CN210125173U

CN210125173U - Folding aircraft model airplane

Info

Publication number: CN210125173U
Application number: CN201920449128.4U
Authority: CN
Inventors: 董怡璇
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-04-04
Filing date: 2019-04-04
Publication date: 2020-03-06
Anticipated expiration: 2029-04-04

Abstract

The utility model relates to a folding aircraft model, which comprises an aircraft body, a folding component and a locking part, wherein the folding component comprises a horn hinged on the side surface of the aircraft body, a screw arranged above the horn and a clamping part arranged at the outer end of the upper surface of the horn, a self-elastic component and a connecting component are arranged between the horn and the aircraft body, the locking part is clamped with the clamping part, the folding component is relatively folded at the two sides of the aircraft body, accomplish the locking through the cooperation relation between joint portion and the sticking department, effectively reduce the volume of model aeroplane and model ship aircraft in idle in-process, connect compactly, shared space when reducing to place and carry conveniently carries and deposits, in addition, break away from the cooperation relation between joint portion and the sticking department during the use, folding assembly is opened to user state, the simple operation, convenient to use automatically through the effect of bullet subassembly and coupling assembling.

Description

Folding aircraft model airplane

Technical Field

The utility model relates to an aeromodelling technical field especially relates to a foldable aircraft model aeroplane and model ship.

Background

The model airplane is usually a smaller model airplane manufactured according to the proportion of a reduced real airplane, is generally the same as a manned airplane, mainly comprises a fuselage, wings, propellers and a power system, is an unmanned airplane operated by utilizing a radio remote control device and a self-contained program control device, and can improve the pleasure of life for people. Because the aircraft body and the horn of traditional model aeroplane and model ship aircraft adopt integral type structure more, model aeroplane and model ship aircraft volume is great when not using, and it is placed and takes the time shared space great, inconvenient carrying during the trip.

SUMMERY OF THE UTILITY MODEL

The utility model aims to solve the technical problem that overcome exist among the prior art not enough, provide a foldable aircraft model aeroplane and model ship.

The utility model discloses a realize through following technical scheme:

the utility model provides a foldable aircraft model aeroplane and model ship, its characterized in that includes aircraft body, symmetry locate two sets of folding assembly of aircraft body both sides and locate the sticking department of aircraft body top, folding assembly is including articulating in the horn of aircraft body side, locate the screw of horn top and locate the joint portion of horn upper surface outer end, be equipped with between horn and the aircraft body from bullet subassembly and coupling assembling, sticking department both sides and joint portion joint.

According to the above technical scheme, preferably, the subassembly that plays certainly includes first connection ear, hinge and torsional spring, first connection ear rigid coupling is in aircraft body side, the horn is articulated in first connection ear department through the hinge with the aircraft body, the torsional spring has been cup jointed in the hinge outside, the torsional spring both ends are connected with horn and aircraft body lateral wall respectively.

According to the above technical scheme, preferably, coupling assembling is including locating first connecting rod and the second connecting rod between horn and the aircraft body, open aircraft body both sides has the standing groove, the horn middle part rigid coupling has the second engaging lug, it is articulated with first connecting rod one end in the standing groove, the first connecting rod other end is articulated with second connecting rod one end, the second connecting rod other end is articulated in second engaging lug department with the horn.

According to the above technical scheme, preferably, the clamping portion includes an arch support plate and a locking shaft, the arch support plate includes vertical plates symmetrically and fixedly connected to the upper surface of the boom and a connecting plate fixedly connected between the two vertical plates, two ends of the locking shaft are fixedly connected to the two vertical plates, and the locking shaft is clamped to the locking portion.

According to the above technical scheme, preferably, the sticking department locates the joint subassembly of the inside both sides of locking box including the locking box and the symmetry of locating aircraft body top, the relative joint portion of joint subassembly sets up, the joint subassembly includes back shaft, locking lever, bracing piece and spring, the back shaft rotates to be connected inside the locking box, the outer rigid coupling of back shaft has the locking lever, locking lever one end runs through the locking box lateral wall and bends down and form hook portion, the locking lever other end upwards extends and runs through the locking box upper surface, the inside rigid coupling of locking box has the bracing piece with locking lever middle part looks butt, the rigid coupling has the spring between the position that the locking lever is close to hook portion and the locking box bottom surface.

The utility model has the advantages that:

the folding components are folded on two sides of the aircraft body relatively, and locking is completed through the matching relation between the clamping parts and the locking parts, so that the volume of the model airplane aircraft in the idle process is effectively reduced, the connection is compact, the occupied space during placement and carrying is reduced, and the model airplane aircraft is convenient to carry and store; in addition, break away from the cooperation relation between joint portion and the sticking department during the use, folding assembly opens to the user state, simple operation, convenient to use automatically through the effect of bullet subassembly and coupling assembling certainly.

