CN210162244U

CN210162244U - Telecontrolled aircraft with shock attenuation prevents falling structure

Info

Publication number: CN210162244U
Application number: CN201920668733.0U
Authority: CN
Inventors: 瞿君
Original assignee: Shenzhen Ruijinyuan Trading Co Ltd
Current assignee: Shenzhen Ruijinyuan Trading Co Ltd
Priority date: 2019-05-10
Filing date: 2019-05-10
Publication date: 2020-03-20
Anticipated expiration: 2029-05-10

Abstract

The utility model relates to the technical field of remote control airplanes, in particular to a remote control airplane with a shock-absorbing and anti-falling structure, which comprises two mounting frameworks, wherein the two mounting frameworks are provided with a motor transmission assembly, the motor transmission assembly is provided with a main wing, the motor transmission assembly is fixedly provided with an auxiliary wing, one end of the installation framework far away from the auxiliary wing is fixedly provided with a fuselage protective shell, the machine body protection shell is provided with two opposite connecting frames, two opposite mounting blocks are fixedly arranged at one ends of the two connecting frames far away from the machine body protection shell, a buffer plate is arranged on one side of the mounting block far away from the connecting frame, a first damping spring is fixedly arranged between one side of the buffer plate opposite to the mounting block, through the utility model discloses an improvement, the antidetonation that has effectively strengthened whole fuselage prevents the characteristic that falls, simple structure, easily operation is fit for promoting.

Description

Telecontrolled aircraft with shock attenuation prevents falling structure

Technical Field

The utility model relates to a remote control aircraft technical field especially relates to a remote control aircraft with shock attenuation prevents falling structure.

Background

With the development and progress of science and technology, people pay more and more attention to the development of resources and vehicles in the aerospace field. In recent years, people not only explore in the technical field of large-scale aviation airplanes, but also invent small-scale remote control aircrafts as aerial photography and remote detection tools. Moreover, with the popularization of science and technology, remote control airplanes still enter the ranks of children's toys at present. However, most of the remote control airplanes sold in the market at present have the limitation of remote control distance, and once the remote control distance is exceeded, the airplanes can land uncontrollably or have the phenomenon of random collision, so that the airplane body is easily damaged. Or in extreme weather, because the remote control plane has light weight and weak wind resistance, the remote control plane is easy to be controlled by a user, and the remote control plane is required to have certain earthquake-resistant and falling-resistant characteristics. Therefore, the utility model provides a remote control aircraft with shock attenuation is prevented falling structure solves above-mentioned problem.

SUMMERY OF THE UTILITY MODEL

The utility model aims at solving the problem that the shock resistance and the falling resistance of the airplane body are poor in the prior art, and providing a remote control airplane with a shock-absorbing and falling-resistant structure.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

designing a remote control aircraft with a shock-absorbing anti-falling structure, comprising two opposite installation frameworks, wherein a motor transmission assembly installed along the vertical direction is fixedly arranged between one opposite sides of the two installation frameworks, a main wing is fixedly arranged at the shaft end of the motor transmission assembly, an auxiliary wing is fixedly arranged at one opposite side of the motor transmission assembly and the main wing, a fuselage protective shell is fixedly arranged at one end of the installation framework far away from the auxiliary wing, two opposite connecting frames are detachably connected at one side of the fuselage protective shell far away from the installation frameworks through screws, two opposite installation blocks are fixedly arranged at one ends of the two connecting frames far away from the fuselage protective shell, a buffer plate is arranged at one side of the installation blocks far away from the connecting frames, and a first shock-absorbing spring is fixedly arranged between one opposite side of the buffer plate and the installation blocks, a tail shaft is fixedly arranged at one end of the mounting framework, which is perpendicular to the mounting direction of the motor transmission assembly, a rotating motor is arranged at one end of the tail shaft, which is far away from the mounting framework, a tail wing is fixedly arranged at the end of a motor shaft of the rotating motor, a tail wing shield matched with the tail wing is fixedly arranged at the outer side of the circumference of the tail wing, an inclined supporting rod is detachably connected to the outer side of the circumference of the tail shaft, which is adjacent to the tail wing shield, through screws, a connecting rod is arranged at one end of the inclined supporting rod, which is far away from the tail shaft, a connecting rod is fixedly connected to one side of the protective shell of the body, one end of the connecting rod, which is far away from the inclined supporting rod, is provided with a chute matched with the inclined supporting rod, a buffer spring is fixedly arranged between the outer side of the circumference of the, the utility model discloses a damping device of a motor vehicle, including anterior casing, installation skeleton, installation roof beam, support column, pivot, first rocking arm, installation frame, installation roof beam, the one side of anterior casing is fixed and is equipped with the anticollision roof beam, the anticollision roof beam with fixed second damping spring that is equipped with between the relative one side of installation roof beam, anterior casing with the adjacent one side of installation roof beam is all fixed and is equipped with a support column, the support column is kept away from the one end of anterior casing is rotated through the pivot and is connected and be equipped with first rocking arm, first rocking arm is kept away from the one.

