Heavy-load airplane model

Abstract

The utility model discloses a heavy-load airplane model which comprises an airplane body, a nose is arranged at the front end of the airplane body, a tail is arranged at the rear end of the airplane body, wings are symmetrically arranged on the two sides of the airplane body, the wings are connected with the airplane body through wing quick-release structures, a vertical fin is arranged on the tail and connected with the tail through a C-shaped hook clamping piece, and the airplane body is of a rectangular structure and is hollow inside. The interior of the fuselage is divided into an upper cabin body and a lower cabin body by the top plate, the layer plates and the bottom plate. The aircraft is reasonable and ingenious in structural design, larger storage space can be formed in the aircraft body due to the rectangular aircraft body, articles in the aircraft body can be placed more orderly due to the separated design of the upper cabin body and the lower cabin body, meanwhile, the top plate, the layer plates and the bottom plate can be used for fixing the articles, and after the aircraft body is loaded, the gravity center of the aircraft can be always kept in the center of the aircraft body; and the pitching attitude of the aircraft in the flight process is more stable.

Description

Technical Field

[0001] The utility model relates to an airplane model, in particular to a large-load airplane model. Background Art

[0002] Aircraft models are often used in applications such as aerial photography. To ensure stable flight, existing aircraft models typically feature streamlined cabins. However, these cabins are relatively small, making it difficult to accommodate cargo when needed. This results in low cabin utilization and limits the scope of aircraft models' applications. Utility Model Content

[0003] In order to overcome the above-mentioned deficiencies, the present invention provides a large-load airplane model with a rationally planned cabin structure so that more articles can be loaded.

[0004] To achieve this purpose, the structure adopted by the present invention is: a large-load aircraft model, including a fuselage, a nose is arranged at the front end of the fuselage, a tail is arranged at the rear end, wings are symmetrically arranged on both sides of the fuselage, and a vertical tail is arranged on the tail. The fuselage is a rectangular structure, hollow inside the fuselage, a top plate is arranged on the top surface of the fuselage, a bottom plate is arranged on the bottom surface, and layer plates are arranged inside the fuselage to divide the interior of the fuselage into an upper cabin and a lower cabin.

[0005] The wings and the fuselage are connected to each other through a wing quick-release structure, which includes a first wing spar, a second wing spar and a buckle lock. The first wing spar and the second wing spar cross the fuselage, and the two ends of the first wing spar and the second wing spar are respectively inserted into the wings on both sides of the fuselage, and the contact surfaces of the wings and the fuselage are connected to each other through the buckle lock.

[0006] One or more C-shaped hooks are provided at the bottom of the vertical tail, and a connecting plate is provided on the tail corresponding to the C-shaped hook. A bayonet is provided on the connecting plate, and a convex block is provided at the end of the C-shaped hook, which cooperates with the bayonet.

[0007] A ejection hook is provided at the bottom of the nose.

[0008] The bottom of the tail is provided with a heat dissipation hole, which connects the fuselage and the nose.

[0009] Grooves are symmetrically arranged on both sides of the bottom of the tail.

[0010] The top plate and the bottom plate are connected to the fuselage through rotating buckles and limiting blocks.

[0011] The nose and tail are conical structures.

[0012] The beneficial effects are: the structural design of the utility model is reasonable and ingenious, the rectangular fuselage allows for a larger storage space inside the fuselage, the separation design of the upper cabin and the lower cabin allows for a more orderly placement of items inside, and at the same time, the top plate, the layer plates and the bottom plate can be used to fix items. After the fuselage is loaded, the center of gravity of the aircraft can always be maintained in the center of the fuselage, making the pitch attitude of the aircraft more stable during flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] The present invention will be described by way of examples with reference to the accompanying drawings, in which:

[0014] Figure 1 It is a three-dimensional structural diagram of the utility model;

[0015] Figure 2 This is a top view of the structure of the utility model;

[0016] Figure 3 This is a bottom-up structural diagram of the present utility model;

[0017] Figure 4 This is a cross-sectional structural diagram of the utility model;

[0018] Figure 5 This is a three-dimensional structural diagram of the utility model without a top plate;

[0019] Figure 6 It is a three-dimensional structural diagram of the fuselage and wing quick-detachable structure;

[0020] Figure 7 This is the structural diagram of the connection between the vertical tail and the tail;

[0021] Figure 8 is a three-dimensional structural diagram of the vertical tail;

[0022] Figure 9 1 is a sectional view of the tail of the aircraft. DETAILED DESCRIPTION

[0023] The present invention will now be described in further detail with reference to the accompanying drawings, which are simplified schematic diagrams that illustrate the basic structure of the present invention in a schematic manner.

