CN218187874U

CN218187874U - Remote control model airplane with landing buffer device

Info

Publication number: CN218187874U
Application number: CN202221049880.8U
Authority: CN
Inventors: 孟一
Original assignee: Rui Ye Century Shenzhen Hobby Co ltd
Current assignee: Rui Ye Century Shenzhen Hobby Co ltd
Priority date: 2022-05-05
Filing date: 2022-05-05
Publication date: 2023-01-03
Anticipated expiration: 2032-05-05

Abstract

The utility model discloses a remote control model airplane with landing buffer device, which comprises a mounting groove arranged at the bottom of the wing of the model airplane, wherein a mounting plate is fixedly connected in the mounting groove through bolts, the bottom of the mounting plate is hinged with a strut, the bottom end of the strut is hinged with a wheel carrier, the inner side of the wheel carrier is rotatably provided with a roller, the outer wall of the wheel carrier is hinged with a first buffer rod, the top end of the first buffer rod is hinged with the outer wall of the strut, the outer wall of the strut is sleeved with a lantern ring, and the bottom of the mounting plate is positioned at the two sides of the strut and symmetrically hinged with two second buffer rods; the utility model discloses in, through the setting of two second buffer beam, when the gyro wheel received the impact of side direction, the wheel carrier can drive the pillar and deflect under the mounting panel to drive two second guide arms and remove, absorb the side direction impact force with the deformation that utilizes two third springs, thereby effectively avoid gyro wheel, wheel carrier and pillar etc. to take place to damage.

Description

Remote control model airplane with landing buffer device

Technical Field

The utility model relates to a remote control model aircraft specifically is a remote control model aircraft with buffer falls to ground.

Background

The remote control model airplane is a remote control flying toy with certain safety, operation simplicity, interest and playability.

At present, although the rear wheels of most remote control model airplanes are provided with the buffer devices, the rear wheels can only buffer the front impact on the airplane wheels, and the lateral force on the airplane wheels cannot be buffered, so that when the model airplane lands, the airplane wheels are prone to being inclined and damaged due to the lateral impact, and the buffering effect is still to be improved.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a remote control model aircraft with buffer falls to ground to solve the problem that proposes in the above-mentioned background art.

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

the utility model provides a remote control model aircraft with buffer falls to ground, is including seting up the mounting groove in the bottom of the wing of model aircraft, through bolt fixedly connected with mounting panel in the mounting groove, the bottom of mounting panel articulates there is the pillar, the bottom of pillar articulates there is the wheel carrier, the inboard of wheel carrier is rotated and is installed the gyro wheel, the outer wall of wheel carrier articulates there is first buffer beam, the top of first buffer beam is articulated with the outer wall of pillar, the outer wall cover of pillar is equipped with the lantern ring, the bilateral symmetry that the bottom of mounting panel is located the pillar articulates there are two second buffer beams, the bottom of second buffer beam all articulates with the lantern ring.

As a further aspect of the present invention: first buffer beam includes first sleeve, first telescopic top is articulated with the pillar, first spring, first movable block, first guide arm have set gradually from top to bottom in first telescopic inside, first movable block and first guide arm fixed connection, the bottom of first guide arm is articulated with the wheel carrier after running through first sleeve, first movable block, first guide arm all with first sleeve sliding connection, the outer wall cover that first guide arm is located first sleeve is equipped with the second spring.

As a further aspect of the present invention: the second buffer rod comprises a second sleeve with a top end hinged to the installation plate, a third spring and a second movable block are sequentially arranged inside the second sleeve from top to bottom, the second movable block is connected with the second sleeve in a sliding mode, a second guide rod is fixedly connected to the bottom surface of the second movable block, and the bottom end of the second guide rod is hinged to the lantern ring after penetrating through the second sleeve.

As a further aspect of the present invention: the lantern ring is connected with the pillar in a sliding mode, and the outer wall of the lantern ring is connected with a screw in a threaded mode.

As the utility model discloses further scheme again: the outer wall of the pillar is provided with a vertical groove, and the threaded end of the screw is abutted to the inner wall of the vertical groove.

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

1. the utility model discloses in, through the setting of two second buffer beam, when the gyro wheel received the impact of side direction, the wheel carrier can drive the pillar and deflect under the mounting panel to drive two second guide arms and remove, absorb the side direction impact force with the deformation that utilizes two third springs, thereby effectively avoid gyro wheel, wheel carrier and pillar etc. to take place to damage.