Drawings

Fig. 1 is a schematic top view of the present invention.

Fig. 2 is a schematic top view of the self-eject assembly of the present invention.

Fig. 3 is a schematic top view of the propeller part of the present invention.

Fig. 4 is a schematic perspective view of the joint portion of the present invention.

Fig. 5 is a front view of the locking portion of the present invention.

Fig. 6 is a side view of the locking portion of the present invention.

In the figure: 1. an arch support plate; 2. a paddle; 3. a horn; 4. a first connecting lug; 5. an aircraft body; 6. a second engaging lug; 7. a placement groove; 8. a second link; 9. a first link; 10. a rectangular escape port; 11. a protection pad; 12. locking the box body; 13. a torsion spring; 14. a motor; 15. rotating the plate; 16. a locking shaft; 17. a locking lever; 18. a support bar; 19. a hook portion; 20. a support shaft; 21. a spring; 22. the T-shaped relief port.

Detailed Description

In order to make those skilled in the art better understand the technical solution of the present invention, the present invention will be further described in detail with reference to the accompanying drawings and preferred embodiments.

As shown in the figure, the utility model comprises an aircraft body 5, two groups of folding components symmetrically arranged at the two sides of the aircraft body 5 and a locking part arranged above the aircraft body 5, the folding component comprises a horn 3 hinged on the side surface of the aircraft body 5, a propeller arranged above the horn 3 and a clamping part arranged at the outer end of the upper surface of the horn 3, a self-elastic component and a connecting component are arranged between the horn 3 and the aircraft body 5, two sides of the locking part are clamped with the clamping part, the propeller in this example comprises a motor 14 arranged above the horn 3, a rotating shaft connected with the motor 14, a rotating plate 15 fixedly connected with the outer wall of the rotating shaft and paddles 2 hinged at two ends of the rotating plate 15, in this example, the paddles 2 are tightly connected with the rotating plate 15, through manual 2 folding paddles, the size of the model airplane aircraft in the idle process is further reduced, and the folding effect is improved. The folding components are folded on two sides of the aircraft body 5 relatively, locking is completed through the matching relation between the clamping parts and the locking parts, the size of the model aircraft in the idle process is effectively reduced, connection is compact, the occupied space during placement and carrying is reduced, and the model aircraft is convenient to carry and store; in addition, break away from the cooperation relation between joint portion and the sticking department during the use, folding assembly opens to the user state, simple operation, convenient to use automatically through the effect of bullet subassembly and coupling assembling certainly.

According to the above embodiment, preferably, the self-elastic component includes the first connection lug 4, the hinge shaft and the torsion spring 13, the first connection lug 4 is fixedly connected to the side surface of the aircraft body 5, the horn 3 is hinged to the aircraft body 5 at the first connection lug 4 through the hinge shaft, in this example, the length of the horn 3 should be less than half of the distance between the two first connection lugs 4 on one side of the aircraft body 5, so as to ensure that the two horns 3 on one side of the aircraft body 5 are relatively folded without interference, the torsion spring 13 is sleeved on the outer side of the hinge shaft, two ends of the torsion spring 13 are respectively connected with the horn 3 and the side wall of the aircraft body 5, and the torsion spring 13 is in a natural state to drive the horn 3 to be unfolded outwards, so that the horn can be automatically opened to a use state, and the.

According to the above embodiment, preferably, coupling assembling is including locating first connecting rod 9 and second connecting rod 8 between horn 3 and aircraft body 5, open there are standing groove 7 in aircraft body 5 both sides, horn 3 middle part rigid coupling has second engaging lug 6, it is articulated with first connecting rod 9 one end in the standing groove 7, the first connecting rod 9 other end is articulated with second connecting rod 8 one end, the second connecting rod 8 other end is articulated in second engaging lug 6 department with horn 3, and first connecting rod 9, second connecting rod 8 and torsional spring 13 ensure that horn 3 keeps relatively fixed with aircraft body 5 under the expansion state to the interact of horn 3, ensure that aircraft model aeroplane and model ship is reliable and stable.

According to the above embodiment, preferably, the clamping portion includes the arched support plate 1 and the locking shaft 16, the arched support plate 1 includes the vertical plates symmetrically fixed to the upper surface of the aircraft arm 3 and the connecting plates fixed between the two vertical plates, two ends of the locking shaft 16 are fixed to the two vertical plates, the locking shaft 16 is clamped to the locking portion, and when the aircraft arm 3 moves to two sides of the aircraft body 5, the locking shaft 16 of the clamping portion is matched with the locking portion in a clamping manner to complete locking.