Preferably, the adjustable buffer device comprises a fixed rod, one end of the fixed rod is provided with a limit chute, the bottom of the limiting sliding groove is provided with an adjusting bolt, the tail part of a stud of the adjusting bolt is fixedly provided with a piston head matched with the limiting sliding groove, one end of the limiting sliding groove far away from the piston head is provided with a movable rod matched with the limiting sliding groove, an adjustable buffer spring is fixedly arranged between one end of the movable rod opposite to the piston head, one end of the movable rod far away from the fixed rod is fixedly connected with the first rocker arm, a fixing lug is arranged on one side of the second rocker arm opposite to the adjusting bolt, a threaded hole matched with the adjusting bolt is arranged on one side of the fixing lug, the appearance of anticollision roof beam with anterior casing phase-match, the main wing with the connecting axle circumference outside of assisting the wing all is equipped with rather than the protection axle sleeve that matches.

The utility model provides a pair of remote control aircraft with shock attenuation is prevented falling structure, beneficial effect lies in: through the arrangement of the mounting beam, the anti-collision beam and the second damping spring, the impact on the front part of the machine body is buffered and is dispersed to a part of the front shell, so that the impact is further relieved through the first rocker arm and the second rocker arm, the appearance of the anti-collision beam is matched with the front shell, and the cool feeling of the machine body is enhanced; the impact from the upper part of the machine body can be directly pressed downwards through the front shell, because the front shell is connected with a heavy transmission device and a motor inside, and the impact force is transmitted to the first rocker arm and the second rocker arm through the front shell and is finally absorbed by the adjustable buffer device; the descending vibrations of bottom can be absorbed by buffer board and the damping spring of undercarriage lower part, and tail department still is equipped with bearing diagonal pole and damping spring to and the fin guard shield, can effectually prevent buckling of tail axle and the damage of fin, wholly strengthened the shockproof and prevent falling the attribute of fuselage, simple structure, practicality are fit for promoting.

Drawings

Fig. 1 is a schematic side view of a remote control aircraft with a shock-absorbing and anti-falling structure according to the present invention;

fig. 2 is a schematic view of a rear view structure of a remote control aircraft with a shock-absorbing and anti-falling structure provided by the present invention;

FIG. 3 is a schematic view of the internal structure of the part 21 of FIG. 1;

fig. 4 is a schematic view of the structure associated with the component 17 of fig. 1.

In the figure: the mounting frame 1, the motor transmission assembly 2, the auxiliary wing 3, the main wing 4, the fuselage protective housing 5, the link 6, the mounting block 7, the buffer plate 8, the first damping spring 9, the tail shaft 10, the tail 11, the tail guard 12, the diagonal bracing rod 13, the connecting rod 14, the buffer spring 15, the front housing 16, the anti-collision beam 17, the support column 18, the first rocker arm 19, the second rocker arm 20, the adjustable buffer device 21, the mounting beam 22, the second damping spring 23, the fixed rod 211, the adjusting bolt 212, the piston head 213, the movable rod 214, the adjustable buffer spring 215 and the limiting sliding groove 216.

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.