[0024] In the description of the utility model, it should be noted that the terms "upper," "lower," "inner," "outer," "front end," "rear end," "both ends," "one end," "the other end," and the like, indicating positions or relationships, are based on the positions or relationships shown in the accompanying drawings and are intended solely to facilitate the description of the utility model and simplify the description. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on the utility model. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0025] In the description of the utility model, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "provided with," "connected," etc., should be understood in a broad sense. For example, "connected" can mean a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or it can be internal communication between two components; a fixed connection can be welding or gluing. Those skilled in the art will understand the specific meanings of the above terms in this utility model based on specific circumstances.

[0026] like Figure 1-Figure 5 The heavy-load aircraft model shown includes a fuselage 1, a nose 3 is provided at the front end of the fuselage 1, a tail 4 is provided at the rear end, wings 2 are symmetrically provided on both sides of the fuselage 1, and a vertical tail 5 is provided on the tail 4. The fuselage 1 is a rectangular structure, and the fuselage 1 is hollow. The rectangular structure is regular, and the fuselage 1 can accommodate more items. The nose 3 and the tail 4 are conical rectifier structures to reduce air resistance and ensure aircraft performance. A top plate 6 is provided on the top surface of the fuselage 1, and a bottom plate 11 is provided on the bottom surface. A layer plate 17 is provided inside the fuselage 1 to divide the interior of the fuselage 1 into an upper cabin 15 and a lower cabin 16. The top plate 6, the bottom plate 11 and the layer plate 17 are of a composite plate structure. The composite plate structure is lightweight. At the same time, the items carried in the fuselage 1 can be fixed to the composite plate by screws and other fixings to prevent the items from moving during flight.

[0027] The wings 2 and the fuselage 1 are connected to each other via a wing quick-release structure. Figure 6As shown, the wing quick-release structure includes a first spar 18, a second spar 19, and a latch 10. The first spar 18 and the second spar 19 are two hollow tubes. The first spar 18 and the second spar 19 are parallel to each other and cross the fuselage 1. The first and second spar 18 and 19 extend beyond the fuselage 1 at both ends. The portions extending beyond the fuselage 1 are inserted into the wings 2 on either side of the fuselage 1, maintaining balance between the wings 2 on both sides. The latch 10 is provided at the contact surface between the wings 2 and the fuselage 1, which enables quick installation and removal of the wings 2 from the fuselage 1. The first spar 18 is located near the front end of the fuselage 1, while the second spar 19 is located near the rear end of the fuselage 1. The first spar 18 is shorter than the second spar 19, providing balanced support for the wings 2. The first and second spar 18 and 19 are carbon fiber tubes with a higher specific strength than steel tubes. This ensures the support strength of the wings 2 while reducing the overall weight. The side of the wing 2 that contacts the fuselage 1 is provided with a connecting plate, with through-holes corresponding to the first and second wing spars 18 and 19. The hasp lock 10 is connected to the fixing plate, which is bonded to the fuselage 1. The fixing plate is also provided with through-holes that communicate with the upper and lower cabins 15 and 16, facilitating the routing of cables for equipment such as the steering gear.

[0028] like Figure 7-Figure 8As shown, the bottom of the vertical fin 5 is provided with one or more C-shaped hooks 52. A connecting plate 41 is provided on the tail 4 to correspond to the C-shaped hooks 52. The connecting plate 41 is provided with a bayonet. A protrusion is provided at the end of the C-shaped hook 52. The protrusion cooperates with the bayonet to enable quick assembly and disassembly of the vertical fin 5 and the tail 4. The C-shaped hook 52 is connected to the bottom of the vertical fin 5 via a clamping block 51. The clamping block 51 is a long, concave-shaped slot in longitudinal section. The clamping block 51 opens upward to clamp the bottom of the vertical fin 5. The bottom of the clamping block 51 is connected to the C-shaped hook 52, with the open end of the C-shaped hook 52 facing the end of the tail 4. A groove 42 is provided at the top of the tail 4, and the bottom of the vertical fin 5 is positioned within the groove 42. The bottom of the vertical fin 5 is inclined, with one end higher than the other. The end away from the end of the tail 4 is at a higher level, while the end closer to the end of the tail 4 is at a lower level. The connection between the bottom of the vertical fin 5 and the clamping block 51 is a protrusion that protrudes from the vertical fin 5, its length and width smaller than the bottom surface. During quick assembly, the vertical fin 5 is inserted into the groove 42, and the C-shaped hook 52 is engaged with the latch on the connecting plate 41 by movement, connecting the vertical fin 5 to the tail 4. Because the opening of the C-shaped hook 52 faces the end of the tail 4, and the front end of the tail 4 faces the wind during flight, the engagement between the C-shaped hook 52 and the connecting plate 41 remains secure. Because one end of the bottom of the vertical fin 5 is higher than the other, the tail 4 provides support when the vertical fin 5 is subjected to wind pressure, ensuring a secure connection. Furthermore, because the C-shaped hook 51 and the connecting plate 41 are hidden in the groove 42, they are less susceptible to external forces and are protected from airflow, further ensuring a secure connection. The quick-release structural components can be made of relatively lightweight materials such as plastic, placing less strain on the tail 4 and preventing the model's center of gravity from shifting during flight. When the vertical tail 5 of the model aircraft can be assembled with a stable and reliable quick-disassembly structure, the vertical tail can be separated from the aircraft body for transportation, thereby reducing the space occupied by the entire aircraft and facilitating transportation.

