Airplane model

Abstract

The utility model discloses an airplane model. The airplane model comprises an airplane body, a seat cabin door and a locking module, a cabin and a mounting cavity which are adjacent are formed in the fuselage, and a mounting hole is formed in the cavity wall of the mounting cavity; the seat cabin door is arranged at a cabin opening of the cabin, the two opposite ends of the seat cabin door form a hinged end and a movable end respectively, the hinged end is hinged to the edge of the cabin opening of the cabin, and a locking hole is formed in the movable end; the locking module comprises a button and a locking piece, the button is contained in the mounting hole in a sliding mode, a certain distance is reserved between the button and the surface of the machine body, the locking piece is arranged in the mounting cavity in a sliding mode, part of the structure penetrates through the cavity wall of the mounting cavity and is inserted into the locking hole, and the button and the locking piece are connected through an inclined face structure. In the airplane model, the button is accommodated in the mounting hole, and a certain distance is reserved between the button and the surface of the fuselage, so that the airflow disturbance generated by the button in the flight process of the airplane model is smaller, and the flight state of the airplane model is more stable.

Description

Technical Field

[0001] The utility model relates to the technical field of model aircraft, in particular to an aircraft model. Background Art

[0002] With the development of science and technology and the improvement of living standards, more and more people are entering the model aircraft circle, and the simulation degree of aircraft models is getting higher and higher.

[0003] In the related art, in order to make the aircraft model more realistic, the aircraft model includes a fuselage and a cabin door, one end of the cabin door is hinged to the fuselage, and the other end of the cabin door is connected to the fuselage through a locking member, and the locking member is slidably provided on the fuselage. The user slides the locking member to make the locking member pass into or out of the locking hole of the cabin door to achieve locking or loosening of the cabin door.

[0004] In order to enable the user to drive the locking member more conveniently, the locking member is generally provided with a gripping portion protruding from the fuselage. However, the provision of the gripping portion will increase the airflow disturbance during the flight of the aircraft model and affect the normal flight of the aircraft model. Utility Model Content

[0005] The purpose of the utility model is to solve at least one of the technical problems existing in the prior art. The utility model provides an airplane model, which can reduce airflow disturbance during the flight of the airplane model while facilitating the user to drive a locking member.

[0006] The aircraft model provided according to the embodiment of the utility model includes a fuselage, a cockpit door and a locking module; an adjacent cockpit and an installation cavity are formed in the fuselage, and a cavity wall of the installation cavity is provided with an installation hole extending to the surface of the fuselage; the cockpit door is arranged at the hatch of the cockpit, and the opposite ends of the cockpit door respectively form a hinged end and a movable end, the hinged end is hinged to the hatch edge of the cockpit, and a locking hole is formed on the movable end; the locking module includes a button and a locking member, the button can be slidably accommodated in the installation hole, and a certain distance is spaced between the button and the surface of the fuselage, the locking member can be slidably arranged in the installation cavity, and a part of the structure passes through the cavity wall of the installation cavity and is inserted into the locking hole to fix the movable end, the button and the locking member are connected by an inclined structure, and when the button extends into the installation cavity under the action of external force, the button can drive the locking member to disengage from the locking hole through the inclined structure.

[0007] The airplane model described in the utility model has at least the following beneficial effects: in the airplane model of the present application, the button is accommodated in the mounting hole, the button and the locking piece are connected by an inclined structure, the locking piece is inserted into the locking hole of the movable end of the cabin door, when the cabin door needs to be opened, the staff presses the button, and then the button can drive the locking piece to disengage from the locking hole through the inclined structure, at this time, the movable end can rotate relative to the hinged end under the action of external force to realize the opening of the cabin door; because the button is accommodated in the mounting hole and there is a certain distance between the button and the surface of the fuselage, during the flight of the airplane model, the button causes less airflow disturbance during the flight of the airplane model, thereby making the flight state of the airplane model more stable.

[0008] According to the airplane model described in the embodiment of the utility model, the locking module also includes an elastic member, the opposite ends of the elastic member are respectively connected to the locking member and the cavity wall of the installation cavity, and the elastic member is used to provide elastic force to keep the locking member inserted into the locking hole.

