A remote-controlled aircraft model with a stable and easily dismantled fuselage

Abstract

The present invention discloses a remote-controlled aircraft model with a stable and easily disassembled fuselage, comprising a main body, the main body being formed by combining and splicing a right half fuselage and a left half fuselage, a driving mechanism being provided at the front end of the nose of the main body, the driving mechanism comprising a motor, a mounting seat, and an engine cover, the engine cover being buckled with the main body, the mounting seat being provided with a concave cavity, and the motor being fixedly installed at the concave cavity of the mounting seat. The present invention adopts a method of clamping the limiting front flange portions of the right half fuselage and the left half fuselage by the mounting seat and the engine cover, and combined with the special structural design of the mounting seat, the mounting seat is subjected to a more balanced force in the fuselage and forms a stable integral structure with the entire fuselage. Compared with the existing method of embedding and pasting the motor in the fuselage with glue, the present invention does not need to destroy the internal mechanism of the fuselage, and the motor can be disassembled and taken out, and the operation is simple and convenient.

Description

Technical Field

[0001] The invention relates to the technical field of aviation models, and in particular to a remote-controlled aircraft model with a stable and easily disassembled fuselage. Background Art

[0002] Aircraft model is a general term for various aircraft models, including various model aircraft such as model airplanes. In order to facilitate low-altitude flight, its technical main body is mostly made of lightweight foam material. During flight, the motor of the aircraft model drives the propeller at its front end to rotate. In existing aircraft models, the motor inside is mostly glued and fixed inside the fuselage. The Chinese invention patent with authorization announcement number CN217908960U discloses a structure for quick-detachment of the main wing of a small aircraft, which includes a fuselage, a main wing mounted on the fuselage, and a main wing bracket, and the motor is inlaid and pasted to the inner ends of the main wing by glue. Although the motor is conveniently installed and fixed by inlaying and pasting the motor in the main wing with glue, when the motor needs to be replaced and repaired, the internal structure of the fuselage needs to be destroyed to remove the motor stuck in the fuselage. To this end, we propose a remote-controlled aircraft model with a stable and easy-to-disassemble fuselage. Summary of the invention

[0003] The purpose of the present invention is to overcome the deficiencies of the prior art and provide a remote-controlled aircraft model with a stable and easily dismantled fuselage.

[0004] To achieve the above-mentioned purpose, the present invention adopts the following technical scheme: a remote-controlled aircraft model with a stable and easily disassembled fuselage, comprising a main fuselage, wherein the main fuselage is formed by merging and splicing a right half fuselage and a left half fuselage, a driving mechanism is provided at the front end of the nose of the main fuselage, the driving mechanism comprises a motor, a mounting seat, and an engine cover, the engine cover is buckled with the main body, the mounting seat is provided with a concave cavity, and the motor is fixedly installed at the concave cavity of the mounting seat.

[0005] To further explain, the left and right sides of the mounting seat are provided with an insertion rod portion, the arc-shaped plate surface extending from the concave cavity mouth of the mounting seat is connected to the insertion rod portions on both sides, the arc-shaped plate surface is provided with a clamping plate portion below the insertion rod portion, the right half fuselage and the left half fuselage are both provided with a limiting front flange portion, the rear side of the limiting front flange portion is provided with a concave cavity portion for installing the mounting seat, the concave cavity portion is provided with a card slot for clamping with the clamping plate portion of the mounting seat, the hood is connected to the mounting seat, and the limiting front flange portion is clamped between the mounting seat and the hood.

[0006] It is further explained that the inner walls of the right half fuselage and the left half fuselage are provided with a support rod groove for accommodating a positioning support rod, the positioning support rod is plugged into the insertion rod portion at the mounting seat, the support rod groove is communicated with the concave cavity portion, and the concave cavity portion is provided with a recessed groove at the front end of the support rod groove for accommodating the insertion rod portion of the mounting seat.

[0007] It is further explained that the front end boss of the mounting seat is embedded in the constriction formed by the limiting front flange portions of the right half fuselage and the left half fuselage, and a first connecting hole for connecting to the motor screw is provided on the annular surface of the front end boss, and a second connecting hole for connecting to the engine hood screw is provided around the front end boss.

[0008] It is further explained that a propeller is installed at the driving shaft of the motor, and a detachable coupling assembly is provided between the propeller and the motor, and the coupling assembly includes a first coupling member and a second coupling member, and the first coupling member and the second coupling member are interlocked.

