CN211987090U

CN211987090U - Model airplane with flight landing buffering function

Info

Publication number: CN211987090U
Application number: CN202020467985.XU
Authority: CN
Inventors: 赵传生
Original assignee: Huai'an Tiandao Technology Innovation Co ltd
Current assignee: Huai'an Tiandao Technology Innovation Co ltd
Priority date: 2020-04-02
Filing date: 2020-04-02
Publication date: 2020-11-24
Anticipated expiration: 2030-04-02

Abstract

The utility model discloses a model airplane with flying landing buffering function in the technical field of model airplanes, which comprises a model airplane body, a connecting rod, a U-shaped damping piece and the like, wherein the U-shaped damping piece comprises symmetrically arranged butt-joint rods, the U-shaped rods are integrally connected between the two butt-joint rods, the openings of the two symmetrically arranged U-shaped damping pieces are opposite, one end of the upper butt-joint rod, which is far away from the U-shaped rods, is connected with the connecting rod, one end of the lower butt-joint rod, which is far away from the U-shaped rods, is fixedly connected with one end of a connecting column, the U-shaped rods can deform under the action of external force, the other ends of the two connecting columns on the butt-joint rods at the same side are fixedly connected with a lifting rod, when the model airplane is subjected to large impact force in the landing process, the U-shaped rods forming the U-shaped damping pieces are subjected to bending deformation under the external force, then the deformation is recovered, thereby protecting the model airplane body.

Description

Model airplane with flight landing buffering function

Technical Field

The utility model relates to a model aeroplane and model ship aircraft technical field, concrete field is a model aeroplane and model ship aircraft with flight descending buffer function.

Background

The aviation model is originally used for popularizing aviation knowledge and cultivating aviation science talents, and along with the development of science and technology, the aviation models of a plurality of specialties are simplified and improved, so that the model is safe, simple in operation, interesting and playable, and more suitable for requirements of aviation model enthusiasts.

The existing model airplane has a fixed structure of an undercarriage and lacks of a buffer mechanism, so that when the model airplane lands, if the speed and angle control is not good, the impact force generated by the model airplane exceeds the buffer absorption capacity of the undercarriage, and the model airplane is damaged by the impact force.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a model aeroplane and model ship aircraft with flight landing buffer function to solve the problem of mentioning in the background art.

In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides a model aeroplane and model ship aircraft with buffering function is descended in flight, includes model aeroplane and model ship aircraft body, the fuselage lower extreme symmetry fixedly connected with connecting rod of model aeroplane and model ship aircraft body, the lower extreme symmetry of connecting rod is provided with U-shaped damping piece, U-shaped damping piece is including the butt joint pole that the symmetry set up, two integrated into one piece is connected with the U-shaped pole between the butt joint pole, and the symmetry sets up two the opening part of U-shaped damping piece is relative, the upside the butt joint pole just keeps away from the one end of U-shaped pole with the connecting rod is connected, the downside the butt joint pole just keeps away from the one end of the one end fixedly connected with spliced pole of U-shaped pole is located the homonymy two on the butt joint pole the.

Preferably, the opening part of U-shaped damping piece is provided with the damping reinforcement, the damping reinforcement is including the spread groove that the symmetry set up, two the spread groove respectively with the downside butt joint pole fixed connection, two fixedly connected with spring between the spread groove.

Preferably, a guide cylinder is fixedly connected to one side wall of each of the two connecting grooves, the guide cylinder is located outside the spring, and the total length of the two guide cylinders is smaller than that of the spring.

Preferably, the connecting pieces are symmetrically and fixedly connected to the side wall of the connecting rod, the connecting pieces are provided with movable holes, the side wall of the U-shaped vibration damping piece is fixedly connected with one end of a movable column matched with the movable holes, and the other end of the movable column penetrates through the movable holes and is fixedly connected with a limiting piece.

Preferably, the lifting rod is an aluminum alloy lifting rod.

Compared with the prior art, the beneficial effects of the utility model are that: a model airplane with flying landing buffering function is characterized in that a U-shaped vibration damping piece is connected to the lower side of a model airplane body through a connecting rod, the U-shaped vibration damping piece comprises symmetrically arranged butt-joint rods, a U-shaped rod is integrally connected between the two butt-joint rods, the openings of the symmetrically arranged two U-shaped vibration damping pieces are opposite, one end of the butt-joint rod at the upper side, which is far away from the U-shaped rod, is connected with the connecting rod, one end of the butt-joint rod at the lower side, which is far away from the U-shaped rod, is fixedly connected with one end of a connecting column, the U-shaped rod can deform under the action of external force, the other ends of the two connecting columns on the butt-joint rods at the same side are fixedly connected with a lifting rod, when the model airplane is subjected to large impact force in the landing process, the U-shaped rod forming the U-shaped vibration damping piece is subjected to, thereby protecting the model airplane body.

