CN217311923U

CN217311923U - Model aircraft with anticollision function

Info

Publication number: CN217311923U
Application number: CN202123324004.XU
Authority: CN
Inventors: 肖泽枫; 王铁勇; 吴家星; 马留飞
Original assignee: Beijing Qizhi Ronghe Education Technology Co ltd
Current assignee: Beijing Qizhi Ronghe Education Technology Co ltd
Priority date: 2021-12-28
Filing date: 2021-12-28
Publication date: 2022-08-30
Anticipated expiration: 2031-12-28

Abstract

The utility model provides a model airplane with an anti-collision function, which belongs to the technical field of aviation models and comprises an airplane main body; the two wings are fixedly connected to the circumferential surface of the airplane main body; the airplane wheel is arranged at the lower end of the wing; and the buffer mechanisms are arranged on one side of the wings, the buffer mechanisms are provided with four groups, each group of buffer mechanisms comprises an arc-shaped plate, a circular groove, a stabilizing strip, a rack, a torsion spring, a sleeve and two long grooves, when the wings are impacted, small fragments can be generated to cause the safety of people to be injured, the airplane is damaged to cause the economic loss of people, and at the moment, the impact force of the impact can be buffered through the buffer mechanisms to reduce the probability of damage and breakage of the wings, so that the use safety of people is improved.

Description

Model aircraft with anticollision function

Technical Field

The utility model belongs to the technical field of the aeromodelling, concretely relates to model aircraft with anticollision function.

Background

The model airplane is a generic term for various aircraft models. It includes model airplanes and other model airplanes. The aviation model activity arouses strong interest from the beginning, and is flourishing for hundreds of years, mainly because it plays an important role in the development of aviation industry and the cultivation of scientific and technical talents.

In prior art, child plays model aircraft or controls model aircraft when flying, makes model aircraft take place to drop or the striking easily, because of the wing is wide big, thinner causes the damage easily, if child is comparatively close to then, the piece of production causes bodily injury and economic loss easily, has endangered child safety when using.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a model aircraft with anticollision function aims at solving the problem that the model wing among the prior art receives the striking and produces the damage easily.

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

a model aircraft having a collision avoidance function, comprising:

an aircraft body;

the two wings are fixedly connected to the circumferential surface of the airplane main body;

the airplane wheel is arranged at the lower end of the wing; and

the buffering mechanism is arranged at one end of the wing and provided with four groups, each group of buffering mechanism comprises an arc-shaped plate, a circular groove, a stabilizing strip, a gear, a rack, a torsion spring, a sleeve and two long grooves, the two long grooves are formed in the circumferential surface of the wing, the circular groove is formed in one side, close to the two long grooves, the torsion spring is fixedly connected to the upper inner wall of the circular groove, the sleeve is rotatably connected to the upper inner wall of the circular groove, the gear is fixedly connected to the circumferential surface of the sleeve, one end of the torsion spring is fixedly connected with the circumferential inner wall of the sleeve, the rack and the stabilizing strip are respectively connected to the inner walls of the two long grooves in a sliding mode, the rack is meshed with the gear, and the arc-shaped plate is fixedly connected to one ends of the rack and the stabilizing strip.

As an optimized scheme of the utility model, still include supplementary damper, supplementary damper is equipped with four groups, and the supplementary damper of every group all includes slide bar, side spring, two places the piece, two hollow blocks and two connecting rods, two place the equal fixed connection of piece in the circumference surface of wing, slide bar fixed connection is in two place the one end that the piece is close to mutually, the circumference surface of slide bar, two are located to the side spring housing the equal sliding connection of hollow block in the circumference surface of slide bar, and the both ends fixed connection that leans on near-end and side spring mutually of two hollow blocks, two the connecting rod all through hinge difference swing joint in the one end of two hollow blocks, two the one end of connecting rod all through hinge swing joint in the one end of arc.

As an optimized scheme, it is a plurality of the spacing groove has all been seted up to the upper end of elongated slot, the equal fixedly connected with stopper in upper end of rack and stabilizer bar, two the equal sliding connection of stopper is in the inner wall of spacing groove.

As a preferred scheme of the utility model, one of them two lower springs of lower extreme fixedly connected with of wing, two the equal fixed connection of lower spring is in the upper end of aircraft wheel, two telescopic links of lower extreme fixedly connected with of wing, two the equal fixed connection of telescopic link is in the upper end of aircraft wheel, two the circumference surface of telescopic link is located to lower spring cover respectively.