Referring to fig. 1-4, a remote control aircraft with shock-absorbing and anti-falling structure comprises two opposite installation frameworks 1, a motor transmission assembly 2 installed along the vertical direction is fixedly arranged between one opposite sides of the two installation frameworks 1, a main wing 4 is fixedly arranged at the shaft end of the motor transmission assembly 2, an auxiliary wing 3 is fixedly arranged at one opposite side of the motor transmission assembly 2 and the main wing 4, a fuselage protective shell 5 is fixedly arranged at one end of the installation framework 1 far away from the auxiliary wing 3, two opposite connecting frames 6 are detachably connected at one side of the fuselage protective shell 5 far away from the installation frameworks 1 through screws, two opposite installation blocks 7 are fixedly arranged at one ends of the two connecting frames 6 far away from the fuselage protective shell 5, a buffer plate 8 is arranged at one side of the installation blocks 7 far away from the connecting frames 6, a first shock-absorbing spring 9 is fixedly arranged between one opposite side of the buffer plate 8 and the installation blocks, a tail shaft 10 is fixedly arranged at one end of the mounting framework 1, which is perpendicular to the mounting direction of the motor transmission component 2, a rotating motor is arranged at one end of the tail shaft 10, which is far away from the mounting framework 1, a tail wing 11 is fixedly arranged at the motor shaft end of the rotating motor, a tail wing shield 12 matched with the tail wing 11 is fixedly arranged at the outer side of the circumference of the tail shaft 10, which is adjacent to the tail wing shield 12, an inclined support rod 13 is detachably connected with the outer side of the circumference of the tail shaft 10, a connecting rod 14 is arranged at one end of the inclined support rod 13, which is far away from the inclined support rod 13, and is fixedly connected with one side of the machine body protective shell 5, a chute matched with the connecting rod 14 is arranged at one end of the connecting rod 14, which is opposite to the inclined support rod 13, a buffer spring 15 is fixedly arranged between the outer sides of the connecting, the fixed installation roof beam 22 that is equipped with in one side that keeps away from installation skeleton 1 of anterior casing 16, one side that anterior casing 16 was kept away from to installation roof beam 22 is equipped with anticollision roof beam 17, fixed second damping spring 23 that is equipped with between the relative one side of anticollision roof beam 17 and installation roof beam 22, anterior casing 16 all is fixed with a support column 18 with the adjacent one side of installation roof beam 22, the one end that anterior casing 16 was kept away from to support column 18 is rotated through the pivot and is connected and be equipped with first rocking arm 19, the one end that support column 18 was kept away from to first rocking arm 19 is rotated through the pivot and is connected and be equipped with second rocking arm 20, be equipped with adjustable buffer 21 between the relative one side of.

The utility model discloses in, adjustable buffer 21 includes dead lever 211, the one end of dead lever 211 is equipped with spacing spout 216, the bottom of spacing spout 216 is equipped with adjusting bolt 212, adjusting bolt 212's the fixed piston head 213 that is equipped with and spacing spout 216 assorted that is equipped with of double-screw bolt afterbody, the one end that piston head 213 was kept away from to spacing spout 216 is equipped with spacing spout 216 assorted movable rod 214, fixed adjustable buffer spring 215 that is equipped with between the relative one end of movable rod 214 and piston head 213, the one end and the first rocking arm 19 fixed connection of dead lever 211 are kept away from to movable rod 214, second rocking arm 20 is equipped with fixed lug with the relative one side of adjusting bolt 212, one side of fixed lug is equipped with the screw hole with adjusting bolt 212 assorted, the appearance and the anterior casing 16 phase-match of anticollision roof beam 17, main wing 4 all is equipped with rather than the phase-.

Through the arrangement of the mounting beam 22, the anti-collision beam 17 and the second damping spring 23, the impact on the front part of the fuselage is buffered and is simultaneously dispersed to a part of the front shell 16, so that the impact is further relieved through the first rocker arm 19 and the second rocker arm 20, the appearance of the anti-collision beam 17 is matched with the front shell 16, and the cool feeling of the fuselage is enhanced; the impact from the upper part of the fuselage may be pressed down directly by the front housing 16, since the front housing 16 is connected to the internal heavy gear and motor, at which point the impact force will be transmitted through the front housing 16 to the first rocker arm 19 and the second rocker arm 20, and finally absorbed by the adjustable damping device 21; the descending vibrations of bottom can be absorbed by buffer board 8 and first damping spring 9 of undercarriage lower part, and tail department still is equipped with bearing diagonal pole 13 and damping spring 15 to and fin guard shield 12, can effectually prevent buckling of tail axle 10 and the damage of fin 11, wholly strengthened the shockproof and prevent falling the attribute of fuselage, simple structure, practicality are fit for promoting.