Furthermore, the opening part of U-shaped damping piece is provided with the damping reinforcement, and the damping reinforcement is including the spread groove that the symmetry set up, two spread grooves respectively with the butt joint pole fixed connection of last downside, fixedly connected with spring between two spread grooves. The damping reinforcement plays supplementary damping effect to the model aeroplane and model ship aircraft, when the model aeroplane and model ship aircraft received great impact force at the landing in-process, component U-shaped pole takes place bending deformation because of receiving external force in the U-shaped damping piece, then resume deformation, consume partial impact force in this process, thereby protect the model aeroplane and model ship aircraft body, the damping reinforcement is receiving the extruded in-process of U-shaped damping piece, impel the spring to take place deformation, then the spring resumes deformation, consume partial impact force in this process, thereby further protection model aeroplane and model ship aircraft body.

Furthermore, a guide cylinder is fixedly connected to one side wall opposite to the two connecting grooves, the guide cylinder is located on the outer side of the spring, and the total length of the two guide cylinders is smaller than that of the spring. The opposite ends of the two guide cylinders are not contacted, and the guide cylinders are arranged to enable the spring to stretch and contract along the vertical direction in the deformation process.

Furthermore, the connecting pieces are symmetrically and fixedly connected to the side walls of the connecting rods, movable holes are formed in the connecting pieces, one ends of movable columns matched with the movable holes are fixedly connected to the side walls of the U-shaped vibration damping pieces, and the other ends of the movable columns penetrate through the movable holes and are fixedly connected with limiting pieces. The setting of connection piece is used for connecting U-shaped damping piece on the connecting rod, makes through the setting of activity post and activity hole, provides certain deformation space for the upper end of U-shaped damping piece.

Drawings

FIG. 1 is a schematic view of the main structure of the present invention;

FIG. 2 is an enlarged schematic view of the present invention at A in FIG. 1;

fig. 3 is an enlarged schematic view of the point B in fig. 1 according to the present invention.

In the figure: 1-model airplane body, 2-connecting rod, 3-U-shaped vibration damping piece, 301-butt joint rod, 302-U-shaped rod, 4-connecting column, 5-lifting rod, 6-vibration damping reinforcing piece, 601-connecting groove, 602-spring, 603-guide cylinder, 7-connecting piece, 8-movable hole and 9-movable column.

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.

The description of the directions (up, down, left, right, front, and back) is made with reference to the structure shown in fig. 1 of the drawings attached to the specification, but the practical direction of the present invention is not limited thereto.

Example (b):

referring to fig. 1-3, the present invention provides a technical solution: referring to fig. 1, a model airplane with a flying landing buffering function comprises a model airplane body 1, wherein connecting rods 2 are symmetrically and fixedly connected to the lower end of the airplane body of the model airplane body 1, U-shaped vibration dampers 3 are symmetrically arranged at the lower ends of the connecting rods 2, the connecting rods 2 are used for being connected with the U-shaped vibration dampers 3, each U-shaped vibration damper 3 comprises symmetrically arranged butt-joint rods 301, a U-shaped rod 302 is integrally connected between the two butt-joint rods 301, the openings of the two symmetrically arranged U-shaped vibration dampers 3 are opposite, one end of the upper butt-joint rod 301, which is far away from the U-shaped rod 302, is connected with the connecting rod 2, one end of the lower butt-joint rod 301, which is far away from the U-shaped rod 302, is fixedly connected with one end of a connecting column 4, the U-shaped rod 302 can deform under the action of external force, and the other ends of the two connecting columns 4 on the butt-joint rods 301 at the same side are, when the model airplane is subjected to a large impact force in the landing process, the U-shaped rod 302 which is a component in the U-shaped vibration damping part 3 is subjected to bending deformation due to external force and then recovers deformation, and partial impact force is consumed in the process, so that the model airplane body 1 is protected.

Referring to fig. 2, specifically, a damping reinforcing member 6 is disposed at an opening of the U-shaped damping member 3, the damping reinforcing member 6 includes symmetrically disposed connecting slots 601, the two connecting slots 601 are respectively and fixedly connected to the upper and lower connecting rods 301, and a spring 602 is fixedly connected between the two connecting slots 601. The damping reinforcement 6 plays a role in assisting damping of the model airplane, when the model airplane is subjected to a large impact force in the landing process, the U-shaped rod 302 in the U-shaped damping part 3 is subjected to bending deformation due to external force and then recovers deformation, partial impact force is consumed in the process, so that the model airplane body 1 is protected, the damping reinforcement 6 promotes the spring 602 to deform in the extrusion process of the U-shaped damping part 3, then the spring 602 recovers deformation, partial impact force is consumed in the process, and the model airplane body 1 is further protected.