As a preferred scheme of the utility model, the lower inner wall fixedly connected with circle axle of elongated slot, the circumferential surface of circle axle is located to the torque spring cover.

As an optimized scheme, the threaded hole is seted up to the lower extreme of aircraft main part, the circumference inner wall threaded connection of screw hole has places the platform.

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

1. in the scheme, when the wing receives the striking, small fragments can be generated to cause the safety of people to be injured, the airplane is damaged, the economic loss of people is also caused, the impact force of the striking can be buffered through the buffering mechanism at the moment, the probability of damage and breakage of the wing is reduced, and the use safety of people is improved.

2. In this scheme, when the aircraft below received the striking, probably received the impact force of below and lead to the aircraft to receive the impact force that the aircraft below received through aircraft below fixed connection's lower spring this moment and cushion, reduce the injury that the aircraft received.

3. In this scheme, when wanting to place the aircraft, can be through the threaded connection of screw hole with place the platform for putting of aircraft with place more stably, difficult crooked damage that causes, also convenient to detach uses when people want to use.

Drawings

The accompanying drawings are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention, and together with the description serve to explain the invention and not to limit the invention. In the drawings:

fig. 1 is a front perspective view of the present invention;

fig. 2 is a first perspective sectional view of the present invention;

fig. 3 is a partial enlarged view of a portion a in fig. 2 according to the present invention;

fig. 4 is a second perspective sectional view of the present invention;

fig. 5 is a partially enlarged view of the utility model at B in fig. 4;

fig. 6 is a third perspective sectional view of the present invention.

In the figure: 1. an aircraft body; 2. an airfoil; 3. an aircraft wheel; 4. an arc-shaped plate; 5. a circular groove; 6. a long groove; 7. a circular shaft; 8. a torsion spring; 9. a sleeve; 10. a gear; 11. a rack; 12. a stabilizing strip; 13. placing the blocks; 14. a slide bar; 15. a hollow block; 16. a side spring; 17. a connecting rod; 18. a limiting groove; 19. a limiting block; 20. a telescopic rod; 21. a lower spring; 22. a placing table; 23. a threaded bore.

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.

Example 1

Referring to fig. 1-6, the present invention provides the following technical solutions:

a model aircraft having a collision avoidance function, comprising:

an aircraft body 1;

the two wings 2 are fixedly connected to the circumferential surface of the airplane body 1;

the airplane wheel 3 is arranged at the lower end of the wing 2; and

the buffering mechanism is arranged on one side of the wing 2 and provided with four groups, each group of buffering mechanism comprises an arc-shaped plate 4, a circular groove 5, a stabilizing strip 12, a gear 10, a rack 11, a torsion spring 8, a sleeve 9 and two long grooves 6, the two long grooves 6 are arranged on the circumferential surface of the wing 2, the circular groove 5 is arranged on one side, close to the two long grooves 6, of the circular groove 5, the torsion spring 8 is fixedly connected to the upper inner wall of the circular groove 5, the sleeve 9 is rotatably connected to the upper inner wall of the circular groove 5, the gear 10 is fixedly connected to the circumferential surface of the sleeve 9, one end of the torsion spring 8 is fixedly connected with the circumferential inner wall of the sleeve 9, the rack 11 and the stabilizing strip 12 are respectively and slidably connected to the inner walls of the two long grooves 6, the rack 11 and the gear 10 are mutually meshed, and the arc-shaped plate 4 is fixedly connected to one ends of the rack 11 and the stabilizing strip 12.

In the embodiment of the present invention, when a child plays with an airplane, an accident occurs, and when the wing 2 is impacted, the arc 4 is impacted, and then the arc 4 pushes the rack 11 and the stabilizing strip 12, which are fixedly connected with the arc, inward and slide into the elongated slot 6, and at the same time, the rack 11 is engaged with the gear 10, and then the rack 11 drives the gear 10 to rotate around the sleeve 9, and the gear 10 drives the torsion spring 8 to rotate, and at this time, because the torsion spring 8 has an elastic force, the torsion spring 8 stores and buffers the impact force applied to the arc 4, after the impact force is reduced, the impact force is converted into an elastic force by the storage of the torsion spring 8, and drives the gear 10 to rotate around the sleeve 9, and is engaged with the rack 11 through the gear 10, and the gear 10 pushes the rack 11 to slide out of the elongated slot 6 to reset, and the impact force applied to the airplane is offset, the damage to the airplane is reduced, the service life of the airplane is prolonged, the possibility that the injury to users is caused by the fragments when the airplane is damaged is reduced, the economic loss of the users is prevented, and the safety of the users in use is improved.