[0009] According to the airplane model described in the embodiment of the utility model, the elastic member includes a spring, a mounting post is provided on the cavity wall of the mounting cavity, the mounting post is located on the side of the locking member away from the locking hole, and one end of the spring is sleeved on the mounting post.

[0010] According to the aircraft model described in the embodiment of the utility model, a locking member is provided with an abutment protrusion, a first abutment slope is formed on the abutment protrusion, a second abutment slope matched with the first abutment slope is formed at one end of the button close to the locking member, and the first abutment slope and the second abutment slope together constitute a slope structure.

[0011] According to the aircraft model described in the embodiment of the utility model, a first guide groove is provided on the hole wall of the mounting hole, and the extension direction of the first guide groove is parallel to the extension direction of the mounting hole. A first guide protrusion is provided on the surface of the button, and the first guide protrusion can be slidably penetrated into the first guide groove. The first guide protrusion abuts against the groove wall of the first guide groove to prevent the button from rotating relative to the fuselage.

[0012] According to the aircraft model described in the embodiment of the utility model, the hole wall of the mounting hole is provided with a plurality of guide ribs spaced apart along the circumference of the mounting hole, and a first guide groove is formed between any two adjacent guide ribs.

[0013] According to the airplane model described in the embodiment of the utility model, a plurality of friction protrusions are provided on one end of the button away from the installation cavity.

[0014] According to the airplane model described in the embodiment of the utility model, a second guide groove for guiding the locking member to approach or move away from the locking hole is provided on the cavity wall of the installation cavity, and a second guide protrusion is provided on the locking member, and the second guide protrusion can be slidably penetrated in the second guide groove.

[0015] According to the airplane model described in the embodiment of the utility model, a guide surface is provided at one end of the locking member close to the locking hole, and the guide surface is used to guide the locking member to be inserted into the locking hole.

[0016] According to the aircraft model described in the embodiment of the utility model, the fuselage includes a first sub-fuselage and a second sub-fuselage, the cockpit is arranged on the first sub-fuselage, the first sub-fuselage is also provided with a accommodating cavity, the second sub-fuselage is detachably arranged in the accommodating cavity, and the installation cavity is formed inside the second sub-fuselage.

[0017] Additional aspects and advantages of the present invention will be given in part in the following description, and in part will become apparent from the following description, or will be learned through the practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The utility model is further described below in conjunction with the accompanying drawings and embodiments;

[0019] Figure 1 This is a schematic diagram of the structure of an aircraft model according to an embodiment of the utility model;

[0020] Figure 2 for Figure 1 A schematic structural diagram of a second sub-fuselage of the aircraft model shown;

[0021] Figure 3 for Figure 2 a cross-sectional view of the second sub-fuselage shown;

[0022] Figure 4 This is a schematic structural diagram of a locking member according to an embodiment of the utility model;

[0023] Figure 5 The figure is a schematic diagram of the structure of a button according to an embodiment of the utility model.

[0024] Reference numerals:

[0025] Body 100; first sub-body 110; second sub-body 120; mounting cavity 121; mounting column 122; first guide groove 123; guide rib 124;

[0026] Cabin door 200; hinged end 210; movable end 220;

[0027] The locking module 300 , the button 310 , the second abutting inclined surface 311 , the first guide protrusion 312 , the friction protrusion 313 , the locking member 320 , the abutting protrusion 321 , the first abutting inclined surface 321 a , the second guide protrusion 322 , the guide surface 323 , and the elastic member 330 . DETAILED DESCRIPTION

[0028] This section will describe in detail the specific embodiments of the utility model. The preferred embodiments of the utility model are shown in the accompanying drawings. The purpose of the accompanying drawings is to supplement the description of the text part of the specification with graphics, so that people can intuitively and vividly understand each technical feature and the overall technical solution of the utility model, but it cannot be understood as a limitation on the protection scope of the utility model.

[0029] In the description of the present invention, it should be understood that descriptions involving orientation, such as up, down, front, back, left, right, etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0030] In the description of the present utility model, "several" means one or more, "more" means more than two, "greater than", "less than", "exceed" etc. are understood to exclude the number itself, and "above", "below", "within" etc. are understood to include the number itself. If there is a description of "first" or "second", it is only used for the purpose of distinguishing the technical features, and cannot be understood as indicating or implying the relative importance or implicitly indicating the number of the indicated technical features or implicitly indicating the order of the indicated technical features.

