CN210473048U

CN210473048U - Model airplane remote control aircraft with small wind resistance

Info

Publication number: CN210473048U
Application number: CN201921167716.5U
Authority: CN
Inventors: 赵传生; 沈扬
Original assignee: Huai'an Tiandao Technology Innovation Co Ltd
Current assignee: Huai'an Tiandao Technology Innovation Co Ltd
Priority date: 2019-07-23
Filing date: 2019-07-23
Publication date: 2020-05-08
Anticipated expiration: 2029-07-23

Abstract

The utility model discloses a model aeroplane and model ship remote control aircraft that windage is less, including fuselage, aircraft nose, the left end face of fuselage and the central point that is in the terminal surface put and offer fluted one, and the right side groove face welding of recess one has the spring, and the spring is kept away from the one end of recess right side groove face and is located the internal weld of recess one and has a linking piece one. This model airplane remote control aircraft that windage is less, through the connection of spring and recess one and link up the piece one, and link up the connection of piece one and connector etc. for when aircraft nose loads onto the wall, the spring can play a cushioning effect, reduce the probability that the aircraft nose is bumped out, the restriction displacement of the relative fuselage of telescopic link restriction aircraft nose through four directions, through the threaded connection of the thread groove one of seting up on linking up the piece one and the connector and the threaded connection of the thread groove two of seting up on linking up the piece two and telescopic link make aircraft nose and fuselage can part, when the aircraft nose is damaged because of the striking, only with changing the aircraft nose, the replacement cost is reduced and the resource has been practiced thrift.

Description

Model airplane remote control aircraft with small wind resistance

Technical Field

The utility model relates to a model aeroplane and model ship remote control aircraft technical field specifically is a model aeroplane and model ship remote control aircraft that windage is less.

Background

The model airplane remote control plane with small wind resistance in the current market often has the situation that the head of the model airplane collides with a wall due to improper operation of children, and the head of the model airplane remote control plane is easy to damage when the head of the model airplane remote control plane collides with the body of the model airplane because the head of the model airplane remote control plane is directly not provided with a buffering structure, so that the whole model airplane remote control plane can only be replaced again under the condition that the head of the model airplane remote control plane is damaged, the replacement cost is high, and resources are wasted.

SUMMERY OF THE UTILITY MODEL

Solves the technical problem

Not enough to prior art, the utility model provides a less model aeroplane and model ship remote control aircraft of windage possesses linking department of aircraft nose and fuselage and has buffer performance, reduces replacement cost, resources are saved's advantage, has solved aircraft nose and fuselage and has not buffer performance, the problem of replacement cost height, extravagant resource.

Technical scheme

For the purpose that there is buffer performance, reduction replacement cost, resources are saved in the linking department of realizing above-mentioned aircraft nose and fuselage, the utility model provides a following technical scheme: a model airplane remote control aircraft with smaller wind resistance comprises an aircraft body and an aircraft nose, wherein a first groove is formed in the center position of the left end face of the aircraft body and on the end face of the aircraft nose, a spring is welded on the right groove face of the first groove, one end of the spring, which is far away from the right groove face of the first groove, is welded inside the first groove, a first thread groove is formed in the end face of the first groove, which is far away from the spring, a first screw is arranged on the right side of the end face base, which is far away from one side of the first thread groove, of the first connection block, a second groove is formed in the upper outer wall face, the lower outer wall face, the left side of the second groove, is provided with a second screw, the second connection block is fixedly connected to the right groove face of the second groove through the second screw, the terminal surface that links up two keep away from two right side groove faces of recess of piece has seted up thread groove two, the inner wall screw thread fixedly connected with telescopic link of thread groove two, the outer wall about the aircraft nose just is located the positive left side of the two recess that each face corresponds and sets up fluted three respectively, the telescopic end of telescopic link just is located the inside welding of recess three and has the fixed plate, one side that the three groove faces of recess were kept away from to the fixed plate is equipped with screw three, the fixed plate passes through three fixed connection of screw at the groove face with three vertically recesses of screw three.

Preferably, the cylindrical surface of the connector is provided with a thread, the thread is arranged from right to left, and the length of the thread is greater than that of the thread groove in the left-right direction.