2. The utility model discloses in, through the setting of first spring and second spring, can make first movable block and second guide arm receive two thrust that opposite direction size is the same simultaneously, when making keep certain contained angle between wheel carrier and pillar, when gyro wheel and ground contact received the impact, the wheel carrier can drive first guide arm to first sleeve inside/outside removal according to the difference of assaulting the atress, absorb the impact that the gyro wheel received with the deformation of utilizing first spring and second spring, thereby play good buffering effect.

3. The utility model discloses in, highly adjust the lantern ring through on the pillar to screw up the bolt and lock the lantern ring, can adjust the precompression volume of two third springs, thereby when the user of being convenient for adjusts the gyro wheel by oneself and receives the side direction and assault, the pillar is at the deflection volume of mounting panel bottom.

Drawings

Fig. 1 is a schematic structural view of a remote control model airplane with a landing buffer device.

Fig. 2 is a schematic structural view of a vertical slot in a remote control model airplane having a landing buffer device.

Fig. 3 is a schematic structural view of a first buffer rod in a remote control model airplane with a landing buffer device.

The aircraft comprises an airfoil 1, a mounting groove 2, a mounting plate 3, a strut 4, a wheel carrier 5, a roller 6, a first buffer rod 7, a first sleeve 8, a first spring 9, a first movable block 10, a first guide rod 11, a second spring 12, a vertical groove 13, a lantern ring 14, a screw 15, a second buffer rod 16, a second sleeve 17, a third spring 18, a second movable block 19 and a second guide rod 20.

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.

Please refer to fig. 1-3, in the embodiment of the present invention, a remote control model airplane with a landing buffer device, includes the mounting groove 2 set up at the bottom of the wing 1 of the model airplane, there is a mounting plate 3 through bolt fixedly connected with in the mounting groove 2, the bottom of the mounting plate 3 is hinged with a pillar 4, the bottom of the pillar 4 is hinged with a wheel carrier 5, the roller 6 is installed in the rotation of the inner side of the wheel carrier 5, the outer wall of the wheel carrier 5 is hinged with a first buffer rod 7, the top of the first buffer rod 7 is hinged with the outer wall of the pillar 4, the outer wall cover of the pillar 4 is provided with a lantern ring 14, the bilateral symmetry of the bottom of the mounting plate 3 located the pillar 4 is hinged with two second buffer rods 16, the bottom of the second buffer rods 16 is hinged with the lantern ring 14.

First buffer beam 7 includes first sleeve 8, the top of first sleeve 8 is articulated with pillar 4, first spring 9, first movable block 10, first guide arm 11 have set gradually from top to bottom in the inside of first sleeve 8, first movable block 10 and first guide arm 11 fixed connection, first guide arm 11's bottom is run through behind the first sleeve 8 articulated with wheel carrier 5, first movable block 10, first guide arm 11 all with first sleeve 8 sliding connection, the outer wall cover that first guide arm 11 is located first sleeve 8 is equipped with second spring 12.

Through the setting of first spring 9 and second spring 12, can make first movable block 10 and second guide arm 11 receive two thrust that opposite direction size is the same simultaneously to when making keep certain contained angle between wheel carrier 5 and pillar 4, when gyro wheel 6 contacts and receives the impact with ground, wheel carrier 5 can drive first guide arm 11 to first sleeve 8 inside/outside removal according to the difference of assaulting the atress, absorb the impact that gyro wheel 6 received with the deformation of first spring 9 and second spring 12, thereby play good buffering effect.

Second buffer pole 16 includes top and the 3 articulated second sleeves 17 of mounting panel, the inside of second sleeves 17 has from top to bottom set gradually third spring 18 and second movable block 19, second movable block 19 and second sleeves 17 sliding connection, the bottom surface fixedly connected with second guide arm 20 of second movable block 19, the bottom of second guide arm 20 runs through behind the second sleeves 17 articulated with the lantern ring 14.

Through the setting of two second buffer beam 16, when gyro wheel 6 received the impact of side direction, wheel carrier 5 can drive pillar 4 and deflect under mounting panel 3 to drive two second guide arms 20 and remove, absorb the side direction impact force with the deformation that utilizes two third springs 18, thereby effectively avoid gyro wheel 6, wheel carrier 5 and pillar 4 etc. to take place to damage.

