 53, a spring 54 and a nut 55.

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 present invention provides a technical solution: an anti-seismic four-axis unmanned aerial vehicle comprises an aircraft body 1 and supporting legs 2 arranged at the bottom end of the aircraft body 1 in a mirror image manner; the bottom of the aircraft main body 1 is provided with a stability-increasing connecting mechanism 3, the middle part of the bottom end of the stability-increasing connecting mechanism 3 is connected with a camera 4, and the stability-increasing connecting mechanism 3 is used for positioning the installation position of the supporting leg 2 and increasing the installation stability of the supporting leg 2; the bottom of the leg 2 is provided with a damping mechanism 5.

Referring to fig. 1, 2, 3 and 4, the stability-enhancing connecting mechanism 3 includes a stability-enhancing plate 31 fixedly connected to the bottom end of the aircraft body 1 through a connecting member 32, and positioning reinforcing portions disposed on both sides of the stability-enhancing plate 31 for positioning the supporting legs 2; the middle part of the bottom end of the stabilizing plate 31 is connected with the top end of the camera 4 into a whole; the positioning and reinforcing part comprises positioning grooves 33 which are arranged on two sides of the stabilizing plate 31 and used for arranging the vertical rods 21 and a pressing piece 34 which is connected to the stabilizing plate 31 in a sliding way; the pressing piece 34 is used for pressing the supporting leg 2 on the groove wall of the positioning groove 33; the two sides of the stabilizing plate 31 are provided with sliding grooves 311 for the pressing piece 34 to pass through at positions close to the positioning groove 33, the overlooking appearance of the positioning groove 33 is in a U-shaped structure, an antifriction pad 331 is bonded in the groove wall of the positioning groove 33, and the groove cavity of the positioning groove 33 is communicated with the groove cavity of the sliding groove 311; the pressing member 34 includes a screw 341 extending into the sliding slot 311, a fixed nut 342 located at the back of the stabilizing plate 31 and installed at the rear end of the screw 341, and a movable nut 344 located at the front of the stabilizing plate 31 and screwed to the front end of the screw 341; a top support pad 343 in contact with the support leg 2 is movably sleeved at a position, in the positioning groove 33, on the outer surface of the screw 341; wherein, the connecting member 32 includes, but is not limited to, a screw and a bolt; the setting of the top supporting pad 343 can reduce the contact wear generated between the screw 341 and the leg 2 when the pressing piece 34 presses the leg 2, and then prolongs the service life of the screw 341 and the leg 2.

In the above scheme, the diameters of the fixed nut 342 and the movable nut 344 both exceed the height of the groove cavity of the sliding groove 311, so that the fixed nut 342 and the movable nut 344 are always located outside the sliding groove 311, the pressing member 34 is convenient to operate to press the leg 2, the whole shape of the top support pad 343 is in a cylindrical or truncated cone structure, and a through hole for the screw 341 to pass through is formed in the middle of the top support pad 343, so that the top support pad 343 can be rapidly sleeved on the screw 341; the overall structure of the stability augmentation plate 31 is in an I-shaped, rectangular or rounded rectangular structure.

Referring to fig. 1, 3 and 5, the right side of the leg 2 is shaped like a "U", and the leg 2 is composed of a vertical rod 21 and a cross rod 22 connected to the bottom end of the vertical rod 21; the damping mechanisms 5 are used for reducing vibration abrasion suffered by the supporting legs 2, at least two groups of damping mechanisms 5 are arranged, the damping mechanisms 5 are connected to the bottom of the cross rod 22, and the cross rod 22 is provided with a guide hole for mounting the damping mechanisms 5; the damping mechanism 5 comprises a stud 53 in threaded connection with the guide hole, a nut 55 positioned above the cross rod 22 and connected with the top end of the stud 53, a bottom block 51 fixedly connected with the bottom end of the stud 53, and a spring 54 positioned between the bottom block 51 and the cross rod 22 and movably sleeved on the outer surface of the stud 53; the bottom end of the bottom block 51 is bonded with a shock pad 52; the damping pad 52, the top supporting pad 343 and the anti-friction pad 331 are made of, but not limited to, rubber; the diameter of the nut 55 exceeds the diameter of the guide hole, so that the nut 55 cannot fall into the guide hole, and the damping mechanism 5 is always firmly installed at the bottom of the cross rod 22 of the support leg 2 under the action of the nut 55.

In the above scheme, the use steps of the stability-increasing connecting mechanism 3 are as follows: the method comprises the following steps that a stabilizing plate 31 is transversely arranged at the bottom of an aircraft body 1 by a connecting piece 32 in advance, and a camera 4 is arranged in the middle of the bottom end of the stabilizing plate 31; then, the supporting legs 2 are installed on two sides of the bottom end of the aircraft body 1 in a mirror image manner, the top end of the vertical rod 21 is connected to the bottom end of the aircraft body 1, at this time, the vertical rod 21 is placed in the groove cavity of the positioning groove 33, and the vertical rod 21 needs to be tightly pressed in the groove cavity of the positioning groove 33 by using the pressing piece 34, namely, the vertical rod 21 is tightly pressed in the positioning groove 33 by using the pressing piece 34 which moves transversely in the sliding groove 311; thereby increase the holistic stability of landing leg 2 for landing leg 2 with increase steady board 31 and firmly combine in an organic whole, improved the steadiness that landing leg 2 and increase steady board 31 are connected, let landing leg 2 stable firm connection in aircraft main part 1 bottom.

