Bionic aircraft fuselage convenient to replace

Abstract

The utility model relates to the technical field of bionic aircrafts, and provides a bionic aircraft fuselage convenient to replace, which comprises a left fuselage and a right fuselage, the left fuselage and the right fuselage are oppositely arranged, a plurality of uniformly distributed insertion holes are formed in the vertical side wall of the side wall of the right fuselage, and insertion rods are fixedly connected to the positions of the left fuselage corresponding to the insertion holes. A plurality of fixing pins are arranged on the cambered surface of the inner wall of the right machine body, the multiple fixing pins correspond to the multiple inserting holes one to one, the fixing pins are slidably connected into the corresponding inserting holes, a sliding ring cavity is formed in the right machine body, and a sliding ring is slidably connected into the sliding ring cavity; and the sliding ring is fixedly connected with an extrusion wedge block corresponding to each fixed pin. According to the device, connecting through holes do not need to be formed in the peripheries of the left fuselage and the right fuselage, a streamline structure between the left fuselage and the right fuselage cannot be damaged, and the left fuselage and the right fuselage are easy and rapid to connect and disassemble and convenient to replace.

Description

Technical Field

[0001] The utility model relates to the technical field of bionic aircraft, in particular to a fuselage of a bionic aircraft which is easy to replace. Background Art

[0002] The bionic flapping wing drone is a new type of drone designed based on the flight patterns of birds and insects in nature. It generates lift and propulsion by mimicking the flapping motion of living creatures, resulting in unique flight performance and potential applications.

[0003] The two ends of the fuselage of existing bionic aircraft are often fixed to each other by bolts. Bolt holes are usually designed at the joint of the two halves of the fuselage, and the two halves of the fuselage are firmly connected together by bolts. This connection method has the advantages of simple structure and reliable force transmission, but the bolt holes will destroy the continuity of the streamlined outer shell, resulting in reduced structural strength and rigidity. In addition, multiple bolts are often provided on the fuselage, which is cumbersome to disassemble and assemble and inconvenient to replace. Utility Model Content

[0004] The purpose of the utility model is to solve the problem in the prior art that the two ends of the fuselage of the existing bionic aircraft are often fixed to each other by bolts, and the joints of the two halves of the fuselage are usually designed with bolt holes, and the two halves of the fuselage are firmly connected together by bolts. This connection method has the advantages of simple structure and reliable force transmission, but the bolt holes will destroy the continuity of the streamlined outer shell, resulting in reduced structural strength and rigidity, and multiple bolts are often provided on the fuselage, which is cumbersome to disassemble and assemble and inconvenient to replace.

[0005] To achieve the above-mentioned object, the present invention adopts the following technical solution: a fuselage of a bionic aircraft that is easy to replace, comprising a left fuselage and a right fuselage, the left fuselage and the right fuselage being arranged opposite each other, a plurality of evenly distributed insertion holes being opened in the vertical side wall of the right fuselage side wall, a plug rod being fixedly connected at the corresponding insertion holes of the left fuselage, a fixing hole being opened in the plug rod, a plurality of fixing pins being provided on the arc surface of the inner wall of the right fuselage, a plurality of the fixing pins being arranged in a one-to-one correspondence with the plurality of insertion holes, the fixing pins being slidably connected inside the corresponding insertion holes, a sliding ring cavity being opened inside the sliding ring cavity, a sliding ring being slidably connected inside the sliding ring, an extrusion wedge being fixedly connected at each fixing pin of the sliding ring, the inclined surface of the extrusion wedge being abutted against the inclined surface of the rear end of the fixing pin, the fixing pin being inserted inside the plug rod, the device does not require opening connecting through holes on the outer periphery of the left and right fuselage, does not destroy the streamlined structure between the left and right fuselage, and the connecting and disassembling operations between the left and right fuselage are simple and quick, making replacement easy.

[0006] As a preferred embodiment, a ring disk is provided on the outer periphery of the rear end of the fixing pin, and a first spring is fixedly connected between the ring disk and the inner wall. By setting the first spring, the fixing pin can be automatically reset, so that the fixing pin can be away from the socket under normal circumstances.