[0009] To further explain, one end of the first coupling member is provided with an insert shaft portion for connecting to the drive shaft of the motor, the other end of the first coupling member is provided with a buckle plate portion, one end of the second coupling member is provided with an elastic claw portion for buckling with the buckle plate portion of the first coupling member, and the other end of the second coupling member is provided with a locking rod portion, and the locking rod portion is passed through the propeller.

[0010] It is further explained that a locking cap is connected to the locking rod portion of the second coupling member, and the propeller is sandwiched between the second coupling member and the locking cap.

[0011] It is further explained that a wing panel is connected to the main fuselage, aileron pieces are arranged on both the left and right sides of the wing panel, and a first servo for controlling the swing of the aileron piece is arranged at the lower middle part of the wing panel.

[0012] It is further explained that a second server for controlling the tail pulley and the tail wing is disposed inside the main body.

[0013] The beneficial effects of the present invention are as follows: the present invention adopts a mounting base and an engine cover to clamp the limiting front flange portions of the right half fuselage and the left half fuselage. Combined with the special structural design of the mounting base, the mounting base is subjected to more balanced force in the fuselage and forms a stable overall structure with the entire fuselage. Compared with the existing method of embedding and pasting the motor in the fuselage with glue, the present invention can disassemble and remove the motor without destroying the internal structure of the fuselage, and the operation is simple and convenient. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of the structure of the present invention.

[0015] Figure 2 It is a schematic diagram of the structural decomposition of the present invention.

[0016] Figure 3 It is a schematic diagram of the structure of the present invention.

[0017] Figure 4 It is a schematic diagram of the internal structure of the present invention.

[0018] Figure 5 It is a schematic diagram of the internal structure of the present invention.

[0019] Figure 6 Schematic diagram of the structural decomposition of the drive mechanism.

[0020] Figure 7 A schematic diagram of the structure of the mounting base.

[0021] Figure 8 This is an enlarged schematic diagram of the structure of the right half of the fuselage.

[0022] Figure Number:

[0023] 10. Main body; 11. Right half body; 111. Front flange portion for limiting; 112. Concave cavity portion; 113. Card slot; 114. Positioning support rod; 115. Support rod channel; 116. Concave sink groove; 12. Left half body; 20. Driving mechanism; 21. Motor; 211. Driving shaft; 22. Mounting seat; 221. Concave cavity opening; 222. Inserting rod portion; 223. Arc-shaped plate surface; 224. Card plate portion; 225. Front end boss; 226. Annular surface; 227. First connecting hole; 228. Second connecting hole; 23. Engine cover;

[0024] 30. Propeller; 31. Locking cap; 41. First connecting member; 411. Inserting shaft portion; 412. Buckle plate portion; 42. Second connecting member; 421. Elastic claw portion; 422. Locking rod portion; 50. Wing spreader; 51. Aileron piece; 61. First server; 62. Second server; 71. Tail pulley; 72. Tail; 80. Battery. DETAILED DESCRIPTION

[0025] In order to make the objectives, technical solutions and advantages of the present invention more clear, the present invention will be further described in detail below with reference to the accompanying drawings.

[0026] Combined with Figure 1 To Attachment Figure 5As shown, a remote-controlled aircraft model with a stable and easily disassembled fuselage includes a main fuselage 10, which is formed by merging and splicing a right half fuselage 11 and a left half fuselage 12. A driving mechanism 20 is provided at the front end of the nose of the main fuselage 10, and a wing display panel 50 is connected to the main fuselage 10. The left and right sides of the wing display panel 50 are provided with aileron pieces 51. A first servo 61 for controlling the swing of the aileron piece 51 is provided at the lower middle part of the wing display panel 50, and a second servo 62 for controlling the tail pulley 71 and the tail 72 is provided inside the main fuselage 10.

[0027] Combined with Figure 4 To Attachment Figure 6 As shown, the driving mechanism 20 includes a motor 21, a mounting seat 22, and a hood 23. The hood 23 is buckled with the main body 10. The mounting seat 22 is provided with a recessed cavity 221. The motor 21 is fixedly mounted at the recessed cavity 221 of the mounting seat 22. Rod portions 222 are provided on the left and right sides of the mounting seat 22. An arc-shaped plate surface 223 extending from the recessed cavity 221 of the mounting seat 22 is connected to the rod portions 222 on both sides. The arc-shaped plate surface 223 is provided with a clamping plate portion 224 below the rod portions 222. The arc-shaped plate surface 223 not only serves to connect the rod portions 222 on both sides, but also enables the mounting seat 22 to be subjected to more balanced force during assembly and disassembly.