The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.

Claims

1. A remote control aircraft with a shock-absorbing falling-preventing structure comprises two opposite installation frameworks (1), and is characterized in that a motor transmission assembly (2) installed along a vertical direction is fixedly arranged between one opposite sides of the two installation frameworks (1), a main wing (4) is fixedly arranged at the shaft end of the motor transmission assembly (2), an auxiliary wing (3) is fixedly arranged on one opposite side of the motor transmission assembly (2) and the main wing (4), a fuselage protective shell (5) is fixedly arranged at one end, far away from the auxiliary wing (3), of the installation framework (1), one side, far away from the fuselage protective shell (5), of the fuselage protective shell (5) is detachably connected with two opposite connecting frames (6) through screws, two opposite installation blocks (7) are fixedly arranged at one end, far away from the fuselage protective shell (5), of the two connecting frames (6), one side of the installation block (7) far away from the connecting frame (6) is provided with a buffer plate (8), one side of the buffer plate (8) opposite to the installation block (7) is fixedly provided with a first damping spring (9), one end of the installation framework (1) vertical to the installation direction of the motor transmission assembly (2) is fixedly provided with a tail shaft (10), one end of the tail shaft (10) far away from the installation framework (1) is provided with a rotating motor, the motor shaft end of the rotating motor is fixedly provided with a tail wing (11), the circumference outer side of the tail wing (11) is fixedly provided with a tail wing shield (12) matched with the tail shaft, the circumference outer side of the tail shaft (10) adjacent to the tail wing shield (12) is provided with an inclined support rod (13) in a detachable connection manner through a screw, one end of the inclined support rod (13) far away from the tail shaft (10) is provided with a connecting rod (14), one end of the inclined supporting rod (13) and one side of the machine body protective shell (5) are fixedly connected through the connecting rod (14), one end of the connecting rod (14) opposite to the inclined supporting rod (13) is provided with a sliding groove matched with the sliding groove, a buffer spring (15) is fixedly arranged between the connecting rod (14) and the outer side of the circumference opposite to the inclined supporting rod (13), one side of the installation framework (1) far away from the tail shaft (10) is fixedly provided with a front shell (16), one side of the front shell (16) far away from the installation framework (1) is fixedly provided with an installation beam (22), one side of the installation beam (22) far away from the front shell (16) is provided with an anti-collision beam (17), one side of the anti-collision beam (17) opposite to the installation beam (22) is fixedly provided with a second damping spring (23), one side of the front shell (16) adjacent to the installation beam (22) is fixedly provided with a supporting column (18), the one end of keeping away from anterior casing (16) is rotated through the pivot to support column (18) and is connected and be equipped with first rocking arm (19), the one end that support column (18) were kept away from in first rocking arm (19) is rotated through the pivot and is connected and be equipped with second rocking arm (20), first rocking arm (19) with be equipped with adjustable buffer (21) between the relative one side of second rocking arm (20).

2. The telecontrolled aircraft with shock-absorbing and crash-proof structure according to claim 1, characterized in that the adjustable damping device (21) comprises a fixed rod (211), a limit sliding groove (216) is provided at one end of the fixed rod (211), an adjusting bolt (212) is provided at the bottom of the limit sliding groove (216), a piston head (213) matched with the limit sliding groove (216) is fixedly provided at the tail of the adjusting bolt (212), a movable rod (214) matched with the limit sliding groove (216) is provided at one end of the limit sliding groove (216) far away from the piston head (213), and an adjustable damping spring (215) is fixedly provided between the end of the movable rod (214) opposite to the piston head (213).

3. The remote control aircraft with the shock-absorbing and crash-proof structure as claimed in claim 2, wherein the end of the movable rod (214) far away from the fixed rod (211) is fixedly connected with the first rocker arm (19), the side of the second rocker arm (20) opposite to the adjusting bolt (212) is provided with a fixed lug, and one side of the fixed lug is provided with a threaded hole matched with the adjusting bolt (212).

4. The remote control aircraft with the shock absorption and falling prevention structure as claimed in claim 2, characterized in that the shape of the anti-collision beam (17) is matched with the front shell (16), and the outer sides of the circumferences of the connecting shafts of the main wing (4) and the auxiliary wing (3) are provided with matched protective bushings.