[0031] In the description of the present invention, unless otherwise clearly defined, terms such as setting, installing, connecting, etc. should be understood in a broad sense, and technicians in the relevant technical field can reasonably determine the specific meanings of the above terms in the present invention based on the specific content of the technical solution.

[0032] Reference below Figures 1 to 5 The aircraft model of the present application is described in detail.

[0033] refer to Figures 1 to 3 The aircraft model includes a fuselage 100, a cockpit door 200 and a locking module 300. The fuselage 100 is provided with a cockpit, and the cockpit door 200 is arranged at the hatch of the cockpit. The front end of the cockpit door 200 is a hinged end 210, and the hinged end 210 is hinged to the front edge of the hatch. The rear end of the cockpit door 200 is a movable end 220, and a locking hole is arranged on the movable end 220. Under the action of external force, the movable end 220 can rotate around the hinged end 210 to achieve the closing or opening of the hatch. The locking module 300 is arranged at the rear edge of the hatch. When the cockpit door 200 closes the hatch, the locking module 300 can be inserted into the locking hole of the movable end 220 to achieve the locking and fixing of the cockpit door 200.

[0034] In order to make the flight state of the aircraft model more stable, the fuselage 100 of the aircraft model is generally set to be streamlined to reduce the air resistance of the aircraft model during flight; and in order to facilitate the staff to operate the locking module 300, the locking module 300 needs to be in contact with the outside of the aircraft model. Accordingly, if the locking module 300 protrudes from the fuselage 100, at this time, the locking module 300 will generate a large airflow disturbance during the flight of the aircraft model, thereby affecting the stability of the aircraft model during flight.

[0035] Based on the above reasons, in some embodiments of the present invention, reference Figure 3 The locking module 300 includes a button 310 and a locking member 320. The fuselage 100 is provided with an installation cavity 121, which is located at the rear side of the cockpit. The upper cavity wall of the installation cavity 121 is provided with a mounting hole, which is connected to the outer side of the installation cavity 121. The locking member 320 is slidably arranged in the installation cavity 121 along the front-back direction, and the front end of the locking member 320 passes through the cavity wall of the installation cavity 121 and is inserted into the locking hole of the movable end 220. The button 310 is slidably accommodated in the mounting hole along the vertical direction, and the button 310 is spaced a certain distance from the surface of the fuselage 100. The lower end of the button 310 and the upper end of the locking member 320 are connected by an inclined structure.

[0036] Furthermore, when the cabin door 200 needs to be opened, the staff can press the button 310, and the button 310 can drive the locking piece 320 to slide backward through the inclined structure to disengage the locking piece 320 from the locking hole. At this time, the staff can drive the movable end 220 to rotate upward relative to the hinged end 210 to open the cabin door 200.

[0037] It can be understood that since the button 310 is accommodated in the mounting hole and there is a certain distance between the button 310 and the surface of the fuselage 100, during the flight of the aircraft model of this embodiment, the airflow can flow smoothly along the surface of the fuselage 100, reducing the impact of the button 310 on the airflow flowing through the surface of the fuselage 100, thereby making the aircraft model of this embodiment more stable during flight.

[0038] Specifically, refer to Figure 3 and Figure 4 An upwardly extending abutting protrusion 321 is provided at the upper end of the locking member 320, and a first abutting inclined surface 321a extending rearwardly and upwardly is provided on the abutting protrusion 321, and a second abutting inclined surface 311 extending forwardly and downwardly is provided at the lower end of the button 310, the first abutting inclined surface 321a abuts against the second abutting inclined surface 311, and the first abutting inclined surface 321a and the second abutting inclined surface 311 together constitute an inclined surface structure.

[0039] When the button 310 is pressed under the action of external force, the button 310 can drive the locking piece 320 to move backward through the inclined structure, so that the locking piece 320 disengages from the locking hole, making it easier for the staff to open the cabin door 200; and when the external force applied to the button 310 is removed, the locking piece 320 needs to slide forward to reset.

[0040] In order to realize the automatic reset of the locking member 320, in some embodiments of the present utility model, reference is made to Figure 3 The locking module 300 also includes an elastic member 330 , which is disposed on the rear side of the locking member 320 , the front end of the elastic member 330 is connected to the rear end of the locking member 320 , and the rear end of the elastic member 330 is connected to the cavity wall of the installation cavity 121 .