[0028] Combined with Figure 6 To Attachment Figure 8 As shown, the right half fuselage 11 and the left half fuselage 12 are both provided with a limiting front flange portion 111, and a concave cavity portion 112 for accommodating the mounting seat 22 is opened on the rear side of the limiting front flange portion 111, and a card slot 113 for engaging with the card plate portion 224 of the mounting seat 22 is provided in the concave cavity portion 112. The concave cavity portions 112 of the right half fuselage 11 and the left half fuselage 12 can cover the entire mounting seat 22, and the motor 21 is fixedly installed in the concave cavity mouth 221 of the mounting seat 22, thereby indirectly realizing that the motor 21 and the entire fuselage form a stable integral structure, ensuring that no abnormal noise caused by loose installation of the motor 21 or the mounting seat 22 will be emitted from the fuselage during flight.

[0029] During installation, the card plate portion 224 of the mounting seat 22 is inserted into the card slot 113 of the right half fuselage 11 to play a role in fixing the installation, the hood 23 is connected to the mounting seat 22, and the limiting front flange portion 111 is clamped between the mounting seat 22 and the hood 23. Since the main body structure of the foam material cannot be directly screwed, the mounting seat 22 and the hood 23 are used to clamp the limiting front flange portions 111 of the right half fuselage 11 and the left half fuselage 12, so that the mounting seat 22 can be installed and fixed at the fuselage body.

[0030] Combined with Figure 4 and attached Figure 8As shown, the inner walls of the right half fuselage 11 and the left half fuselage 12 are provided with a rod groove 115 for accommodating the positioning rod 114, the positioning rod 114 is plugged with the rod insertion portion 222 at the mounting seat 22, the rod groove 115 is connected with the concave cavity portion 112, and the concave cavity portion 112 is provided with a concave groove 116 for accommodating the rod insertion portion 222 of the mounting seat 22 at the front end of the rod groove 115. Since the main structure of the fuselage is made of foam material, the mounting seat 22 is provided with an insertion rod portion 222 that is inserted into the concave groove 116, and the contact space between the insertion rod portion 222 and the concave groove 116 is large, which can play a role in limiting when the card plate portion 224 is inserted into the card slot 113.

[0031] Combined with Figure 5 As shown, the front end boss 225 of the mounting seat 22 is embedded in the constriction formed by the limiting front flange portions 111 of the right half fuselage 11 and the left half fuselage 12, and a first connecting hole 227 for screw connection to the motor 21 is provided on the annular surface 226 of the front end boss 225, and a second connecting hole 228 for screw connection to the engine cover 23 is provided around the front end boss 225. Before removing the motor 21 from the fuselage, the engine cover 23 needs to be removed first.

[0032] Combined with Figure 1 and attached Figure 2 As shown, a propeller 30 is installed at the driving shaft 211 of the motor 21, and a detachable coupling assembly is provided between the propeller 30 and the motor 21, and the coupling assembly includes a first coupling member 41 and a second coupling member 42, and the first coupling member 41 and the second coupling member 42 are buckled. A detachable battery 80 is also provided in the main body 10, and the battery 80 is used to power the motor 21 and other devices.

[0033] Combined with Figure 1 and attached Figure 2 As shown, one end of the first coupling 41 is provided with an inserting shaft portion 411 for connecting with the driving shaft 211 of the motor 21, the other end of the first coupling 41 is provided with a buckle plate portion 412, one end of the second coupling 42 is provided with an elastic claw portion 421 for buckling with the buckle plate portion 412 of the first coupling 41, and the other end of the second coupling 42 is provided with a locking rod portion 422, which is penetrated by the propeller 30. The locking rod portion 422 of the second coupling 42 is connected with a locking cap 31, and the propeller 30 is sandwiched between the second coupling 42 and the locking cap 31. When the model aircraft falls to the ground during flight, the coupling assembly can realize the separation between the motor 21 and the propeller 30, and the buckle plate portion 412 of the first coupling 41 can be disconnected from the elastic claw portion 421 of the second coupling 42, thereby preventing the impact force of the fall from the ground from damaging the motor 21, thereby protecting the motor 21.

[0034] Before disassembling the motor 21, the propeller 30 must be removed from the drive shaft 211 of the motor 21, and then the hood 23 must be disassembled to release the locking state of the hood 23 and the front flange portion 111 of the fuselage that limits the mounting seat 22. Then the right half fuselage 11 and the left half fuselage 12 can be separated, and then the mounting seat 22 and the motor 21 can be taken out together. Compared with the existing method of embedding and pasting the motor in the fuselage with glue, the present invention can disassemble and remove the motor 21 without destroying the internal structure of the fuselage, which is convenient for motor disassembly and maintenance, and the concave cavity portion 112 of the right half fuselage 11 and the left half fuselage 12 can cover the entire mounting seat 22, thereby indirectly realizing that the motor 21 and the entire fuselage form a stable integral structure.