Referring to fig. 2, specifically, a guide cylinder 603 is fixedly connected to a side wall of each of the two connecting slots 601, the guide cylinder 603 is located outside the spring 602, and a total length of the two guide cylinders 603 is smaller than a length of the spring 602. The opposite ends of the two guide cylinders 603 are not in contact, and the guide cylinders 603 are arranged to make the spring 602 extend and contract in the vertical direction during the deformation process.

Referring to fig. 3, specifically, the connecting pieces 7 are symmetrically and fixedly connected to the side wall of the connecting rod 2, the connecting pieces 7 are provided with movable holes 8, one end of a movable column 9 used in cooperation with the movable holes 8 is fixedly connected to the side wall of the U-shaped vibration damping member 3, and the other end of the movable column 9 penetrates through the movable holes 8 and is fixedly connected with a limiting piece. The connecting piece 7 is used for connecting the U-shaped vibration damping piece 3 to the connecting rod 2, and a certain deformation space is provided for the upper end of the U-shaped vibration damping piece 3 through the arrangement of the movable column 9 and the movable hole 8.

Specifically, the lifting bar 5 is an aluminum alloy lifting bar.

The working principle is as follows: the connecting rod 2 is used for connecting the U-shaped vibration damping piece 3, the U-shaped vibration damping piece 3 comprises two butt joint rods 301 which are symmetrically arranged, a U-shaped rod 302 is integrally connected between the two butt joint rods 301, the openings of the two symmetrically arranged U-shaped vibration reduction pieces 3 are opposite, one end of the butt joint rod 301 at the upper side, which is far away from the U-shaped rod 302, is connected with the connecting rod 2, one end of the butt joint rod 301 at the lower side, which is far away from the U-shaped rod 302, is fixedly connected with one end of the connecting column 4, the U-shaped rod 302 can deform under the action of external force, the other ends of the two connecting columns 4 on the butt joint rod 301 at the same side are fixedly connected with the lifting rod 5, when the model airplane is subjected to a large impact force in the landing process, the U-shaped rod 302 of the U-shaped vibration damping part 3 is subjected to bending deformation due to external force, then, the deformation is recovered, and part of the impact force is consumed in the process, thereby protecting the model airplane body 1.

In the description of the present invention, unless expressly stated or limited otherwise, the terms "disposed," "mounted," "connected," and "fixed" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral part; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

The utility model discloses the standard parts that use all can purchase from the market, and dysmorphism piece all can be customized according to the record of description and attached drawing.

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. The utility model provides a model aeroplane and model ship aircraft with flight landing buffer function, includes model aeroplane and model ship aircraft body (1), its characterized in that: fuselage lower extreme symmetry fixedly connected with connecting rod (2) of model aeroplane and model ship aircraft body (1), the lower extreme symmetry of connecting rod (2) is provided with U-shaped damping piece (3), U-shaped damping piece (3) are including butt joint pole (301) that the symmetry set up, two integrated into one piece is connected with U-shaped pole (302) between butt joint pole (301), and the symmetry sets up two the opening part of U-shaped damping piece (3) is relative, the upside butt joint pole (301) and keep away from the one end of U-shaped pole (302) with connecting rod (2) are connected, the downside butt joint pole (301) and keep away from the one end fixedly connected with spliced pole (4) of U-shaped pole (302), be located the homonymy two on butt joint pole (301 the other end of spliced pole (4) all with lifting rod (5) fixed connection.

2. The model airplane with the flight landing buffering function according to claim 1, wherein: the opening part of U-shaped damping piece (3) is provided with damping reinforcement (6), damping reinforcement (6) are including connecting groove (601) that the symmetry set up, two connecting groove (601) respectively with the downside butt joint pole (301) fixed connection, two fixedly connected with spring (602) between connecting groove (601).

3. The model airplane with the flight landing buffering function according to claim 2, wherein: two fixedly connected with guide cylinder (603) on the relative lateral wall of spread groove (601), guide cylinder (603) are located the outward appearance of spring (602), two the total length of guide cylinder (603) is less than the length of spring (602).

4. The model airplane with the flight landing buffering function according to claim 1, wherein: the connecting rod is characterized in that connecting pieces (7) are symmetrically and fixedly connected to the side wall of the connecting rod (2), movable holes (8) are formed in the connecting pieces (7), one end of a movable column (9) matched with the movable holes (8) is fixedly connected to the side wall of the U-shaped vibration damping piece (3), and the other end of the movable column (9) penetrates through the movable holes (8) and is fixedly connected with limiting pieces.

5. The model airplane with the flight landing buffering function according to claim 1, wherein: the lifting rod (5) is an aluminum alloy lifting rod.