[0041] Furthermore, when the button 310 is pressed under the action of external force, the button 310 can drive the locking member 320 through the inclined structure to overcome the elastic force of the elastic member 330 and slide backward, so that the locking member 320 is disengaged from the locking hole. At this time, the cabin door 200 can be opened; when the external force applied to the button 310 is removed, under the elastic force of the elastic member 330, the locking member 320 can slide forward to be inserted into the locking hole to achieve the locking of the cabin door 200. In the process of the locking member 320 sliding forward, the locking member 320 can push the button 310 to move upward and reset through the inclined structure.

[0042] Specifically, refer to Figure 3 The elastic member 330 is a spring, and a mounting column 122 extending forward and backward is provided on the cavity wall of the mounting cavity 121 located on the rear side of the locking member 320. The rear end of the spring is sleeved on the mounting column 122 and connected to the rear side cavity wall of the mounting cavity 121.

[0043] It is understandable that in the process of the locking member 320 moving backward to compress the spring, in addition to being compressed in the front-to-back direction, the spring may bend left and right; by providing the mounting post 122, the mounting post 122 can guide the spring during the spring compression process to reduce the probability of the spring bending left and right.

[0044] Optionally, in other embodiments of the utility model, in addition to being arranged on the rear side of the locking member 320, the spring can also be arranged on the front side of the locking member 320. In this case, the spring is a tension spring, and the front end of the spring is connected to the front cavity wall of the installation cavity 121, and the rear end of the spring is connected to the front end of the locking member 320.

[0045] It should be noted that since the button 310 and the locking member 320 are connected by a slope structure, when the button 310 rotates relative to the hole wall of the mounting hole, the position of the second abutment slope 311 on the button 310 changes, making it difficult for the first abutment slope 321a to adapt to the second abutment slope 311.

[0046] In order to reduce the probability of the button 310 rotating relative to the hole wall of the mounting hole, in some embodiments of the present invention, reference Figure 3 and Figure 5 A vertically extending first guide groove 123 is provided on the hole wall of the mounting hole, and a vertically extending first guide protrusion 312 is provided on the circumferential surface of the button 310. The first guide protrusion 312 is slidably arranged in the first guide groove 123 along the vertical direction, and the first guide protrusion 312 abuts against the groove wall of the first guide groove 123 in the circumferential direction of the mounting hole.

[0047] Since the first guide protrusion 312 abuts against the groove wall of the first guide groove 123 in the circumferential direction of the mounting hole, the first guide protrusion 312 can cooperate with the first guide groove 123 to prevent the button 310 from rotating relative to the mounting hole, so that the posture of the first abutment bevel 321a can always be adapted to the second abutment bevel 311.

[0048] Specifically, refer to Figure 3 The hole wall of the mounting hole is provided with a plurality of guide ribs 124 spaced apart along the circumference of the mounting hole, and a first guide groove 123 is formed between any two adjacent guide ribs 124 .

[0049] In some embodiments of the present invention, in order to prevent the user's finger from slipping between the button 310 when the user presses the button 310, Figure 5 A plurality of friction protrusions 313 are provided on the end surface of the button 310 close to the surface of the body 100 .

[0050] It is understandable that the provision of the friction protrusion 313 can increase the friction coefficient between the button 310 and the user's hand, so as to reduce the probability of slippage between the user's hand and the button 310 when the user presses the button 310 .

[0051] In order to enable the locking member 320 to slide accurately in the front-to-back direction, in some embodiments of the present invention, Figure 4 A second guide groove (not shown in the figure) is provided on the cavity wall of the installation cavity 121 to guide the locking member 320 to slide forward and backward. The second guide groove extends along the front-to-back direction. A second guide protrusion 322 is provided on the locking member 320. The second guide protrusion 322 can be slidably inserted into the second guide groove along the front-to-back direction.

[0052] In order to enable the locking member 320 to be accurately inserted into the locking hole, in some embodiments of the present invention, reference Figure 4 A guide surface 323 is provided at the front end of the locking member 320 .

[0053] Furthermore, when the locking member 320 slides forward, the guide surface 323 can guide the locking member 320 to be inserted into the locking hole, so that the locking member 320 can be accurately inserted into the locking hole.