[0035] In the description of the present invention, it is necessary to understand that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying 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.

[0036] It should be understood that the present invention uses the terms "first", "second", etc. to describe various information, but these information should not be limited to these terms, and these terms are only used to distinguish the same type of information from each other. For example, without departing from the scope of the present invention, "first" information may also be referred to as "second" information, and similarly, "second" information may also be referred to as "first" information.

[0037] The above description does not limit the technical scope of the present invention in any way. Any modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention are still within the scope of the technical solution of the present invention.

Claims

1. A remote-controlled aircraft model with a stable and easily disassembled fuselage, comprising a main fuselage (10), wherein the main fuselage (10) is formed by combining and splicing a right half fuselage (11) and a left half fuselage (12), and characterized in that: A driving mechanism (20) is provided at the front end of the head of the main body (10), the driving mechanism (20) comprising a motor (21), a mounting seat (22), and an engine cover (23), the engine cover (23) being buckled with the main body (10), the mounting seat (22) being provided with a concave cavity opening (221), and the motor (21) being fixedly mounted at the concave cavity opening (221) of the mounting seat (22); The left and right sides of the mounting seat (22) are provided with an insertion rod portion (222); an arc-shaped plate surface (223) extending from the concave cavity opening (221) of the mounting seat (22) is connected to the insertion rod portions (222) on both sides; a clamping plate portion (224) is provided on the arc-shaped plate surface (223) below the insertion rod portion (222); the right half fuselage (11) and the left half fuselage (12) are both provided with a limiting front flange portion (111); the limiting A concave cavity (112) for mounting the mounting seat (22) is provided on the rear side of the front flange (111), a card slot (113) for engaging with the card plate (224) of the mounting seat (22) is provided in the concave cavity (112), the engine cover (23) is connected to the mounting seat (22), and the position-limiting front flange (111) is sandwiched between the mounting seat (22) and the engine cover (23); A propeller (30) is installed at the driving shaft (211) of the motor (21), and a detachable shaft coupling assembly is provided between the propeller (30) and the motor (21), the shaft coupling assembly comprising a first shaft coupling member (41) and a second shaft coupling member (42), the first shaft coupling member (41) and the second shaft coupling member (42) being interlocked; One end of the first shaft connecting member (41) is provided with an inserting shaft portion (411) for connecting to the driving shaft (211) of the motor (21), the other end of the first shaft connecting member (41) is provided with a buckle plate portion (412), one end of the second shaft connecting member (42) is provided with an elastic claw portion (421) for buckling with the buckle plate portion (412) of the first shaft connecting member (41), the other end of the second shaft connecting member (42) is provided with a locking rod portion (422), and the locking rod portion (422) is inserted into the propeller (30); A locking cap component (31) is connected to the locking rod portion (422) of the second shaft connecting component (42), and the propeller (30) is sandwiched between the second shaft connecting component (42) and the locking cap component (31).

2. A remote-controlled aircraft model with a stable and easily dismantled fuselage according to claim 1, characterized in that: The inner walls of the right half fuselage (11) and the left half fuselage (12) are both provided with a rod groove (115) for accommodating a positioning rod (114); the positioning rod (114) is plugged into the rod insertion portion (222) at the mounting seat (22); the rod groove (115) is communicated with the concave cavity portion (112); and the concave cavity portion (112) is provided with a recessed groove (116) at the front end of the rod groove (115) for accommodating the rod insertion portion (222) of the mounting seat (22).

3. The remote-controlled aircraft model with a stable and easily dismantled fuselage according to claim 1, characterized in that: The front end boss (225) of the mounting seat (22) is embedded in the constriction formed by the limiting front flange portions (111) of the right half fuselage (11) and the left half fuselage (12), and a first connection hole (227) for screw connection to the motor (21) is provided on the annular surface (226) of the front end boss (225), and a second connection hole (228) for screw connection to the engine cover (23) is provided around the front end boss (225).

4. The remote-controlled aircraft model with a stable and easily dismantled fuselage according to claim 1, characterized in that: A wing panel (50) is connected to the main body (10), ailerons (51) are provided on both left and right sides of the wing panel (50), and a first servo (61) for controlling the swing of the ailerons (51) is provided at the lower middle part of the wing panel (50).

5. The remote-controlled aircraft model with a stable and easily dismantled fuselage according to claim 1, characterized in that: A second server (62) for controlling a tail pulley (71) and a tail wing (72) is provided inside the main body (10).

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