The use steps of the pressing piece 34 are as follows: after the vertical rod 21 is vertically arranged in the positioning groove 33, the screw 341 passes through the sliding groove 311, so that the middle section of the screw 341 is positioned in the positioning groove 33, and at the moment, the middle section of the screw 341 is movably sleeved with the supporting pad 343; the fixed nut 342 and the movable nut 344 are used for limiting the screw 341 in the chute 311; during the use, lateral shifting screw 341, make the surface of top brace pad 343 press close to the surface of montant 21, then rotate nut 344, make nut 344 spiral rotation on screw 341, through deciding nut 342 and the cooperation of moving nut 344, let clamping member 34 stably install in spout 311, screw 341 cooperation top brace pad 343 this moment, firmly press the montant 21 to hold in the slot cavity of constant head tank 33, play the effect that increases montant 21 and settle the fastness with this, further consolidate landing leg 2, make landing leg 2 and steadying plate 31 firmly combine in an organic whole, holistic stability when landing leg 2 is installed in aircraft main part 1 bottom has been increased.

The utility model can form the positioning frame of the landing leg 2 on the aircraft main body 1 through the arranged stability-increasing connecting mechanism 3, so that the landing leg 2 is combined with the aircraft main body 1 more stably and firmly, the overall shock resistance of the landing leg 2 is improved, and the yield of vibration and shaking of the landing leg 2 under the action of external sand wind scouring collision when the unmanned aerial vehicle is used is greatly reduced; rely on the damper 5 that sets up simultaneously, can be when this aircraft landing leg 2 contacts with the ground, spring 54 between horizontal pole 22 and the bottom block 51 can produce elastic deformation, shake wearing and tearing to the produced contact of landing leg 2 when reducing the aircraft to descend with this, thereby the shock resistance of landing leg 2 has further been improved, take place the fracture probability when reducing landing leg 2 and use, make this aircraft wholly have the characteristics of shock resistance, be favorable to this unmanned aerial vehicle aircraft's using widely.

Wherein, four screws of this four shaft unmanned aerial vehicle aircrafts all are the simple mechanism that the motor directly links, and crisscross overall arrangement allows the aircraft to obtain the power of rotatory fuselage through changing the motor speed to adjustment self gesture, its camera 4 and aircraft cooperate and use, and its four shaft unmanned aerial vehicle aircrafts's structural principle is well-known technology, and its theory of operation is common technique, and the event is not repeated here.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that 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

1. An anti-seismic four-axis unmanned aerial vehicle comprises an aircraft main body (1) and supporting legs (2) arranged at the bottom end of the aircraft main body (1) in a mirror image manner; the method is characterized in that: the stability augmentation connecting mechanism (3) is arranged at the bottom of the aircraft main body (1), the middle of the bottom end of the stability augmentation connecting mechanism (3) is connected with a camera (4), and the stability augmentation connecting mechanism (3) is used for positioning the installation position of the supporting leg (2) and increasing the installation stability of the supporting leg (2); and the bottom of the supporting leg (2) is provided with a damping mechanism (5).

2. The anti-seismic quadcopter aircraft according to claim 1, characterized in that: the stability augmentation connecting mechanism (3) comprises a stability augmentation plate (31) fixedly connected to the bottom end of the aircraft main body (1) through a connecting piece (32) and positioning and reinforcing parts arranged on two sides of the stability augmentation plate (31) and used for positioning the supporting legs (2); the middle part of the bottom end of the stabilizing plate (31) is connected with the top end of the camera (4) into a whole.

3. The anti-seismic quadcopter aircraft according to claim 2, characterized in that: the positioning and reinforcing part comprises positioning grooves (33) which are arranged on two sides of the stabilizing plate (31) and used for arranging the vertical rods, and a pressing piece (34) which is connected to the stabilizing plate (31) in a sliding way; the pressing piece (34) is used for pressing the supporting leg (2) on the groove wall of the positioning groove (33); the two sides of the stabilizing plate (31) are provided with sliding grooves (311) which are close to the positioning grooves (33) and are used for the pressing pieces (34) to pass through, the overlooking appearance of the positioning grooves (33) is of a U-shaped structure, the groove walls of the positioning grooves (33) are internally bonded with antifriction pads (331), and the groove cavities of the positioning grooves (33) are communicated with the groove cavities of the sliding grooves (311).

4. The anti-seismic quadcopter aircraft according to claim 3, characterized in that: the pressing piece (34) comprises a screw (341) extending into the sliding groove (311), a fixed nut (342) positioned on the back of the stabilizing plate (31) and installed at the rear end of the screw (341), and a movable nut (344) positioned on the front of the stabilizing plate (31) and connected to the front end of the screw (341) in a threaded manner; the outer surface of the screw rod (341) is positioned in the positioning groove (33) and is movably sleeved with a jacking pad (343) which is in contact with the supporting leg (2).

5. The anti-seismic quadcopter aircraft according to claim 1, characterized in that: the right-view appearance of the supporting leg (2) is in a U-shaped structure, and the supporting leg (2) is composed of a vertical rod (21) and a cross rod (22) connected to the bottom end of the vertical rod (21); damper (5) are used for reducing the vibrations wearing and tearing that landing leg (2) received, and this damper (5) are provided with at least two sets ofly, and damper (5) are connected in horizontal pole (22) bottom, and offer the guiding hole that supplies damper (5) to install on horizontal pole (22).

6. The anti-seismic quad unmanned aerial vehicle aircraft of claim 1 or 5, wherein: the damping mechanism (5) comprises a stud (53) in threaded connection with the guide hole, a nut (55) positioned above the cross rod (22) and connected to the top end of the stud (53), a bottom block (51) fixedly connected to the bottom end of the stud (53), and a spring (54) positioned between the bottom block (51) and the cross rod (22) and movably sleeved on the outer surface of the stud (53); the bottom end of the bottom block (51) is bonded with a shock pad (52).