[0007] As a preferred embodiment, the rear end of the sliding ring is fixedly connected to two symmetrically distributed pulling frames. By providing the pulling frames, the user can use a hook tool to pull the sliding ring to move it.

[0008] As a preferred embodiment, a plurality of evenly distributed mounting plates are fixedly connected inside the left fuselage, a second spring is fixedly connected to the end face of the mounting plate, and the movable end of the second spring is fixedly connected to the sliding ring. By arranging the mounting plate in conjunction with the second spring, the sliding ring can be automatically reset.

[0009] As a preferred embodiment, a plurality of evenly distributed guide rods are fixedly connected inside the right fuselage, and the guide rods are slidably connected to the sliding ring. The guide rods are provided to limit the movement of the sliding ring, making the movement of the sliding ring more stable.

[0010] As a preferred embodiment, the left fuselage and the right fuselage are both streamlined in design, which can reduce air resistance and improve flight efficiency.

[0011] As a preferred embodiment, the left and right fuselages are made of carbon fiber reinforced plastic material, which has excellent mechanical properties, can withstand various stresses during flight, and is lightweight.

[0012] As a preferred embodiment, a counterweight block is fixedly connected to the inside of the left fuselage. The counterweight block has the same weight as the various accessories in the right fuselage, which can make the internal weight of the left and right fuselages the same, making the weight at both ends of the aircraft more even and making the flight more balanced.

[0013] Compared with the prior art, the advantages and positive effects of the present invention are:

[0014] 1. The utility model does not require a connecting through hole to be provided on the outer periphery of the left and right fuselages, and the streamlined structure between the left and right fuselages will not be damaged. Moreover, the connecting and disassembling operations between the left and right fuselages are simple and quick, and are convenient for replacement.

[0015] 2. In the present invention, the left and right fuselages are made of carbon fiber reinforced plastic material, which has excellent mechanical properties and can withstand various stresses during flight while being lightweight. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1A schematic diagram of the three-dimensional structure of a fuselage of a bionic aircraft that is easily replaceable provided by the utility model;

[0017] Figure 2 A schematic diagram of the internal structure of the left fuselage of a bionic aircraft that is easily replaceable provided by the utility model;

[0018] Figure 3 A schematic diagram of the internal structure of the right fuselage of a bionic aircraft that is easily replaceable provided by the utility model;

[0019] Figure 4 A schematic diagram of the internal structure of the right fuselage of a bionic aircraft that is easily replaceable provided by the present invention (after removing the sliding ring);

[0020] Figure 5 This is a schematic diagram of the front structure of a sliding ring of a fuselage of a bionic aircraft that is easy to replace provided by the utility model.

[0021] Figure 6 This is a schematic diagram of the front structure of a sliding ring of a fuselage of a bionic aircraft that is easy to replace provided by the utility model;

[0022] Figure 7 The utility model provides a bionic aircraft fuselage that is easy to replace Figure 4 A partial enlarged view of the middle part;

[0023] Legend:

[0024] 1. Left fuselage; 2. Right fuselage; 3. Sliding ring; 4. Insertion hole; 5. Guide rod; 6. Fixing pin; 7. Ring disk; 8. First spring; 9. Extrusion wedge; 10. Pulling frame; 11. Second spring; 12. Sliding ring cavity; 13. Mounting plate; 15. Insertion rod; 16. Fixing hole; 17. Counterweight. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0026] See also Figure 1-7The utility model provides a technical solution: a fuselage of a bionic aircraft that is easy to replace, including a left fuselage 1 and a right fuselage 2, the left fuselage 1 and the right fuselage 2 are arranged opposite to each other, a plurality of evenly distributed sockets 4 are opened in the vertical side wall of the right fuselage 2, the left fuselage 1 is fixedly connected to the corresponding sockets 4 with a plug rod 15, and a fixing hole 16 is opened in the plug rod 15, and a plurality of fixing pins 6 are provided on the arc surface of the inner wall of the right fuselage 2, and the plurality of fixing pins 6 are arranged in a one-to-one correspondence with the plurality of sockets 4, and the fixing pins 6 are slidably connected to the corresponding sockets 4 Internally, a sliding ring cavity 12 is opened inside the right fuselage 2, and a sliding ring 3 is slidably connected in the sliding ring cavity 12. The sliding ring 3 is fixedly connected to an extrusion wedge 9 corresponding to each fixed pin 6. The inclined surface of the extrusion wedge 9 is against the inclined surface of the rear end of the fixed pin 6. The fixed pin 6 is inserted inside the insertion rod 15. This device does not require connecting through holes on the outer periphery of the left fuselage 1 and the right fuselage 2, and will not destroy the streamlined structure between the left fuselage 1 and the right fuselage 2. The connection and disassembly operation between the left fuselage 1 and the right fuselage 2 is simple and quick, and is convenient for replacement.