[0054] In order to facilitate the replacement of the locking module 300, in some embodiments of the present invention, refer to Figure 1 and Figure 2 The fuselage 100 includes a first sub-fuselage 110 and a second sub-fuselage 120 . The cockpit is arranged on the first sub-fuselage 110 . The first sub-fuselage 110 is also provided with a receiving cavity. The second sub-fuselage 120 is detachably arranged in the receiving cavity. The installation cavity 121 is formed inside the second sub-fuselage 120 .

[0055] Since the locking module 300 is disposed in the installation cavity 121 of the second sub-body 120, when the locking module 300 needs to be replaced, the staff can directly take out the second sub-body 120 from the accommodating cavity and then install a new second sub-body 120 in the accommodating cavity.

[0056] Although the embodiments of the present invention have been shown and described, those skilled in the art will appreciate that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the claims and their equivalents.

Claims

1. An airplane model, characterized in that: include: A fuselage, wherein a cockpit and an installation cavity are formed adjacent to each other, and a cavity wall of the installation cavity is provided with an installation hole extending to a surface of the fuselage; A cockpit door, arranged at the hatch of the cockpit, wherein two opposite ends of the cockpit door respectively form a hinged end and a movable end, the hinged end is hinged to the hatch edge of the cockpit, and a locking hole is formed on the movable end; A locking module, the locking module comprising a button and a locking piece, the button being slidably accommodated in the mounting hole, and the button being spaced a certain distance from the surface of the fuselage, the locking piece being slidably disposed in the mounting cavity, and a partial structure passing through the cavity wall of the mounting cavity and inserted into the locking hole to fix the movable end, the button and the locking piece being connected by an inclined structure, and when the button extends into the mounting cavity under the action of an external force, the button can drive the locking piece to disengage from the locking hole through the inclined structure.

2. An aircraft model according to claim 1, characterized in that: The locking module also includes an elastic member, the opposite ends of which are respectively connected to the locking member and the cavity wall of the installation cavity, and the elastic member is used to provide elastic force to keep the locking member inserted into the locking hole.

3. An aircraft model according to claim 2, characterized in that: The elastic member comprises a spring. A mounting post is arranged on the cavity wall of the mounting cavity. The mounting post is located on a side of the locking member away from the locking hole. One end of the spring is sleeved on the mounting post.

4. An aircraft model according to claim 1, characterized in that: The locking member is provided with an abutment protrusion, on which a first abutment slope is formed, and an end of the button close to the locking member is formed with a second abutment slope matched with the first abutment slope, and the first abutment slope and the second abutment slope together constitute the slope structure.

5. An aircraft model according to claim 1, characterized in that: A first guide groove is provided on the hole wall of the mounting hole, and an extension direction of the first guide groove is parallel to an extension direction of the mounting hole. A first guide protrusion is provided on the surface of the button, and the first guide protrusion can be slidably penetrated into the first guide groove. The first guide protrusion abuts against the groove wall of the first guide groove to prevent the button from rotating relative to the fuselage.

6. An aircraft model according to claim 5, characterized in that: The hole wall of the mounting hole is provided with a plurality of guide ribs spaced apart along the circumference of the mounting hole, and a first guide groove is formed between any two adjacent guide ribs.

7. An aircraft model according to claim 1, characterized in that: A plurality of friction protrusions are arranged on one end of the button away from the installation cavity.

8. An aircraft model according to claim 1, characterized in that: A second guide groove for guiding the locking member to approach or move away from the locking hole is provided on the cavity wall of the installation cavity, and a second guide protrusion is provided on the locking member. The second guide protrusion can be slidably penetrated in the second guide groove.

9. An aircraft model according to claim 1, characterized in that: A guide surface is provided at one end of the locking member close to the locking hole, and the guide surface is used to guide the locking member to be inserted into the locking hole.

10. An aircraft model according to claim 1, characterized in that: The fuselage includes a first sub-fuselage and a second sub-fuselage, the cockpit is arranged on the first sub-fuselage, the first sub-fuselage is also provided with a receiving cavity, the second sub-fuselage is detachably arranged in the receiving cavity, and the installation cavity is formed inside the second sub-fuselage.

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