The lantern ring 14 is connected with the support 4 in a sliding mode, and a screw 15 is connected to the outer wall of the lantern ring 14 in a threaded mode.

By adjusting the height of the collar 14 on the post 4 and tightening the bolt 15 to lock the collar 14, the amount of precompression of the two third springs 18 can be adjusted, thereby facilitating the user to self-adjust the amount of deflection of the post 4 at the bottom of the mounting plate 3 when the roller 6 is laterally impacted.

The outer wall of the pillar 4 is provided with a vertical groove 13, and the threaded end of the screw 15 is abutted against the inner wall of the vertical groove 13.

The collar 14 is prevented from rotating on the post 4 by the cooperation of the vertical slots 13 with the screws 15.

The utility model discloses a theory of operation is:

the utility model discloses in, through the setting of two second buffer beam 16, when gyro wheel 6 received the impact of side direction, wheel carrier 5 can drive pillar 4 and deflect under mounting panel 3 to drive two second guide arms 20 and remove, absorb the side direction impact force with the deformation that utilizes two third springs 18, thereby effectively avoid gyro wheel 6, wheel carrier 5 and pillar 4 etc. to take place to damage.

The utility model discloses in, through the setting of first spring 9 and second spring 12, can make first movable block 10 and second guide arm 11 receive two opposite direction big or small the same thrust simultaneously, so that when keeping certain contained angle between wheel carrier 5 and pillar 4, when gyro wheel 6 and ground contact received the impact, wheel carrier 5 can drive first guide arm 11 to first sleeve 8 inside/outside removal according to the difference of assaulting the atress, absorb the impact that gyro wheel 6 received with the deformation of second spring 12, thereby play good buffering effect.

The utility model discloses in, adjust through the height to lantern ring 14 on pillar 4 to screw up bolt 15 and lock lantern ring 14, can adjust the precompression volume of two third springs 18, thereby when being convenient for the user adjusts gyro wheel 6 by oneself and receives the side impact, pillar 4 is at the deflection volume of mounting panel 3 bottom.

Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments or portions thereof without departing from the spirit and scope of the invention.

Claims

1. A remote control model airplane with a landing buffer device is characterized in that: including offering mounting groove (2) in wing (1) bottom at model aircraft, through bolt fixedly connected with mounting panel (3) in mounting groove (2), the bottom of mounting panel (3) articulates there is pillar (4), the bottom of pillar (4) articulates there is wheel carrier (5), gyro wheel (6) are installed in the inboard rotation of wheel carrier (5), the outer wall of wheel carrier (5) articulates there is first buffer beam (7), the top of first buffer beam (7) is articulated with the outer wall of pillar (4), the outer wall cover of pillar (4) is equipped with lantern ring (14), the bilateral symmetry that the bottom of mounting panel (3) is located pillar (4) articulates there are two second buffer beams (16), the bottom of second buffer beam (16) all articulates with lantern ring (14).

2. The remote control model aircraft with landing cushioning device of claim 1, wherein: first buffer beam (7) include first sleeve (8), the top and pillar (4) of first sleeve (8) are articulated, the inside of first sleeve (8) has set gradually first spring (9), first movable block (10), first guide arm (11) from top to bottom, first movable block (10) and first guide arm (11) fixed connection, the bottom of first guide arm (11) runs through behind first sleeve (8) articulated with wheel carrier (5), first movable block (10), first guide arm (11) all with first sleeve (8) sliding connection, outer wall cover that first guide arm (11) are located first sleeve (8) is equipped with second spring (12).

3. A remote controlled model aircraft having a landing cushioning device as set forth in claim 1, wherein: second buffer beam (16) include top and mounting panel (3) articulated second sleeve (17), the inside of second sleeve (17) has set gradually third spring (18) and second movable block (19) from top to bottom, second movable block (19) and second sleeve (17) sliding connection, the bottom surface fixedly connected with second guide arm (20) of second movable block (19), the bottom of second guide arm (20) runs through behind second sleeve (17) and articulates with the lantern ring (14).

4. The remote control model aircraft with landing cushioning device of claim 1, wherein: the lantern ring (14) is connected with the strut (4) in a sliding mode, and the outer wall of the lantern ring (14) is connected with a screw (15) in a threaded mode.

5. The remote control model airplane with landing cushioning device according to claim 4, wherein: the outer wall of the pillar (4) is provided with a vertical groove (13), and the threaded end of the screw (15) is abutted to the inner wall of the vertical groove (13).