According to the above embodiment, preferably, the locking portion includes a locking box 12 disposed above the aircraft body 5 and clamping components symmetrically disposed on two sides inside the locking box 12, the clamping components are disposed opposite to the clamping portion, the clamping components include a support shaft 20, a locking rod 17, a support rod 18 and a spring 21, the support shaft 20 is rotatably connected inside the locking box 12, the locking rod 17 is fixedly connected outside the support shaft 20, one end of the locking rod 17 penetrates through a side wall of the locking box 12 and is bent downward to form a hook portion 19, the other end of the locking rod 17 extends upward and penetrates through an upper surface of the locking box 12, in this example, a T-shaped receding opening 22 is formed in a position of the side wall of the locking box 12 opposite to the hook portion 19, so as to ensure that the hook portion 19 is not interfered in a matching process with the locking shaft 16, a support rod 18 abutting against a middle portion of the locking rod, a spring 21 is fixedly connected between the position of the locking rod 17 close to the bent hook part 19 and the bottom surface of the locking box body 12, in this example, the upper part of the locking box body 12, which is opposite to the upper end of the locking rod 17, is provided with a rectangular relief opening 10 for an operator to pull the locking rod 17, in this example, the upper end of the locking rod 17 is provided with a protective pad 11 for increasing the friction between the locking rod 17 and the hand of the operator, so that the operator can pull the locking rod 17 in the process of opening the folded aircraft model to separate the locking rod 17 from the clamping fit with the locking shaft 16, when the arm 3 moves towards the two sides of the aircraft body 5, the locking shaft 16 is driven to move towards the bent hook part 19 of the locking rod 17, the locking shaft 16 is clamped in the bent hook part 19 of the locking rod 17 through the action of the spring 21, the aircraft model is folded, and when the aircraft model needs to be opened, the locking, the horn 3 receives the automatic service condition of opening to of the effect of bullet subassembly, simple operation.

The folding components are folded on two sides of the aircraft body 5 relatively, locking is completed through the matching relation between the clamping parts and the locking parts, the size of the model aircraft in the idle process is effectively reduced, connection is compact, the occupied space during placement and carrying is reduced, and the model aircraft is convenient to carry and store; in addition, break away from the cooperation relation between joint portion and the sticking department during the use, folding assembly opens to the user state, simple operation, convenient to use automatically through the effect of bullet subassembly and coupling assembling certainly.

The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.

Claims

1. The utility model provides a foldable aircraft model aeroplane and model ship, its characterized in that includes aircraft body, symmetry locate two sets of folding assembly of aircraft body both sides and locate the sticking department of aircraft body top, folding assembly is including articulating in the horn of aircraft body side, locate the screw of horn top and locate the joint portion of horn upper surface outer end, be equipped with between horn and the aircraft body from bullet subassembly and coupling assembling, sticking department both sides and joint portion joint.

2. The foldable aircraft model according to claim 1, wherein the self-eject assembly comprises a first connecting lug, a hinge shaft and a torsion spring, the first connecting lug is fixedly connected to the side of the aircraft body, the horn is hinged to the aircraft body at the first connecting lug through the hinge shaft, the torsion spring is sleeved outside the hinge shaft, and two ends of the torsion spring are respectively connected to the horn and the side wall of the aircraft body.

3. The foldable aircraft model according to claim 2, wherein the connecting assembly comprises a first connecting rod and a second connecting rod arranged between the horn and the aircraft body, the aircraft body is provided with a slot on both sides, the horn is fixedly connected with a second connecting lug in the middle, the slot is hinged with one end of the first connecting rod, the other end of the first connecting rod is hinged with one end of the second connecting rod, and the other end of the second connecting rod is hinged with the horn at the second connecting lug.

4. The foldable aircraft model according to claim 3, wherein the clamping portion comprises an arched support plate and a locking shaft, the arched support plate comprises vertical plates symmetrically fixed on the upper surface of the arm and a connecting plate fixed between the two vertical plates, two ends of the locking shaft are fixed on the two vertical plates, and the locking shaft is clamped with the locking portion.

5. The folding aircraft model according to claim 4, wherein the locking portion comprises a locking box body arranged above the aircraft body and clamping components symmetrically arranged on two sides inside the locking box body, the clamping components are arranged opposite to the clamping portions, each clamping component comprises a support shaft, a locking rod, a support rod and a spring, the support shaft is rotatably connected inside the locking box body, the locking rod is fixedly connected outside the support shaft, one end of the locking rod penetrates through the side wall of the locking box body and is bent downwards to form a hook portion, the other end of the locking rod extends upwards and penetrates through the upper surface of the locking box body, the support rod abutting against the middle portion of the locking rod is fixedly connected inside the locking box body, and the spring is fixedly connected between the position, close to the hook portion, of the locking rod and the bottom.