Referring to fig. 3 specifically, the aircraft wing structure further comprises four groups of auxiliary damping mechanisms, each group of auxiliary damping mechanisms comprises a sliding rod 14, a side spring 16, two placing blocks 13, two hollow blocks 15 and two connecting rods 17, the two placing blocks 13 are both fixedly connected to the circumferential surface of the wing 2, the sliding rod 14 is fixedly connected to one end, close to the two placing blocks 13, of the two placing blocks 13, the side spring 16 is sleeved on the circumferential surface of the sliding rod 14, the two hollow blocks 15 are both slidably connected to the circumferential surface of the sliding rod 14, the near ends of the two hollow blocks 15 are fixedly connected to the two ends of the side spring 16, the two connecting rods 17 are both movably hinged to one ends of the two hollow blocks 15 through hinge shafts, and one ends of the two connecting rods 17 are both movably hinged to one end of the arc-shaped plate 4 through hinge shafts.

In this embodiment: when the arc 4 receives the striking, the arc 4 drives two connecting rods 17 through the hinge and carries out the angle deflection, so two connecting rods 17 drive two hollow blocks 15 through the hinge and slide and be close to extrusion side spring 16 each other on the circumference surface of slide bar 14, receive the impact force to the arc 4 because of side spring 16 self elastic force and have carried out conversion and absorption, the impact force that the arc 4 received has further been offset, 16 absorb the back at the impact force that the arc 4 received at the side spring, convert into self elastic force and impel two hollow blocks 15 to remove to opposite direction, two hollow blocks 15 promote connecting rod 17 simultaneously and carry out the angle deflection, two connecting rods 17 promote arc 4 and reset.

Specifically, referring to fig. 5, the upper ends of the plurality of elongated slots 6 are respectively provided with a limiting groove 18, the upper ends of the rack 11 and the stabilizing strip 12 are respectively and fixedly connected with limiting blocks 19, and the two limiting blocks 19 are respectively and slidably connected to the inner wall of the limiting groove 18.

In this embodiment: when the rack 11 and the stabilizing strip 12 slide in the long groove 6, the limiting block 19 is driven to slide in the limiting groove 18, so that the rack 11 and the stabilizing strip 12 are more stable when sliding, the rack 11 and the stabilizing strip 12 are not easy to slip off, and the rack 11 and the gear 10 are more tightly meshed.

Referring to fig. 4, the lower end of one wing 2 is fixedly connected with two lower springs 21, the two lower springs 21 are both fixedly connected to the upper end of the aircraft wheel 3, the lower end of the wing 2 is fixedly connected with two telescopic rods 20, the two telescopic rods 20 are both fixedly connected to the upper end of the aircraft wheel 3, and the two lower springs 21 are respectively sleeved on the circumferential surface of the telescopic rods 20.

In this embodiment: when the aircraft receives the striking, probably receive the impact force from the below, lead to the aircraft to receive the injury, can reduce the aircraft from the impact force of below through lower spring 21 this moment, can also carry on spacingly through telescopic link 20 to lower spring 21's motion, reduce lower spring 21 roll, make lower spring 21's removal more stable, make lower spring 21 be difficult for elastic deformation to have reduced because of lower spring 21 rocks the possibility that leads to lower spring 21 buffering effect to reduce.

Specifically, referring to fig. 3, a circular shaft 7 is fixedly connected to a lower inner wall of the elongated slot 6, and a torsion spring 8 is sleeved on a circumferential surface of the circular shaft 7.

In this embodiment: probably because of the impact force influence horizontal shaking produces crooked when torsion spring 8 uses for torsion spring 8 is when buffering, and the buffering effect reduces and torsion spring 8 self receives the damage, can use round axle 7 to carry out spacing messenger round axle 7 to torsion spring 8 motion this moment, uses more stably to be difficult for crooked.

Specifically, referring to fig. 6, a threaded hole 23 is formed at the lower end of the aircraft body 1, and a placing table 22 is connected to the circumferential inner wall of the threaded hole 23 in a threaded manner.

In this embodiment: when people place the aircraft, can fix the exhibition with the aircraft through the screw-thread fit of screw hole 23 and placing platform 22 for it is not fragile to place more stably.