[0029] The bottom of the nose 3 is provided with an ejection hook 12, which facilitates the ejection takeoff of the aircraft.

[0030] The bottom of the tail 4 is provided with a heat dissipation hole 13, which connects the fuselage 1 and the nose 3. There is a through hole at the nose 3 that penetrates the fuselage 1. During flight, air flows in from the nose 3 and flows out from the heat dissipation hole 13. In this process, on the one hand, the lift of the aircraft can be enhanced, and on the other hand, the heat generated by the operation of various equipment in the fuselage 1 can be taken away, thereby ensuring the stable operation of the equipment.

[0031] The bottom of the tail 4 is symmetrically provided with grooves 14 , which are grasping grooves and can facilitate gripping when throwing the aircraft.

[0032] The top plate 6 and the bottom plate 11 are connected to the fuselage 1 through a rotating buckle 9 and a limit block 7. The rotating buckle 9 and the limit block 7 are arranged on the fuselage 1 at both ends of the top plate 6 or the bottom plate 11. The rotating buckle 9 is a long strip of plate connected to the fuselage 1 through a rotating shaft. The limit block 7 is provided with a plurality of protrusions, and the top plate 6 or the bottom plate 11 is provided with through holes corresponding to the protrusions. During installation, the through holes at one end of the top plate 6 or the bottom plate 11 are engaged with the protrusions on the limit block 7, and the rotating buckle 9 at the other end is rotated to make it engage with the connected top plate 6 or bottom plate.

[0033] The structural design of the utility model is reasonable and ingenious. The rectangular fuselage allows for a larger storage space inside the fuselage. The separation design of the upper cabin and the lower cabin allows for a more orderly placement of items inside. At the same time, the top plate, the layer plates, and the bottom plate can be used to fix items. After the fuselage is loaded, the center of gravity of the aircraft can always be maintained in the center of the fuselage, making the pitch attitude of the aircraft more stable during flight.

[0034] The above description is based on the present invention. Based on the above description, relevant personnel can make various changes and modifications without departing from the technical concept of this utility model. The technical scope of this utility model is not limited to the content of the specification. Its technical scope must be determined according to the scope of the claims.

Claims

1. A heavy-load aircraft model, comprising a fuselage (1), a nose (3) being provided at the front end of the fuselage (1), a tail (4) being provided at the rear end, wings (2) being symmetrically provided on both sides of the fuselage (1), and a vertical tail (5) being provided on the tail (4), characterized in that: The fuselage (1) is a rectangular structure, and the interior of the fuselage (1) is hollow. A top plate (6) is provided on the top surface of the fuselage (1), and a bottom plate (11) is provided on the bottom surface. A layer plate (17) is provided inside the fuselage (1) to separate the interior of the fuselage (1) into an upper cabin (15) and a lower cabin (16).

2. The heavy-load aircraft model according to claim 1, characterized in that: The wings (2) and the fuselage (1) are connected to each other via a wing quick-detach structure, wherein the wing quick-detach structure comprises a first wing spar (18), a second wing spar (19) and a snap lock (10), wherein the first wing spar (18) and the second wing spar (19) pass through the fuselage (1), and the two ends of the first wing spar (18) and the second wing spar (19) are respectively inserted into the wings (2) on both sides of the fuselage (1), and the contact surfaces of the wings (2) and the fuselage (1) are connected to each other via the snap lock (10).

3. The heavy-load aircraft model according to claim 1, characterized in that: The bottom of the vertical tail (5) is provided with one or more C-shaped hooks (52), the tail (4) is provided with a connecting plate (41) corresponding to the C-shaped hooks (52), the connecting plate (41) is provided with a bayonet, and the end of the C-shaped hook (52) is provided with a protrusion, which cooperates with the bayonet.

4. The heavy-load aircraft model according to claim 1, characterized in that: The bottom of the machine head (3) is provided with an ejection hook (12).

5. The heavy-load aircraft model according to claim 1, characterized in that: The bottom of the tail (4) is provided with a heat dissipation hole (13), and the heat dissipation hole (13) is connected with the fuselage (1) and the head (3).

6. The heavy-load aircraft model according to claim 1, characterized in that: Grooves (14) are symmetrically arranged on both sides of the bottom of the tail (4).

7. The heavy-load aircraft model according to claim 1, characterized in that: The top plate (6) and the bottom plate (11) are connected to the body (1) via a rotating buckle (9) and a limiting block (7).

8. The heavy-load aircraft model according to claim 1, characterized in that: The nose (3) and tail (4) are of conical structure.

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