Preferably, the cylindrical surface of the telescopic rod is provided with threads from right to left, and the size of the thread surface of the telescopic rod is matched with that of the thread groove.

Preferably, the number of the second grooves and the number of the third grooves are four, and the corresponding surfaces are symmetrical in pairs.

Preferably, the number of the second connecting block, the second thread groove, the telescopic rod and the fixing plate is four.

Preferably, the number of the third screws is sixteen, and four screws are fixed on each fixing plate.

Has the beneficial effects.

This model airplane remote control aircraft that windage is less, through the connection of spring and recess one and link up the piece one, and link up the connection of piece one and connector etc. for when aircraft nose loads onto the wall, the spring can play a cushioning effect, reduce the probability that the aircraft nose is bumped out, the restriction displacement of the relative fuselage of telescopic link restriction aircraft nose through four directions, through the threaded connection of the thread groove one of seting up on linking up the piece one and the connector and the threaded connection of the thread groove two of seting up on linking up the piece two and telescopic link make aircraft nose and fuselage can part, when the aircraft nose is damaged because of the striking, only with changing the aircraft nose, the replacement cost is reduced and the resource has been practiced thrift.

Drawings

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

fig. 2 is a bottom view of the structure of the present invention;

fig. 3 is an enlarged view of a position a in the structure 1 of the present invention.

In the figure: the machine comprises a machine body 1, a machine head 2, a groove I3, a spring 4, a connecting block I5, a thread groove I6, a connecting head 7, a screw I8, a groove II 9, a connecting block II 10, a screw II 11, a thread groove II 12, a telescopic rod 13, a groove III 14, a fixing plate 15 and a screw III 16.

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.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", and the like, indicate the orientation or positional relationship indicated based on the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.

In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," and "fixed" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally formed; 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 according to specific situations by those skilled in the art.

Referring to fig. 1-3, the present invention provides a technical solution: a model airplane remote control aircraft with smaller wind resistance comprises an aircraft body 1 and an aircraft nose 2, wherein a groove I3 is formed in the left end face of the aircraft body 1 and in the center of the end face, a spring 4 is welded on the right groove face of the groove I3, the spring 4, a connecting block I5 and a connector 7 are connected through the groove I3, the spring 4 plays a role of buffering when the aircraft nose 2 is installed on a wall, the probability that the aircraft nose 2 is damaged by collision is reduced, the connecting block I5 is welded inside the groove I3 and at one end, far away from the right groove face of the groove I3, of the spring 4, the connecting block I5 is welded inside the groove I3, the aircraft nose 2 and the aircraft body 1 can be separated through threaded connection of a thread groove I6 and the connector 7 formed in the connecting block I5 and threaded connection of a thread groove II 12 and a telescopic rod 13 formed in the connecting block II 10, so that the aircraft nose 2 is only replaced by the aircraft nose 2, the replacement cost is reduced and resources are saved, a first thread groove 6 is formed in the end face, on one side, away from the spring 4, of a first connecting block 5, a connecting head 7 is fixedly connected to the inner wall of the first thread groove 6 through threads, the cylindrical surface of the connecting head 7 is provided with threads, the thread forming direction is formed from right to left, the length of the threads is larger than that of the first thread groove 6 in the left-right direction, a first screw 8 is arranged on the right side of a base of the end face, away from the first thread groove 6, of the connecting head 7, the connecting head 7 is fixedly connected to the central position of the right end face of the machine head 2 through the first screw 8, two grooves 9 are formed in the upper, lower, left and right outer wall faces of the machine body 1 respectively, the number of the two grooves 9 and the three grooves 14 is four, the corresponding faces are symmetrical in pairs, a second connecting block 10 is arranged on the right side groove, a second screw 11 is arranged on the left of the base of the second joining block 10, the second joining block 10 is fixedly connected to the right groove face of the second groove 9 through the second screw 11, a second thread groove 12 is formed in the end face, far away from the right groove face of the second groove 9, of the second joining block 10, a telescopic rod 13 is fixedly connected to the inner wall threads of the second thread groove 12, the telescopic rods 13 in four directions limit the limited displacement of the head 2 relative to the machine body 1, so that the head 2 cannot shake relative to the machine body 1, threads are formed in the cylindrical surface of the telescopic rod 13 from right to left, the size of the thread face of the telescopic rod 13 is matched with the second thread groove 12, three grooves 14 are formed in the right left of the corresponding second grooves 9 on the upper, lower, left and right outer wall surfaces of the head 2 respectively, a fixing plate 15 is welded in the telescopic end of the telescopic rod 13 and located in the third grooves 14, a third screw 16 is arranged on one, four fixing plates 15 are fixed on each fixing plate 15, and the fixing plates 15 are fixedly connected to the groove surfaces of the grooves three 14 perpendicular to the screws three 16 through screws three 16.