The utility model discloses a theory of operation and use flow: when the side surface of the airplane is impacted, the arc-shaped plate 4 can be extruded, the arc-shaped plate 4 drives the stabilizing strip 12 and the rack 11 to slide towards the inner elongated slot 6, the rack 11 drives the gear 10 to rotate by taking the sleeve 9 as an axis, the gear 10 drives the torsion spring 8 to rotate, the impact force on the arc-shaped plate 4 is buffered by the elastic force of the torsion spring 8, after the received impact force is counteracted, the buffer mechanism is pushed to reset by the elastic force of the torsion spring 8, and the damage to the airplane, caused by the offset of the impact force, is reduced.

Finally, it should be noted that: 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 described in the foregoing embodiments, or equivalents may be substituted for elements thereof. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A model aircraft with collision avoidance functionality, comprising:

an aircraft body (1);

the two wings (2) are fixedly connected to the circumferential surface of the airplane main body (1);

the airplane wheel (3) is arranged at the lower end of the wing (2); and

the buffer mechanism is arranged on one side of the wing (2), four groups of buffer mechanisms are arranged, each group of buffer mechanism comprises an arc-shaped plate (4), a circular groove (5), a stabilizing strip (12), a rack (11), a torsion spring (8), a gear (10), a sleeve (9) and two long grooves (6), the two long grooves (6) are arranged on the circumferential surface of the wing (2), the circular groove (5) is arranged on one side, close to the two long grooves (6), of the two long grooves (6), the torsion spring (8) is fixedly connected to the upper inner wall of the circular groove (5), the sleeve (9) is rotatably connected to the upper inner wall of the circular groove (5), the gear (10) is fixedly connected to the circumferential surface of the sleeve (9), one end of the torsion spring (8) is fixedly connected with the circumferential inner wall of the sleeve (9), and the rack (11) and the stabilizing strip (12) are respectively connected to the inner walls of the two long grooves (6) in a sliding manner, the rack (11) is meshed with the gear (10), and the arc-shaped plate (4) is fixedly connected to one ends of the rack (11) and the stabilizing strip (12).

2. A model aircraft with collision avoidance functionality according to claim 1, wherein: the airplane wing vibration damper further comprises four groups of auxiliary damping mechanisms, each group of auxiliary damping mechanism comprises a sliding rod (14), a side spring (16), two placing blocks (13), two hollow blocks (15) and two connecting rods (17), the two placing blocks (13) are fixedly connected to one circumferential surface of the wing (2), the sliding rod (14) is fixedly connected with one end of the two placing blocks (13) close to each other, the side spring (16) is sleeved on the circumferential surface of the sliding rod (14), the two hollow blocks (15) are both connected to the circumferential surface of the sliding rod (14) in a sliding manner, and the near ends of the two hollow blocks (15) are fixedly connected with the two ends of the side spring (16), the two connecting rods (17) are respectively and movably hinged at one ends of the two hollow blocks (15) through hinge shafts, and one ends of the two connecting rods (17) are respectively and movably hinged at one end of the arc-shaped plate (4) through hinge shafts.

3. A model aircraft with collision avoidance function according to claim 2, wherein: limiting grooves (18) are formed in the upper ends of the long grooves (6), limiting blocks (19) are fixedly connected to the upper ends of the racks (11) and the stabilizing strips (12), and the two limiting blocks (19) are connected to the inner walls of the limiting grooves (18) in a sliding mode.

4. A model aircraft with collision avoidance function as claimed in claim 3, wherein: one of them two lower spring (21) of lower extreme fixedly connected with of wing (2), two the equal fixed connection in the upper end of aircraft wheel (3) of lower spring (21), two telescopic link (20) of lower extreme fixedly connected with of wing (2), two the equal fixed connection in the upper end of aircraft wheel (3) of telescopic link (20), two the circumference surface of telescopic link (20) is located respectively to lower spring (21).

5. A model aircraft with collision avoidance function as claimed in claim 4, wherein: the lower inner wall of the long groove (6) is fixedly connected with a round shaft (7), and the torsion spring (8) is sleeved on the circumferential surface of the round shaft (7).

6. A model aircraft with collision avoidance function as claimed in claim 5, wherein: the lower end of the airplane main body (1) is provided with a threaded hole (23), and the circumferential inner wall of the threaded hole (23) is in threaded connection with a placing table (22).