The working principle is as follows: during the use, through recess one 3 and spring 4 and linking piece one 5 be connected, spring 4 and linking piece one 5 and connector 7, make aircraft nose 2 and fuselage 1 have the performance of buffering, the restriction displacement of aircraft nose 2 relative fuselage 1 is restricted through the telescopic link 13 of four directions, make aircraft nose 2 can not rock relative fuselage 1, threaded connection through threaded groove one 6 of seting up on linking piece one 5 and connector 7 and threaded connection of seting up on linking piece two 10 and telescopic link 13 make aircraft nose 2 and fuselage 1 can part, thereby when aircraft nose 2 because the striking damages, only need change aircraft nose 2, the replacement cost is reduced and the resource has been practiced thrift.

It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

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 less model aeroplane and model ship remote control aircraft of windage, includes fuselage (1), aircraft nose (2), its characterized in that: the left end face of the machine body (1) and the central position at the end face are provided with a first groove (3), the right groove face of the first groove (3) is welded with a spring (4), one end, far away from the first groove (3), of the spring (4) is welded inside the first groove (3), a first connecting block (5) is welded inside the first groove (3), one side end face, far away from the spring (4), of the first connecting block (5) is provided with a first thread groove (6), the inner wall thread of the first thread groove (6) is fixedly connected with a connector (7), the right side, far away from the end face base on one side of the first thread groove (6), of the connector (7) is provided with a first screw (8), the connector (7) is fixedly connected to the central position of the right end face of the machine head (2) through the first screw (8), the upper outer wall face, the lower outer wall face, the left wall face and the right wall face of the machine body (1) are respectively provided with a, a second screw (11) is arranged on the left of the second joining block (10) base, the second joining block (10) is fixedly connected to the right groove surface of the second groove (9) through the second screw (11), the end surface of the second connecting block (10) far away from the right groove surface of the second groove (9) is provided with a second thread groove (12), the inner wall of the second thread groove (12) is fixedly connected with a telescopic rod (13) through threads, the upper, lower, left and right outer wall surfaces of the machine head (2) and right and left sides of the corresponding grooves II (9) on each surface are respectively provided with a groove III (14), a fixing plate (15) is welded at the telescopic end of the telescopic rod (13) and positioned in the groove III (14), a third screw (16) is arranged on one side of the fixing plate (15) far away from the groove surface of the third groove (14), the fixing plate (15) is fixedly connected to the groove surface of the groove III (14) perpendicular to the screw III (16) through a screw III (16).

2. The remote control airplane with a small wind resistance model airplane as claimed in claim 1, wherein: the cylindrical surface of the connector (7) is provided with threads, the thread forming direction is from right to left, and the length of the threads is greater than that of the thread groove I (6) in the left-right direction.

3. The remote control airplane with a small wind resistance model airplane as claimed in claim 1, wherein: the cylindrical surface of the telescopic rod (13) is provided with threads from right to left, and the size of the thread surface of the telescopic rod (13) is matched with that of the second thread groove (12).

4. The remote control airplane with a small wind resistance model airplane as claimed in claim 1, wherein: the number of the second grooves (9) and the number of the third grooves (14) are four, and the corresponding surfaces are symmetrical in pairs.

5. The remote control airplane with a small wind resistance model airplane as claimed in claim 1, wherein: the number of the second joining block (10), the second thread groove (12), the telescopic rod (13) and the fixing plate (15) is four.

6. The remote control airplane with a small wind resistance model airplane as claimed in claim 1, wherein: the number of the screws three (16) is sixteen, and four screws are fixed on each fixing plate (15).