[0027] like Figure 1-7 As shown, a ring disk 7 is provided on the outer periphery of the rear end of the fixing pin 6, and a first spring 8 is fixedly connected between the ring disk 7 and the inner wall. By setting the first spring 8, the fixing pin 6 can be automatically reset, so that the fixing pin 6 can be away from the socket 4 under normal circumstances.

[0028] like Figure 1-7 As shown, the rear end of the sliding ring 3 is fixedly connected to two symmetrically distributed pulling frames 10. By providing the pulling frames 10, the user can use a hook tool to pull the sliding ring 3 to move.

[0029] like Figure 1-7 As shown, a plurality of evenly distributed mounting plates 13 are fixedly connected inside the left fuselage 1, a second spring 11 is fixedly connected to the end face of the mounting plate 13, and a movable end of the second spring 11 is fixedly connected to the sliding ring 3. By arranging the mounting plate 13 in conjunction with the second spring 11, the sliding ring 3 can be automatically reset.

[0030] like Figure 1-7 As shown, a plurality of evenly distributed guide rods 5 are fixedly connected inside the right fuselage 2, and the guide rods 5 are slidably connected to the sliding ring 3. The guide rods 5 are provided to limit the movement of the sliding ring 3, making the movement of the sliding ring 3 more stable.

[0031] like Figure 1-7 As shown, the left fuselage 1 and the right fuselage 2 are both streamlined in design, which can reduce air resistance and improve flight efficiency.

[0032] like Figure 1-7As shown, the left fuselage 1 and the right fuselage 2 are made of carbon fiber reinforced plastic CFRP material, which has excellent mechanical properties and can withstand various stresses during flight while being lightweight.

[0033] like Figure 1-7 As shown, a counterweight block 17 is fixedly connected to the inside of the left fuselage 1. The counterweight block 17 has the same weight as the various accessories in the right fuselage 2, which can make the internal weight of the left fuselage 1 and the right fuselage 2 the same, making the weight at both ends of the aircraft more even and making the flight more balanced.

[0034] Working principle: When the fuselage is in use, after the various mounting parts of the aircraft are installed between the left fuselage 1, the insertion rod 15 on the left fuselage 1 is inserted into the insertion hole 4 in the right fuselage 2 under the adjustment of the pulling frame 10 pulled by a hook tool, and then the pulling frame 10 is released. The sliding ring 3 is no longer subjected to force and is driven to move by the deformation recovery of the second spring 11. Through the guide limit of the guide rod 5, the multiple extrusion wedges 9 on the sliding ring 3 squeeze the rear end of the fixing pin 6, causing the fixing pin 6 to slide into the insertion hole 4, thereby causing the fixing pin 6 to be inserted into the fixing hole 16, that is, The function of fixing the left fuselage 1 and the right fuselage 2 is realized. Conversely, when the left fuselage 1 and the right fuselage 2 need to be removed, it is only necessary to pull the sliding ring 3 in the opposite direction by pulling the pulling frame 10, and the fixing pin 6 can slide out of the fixing hole 16 under the restoring deformation effect of the first spring 8 to release the fixation, that is, the fixation between the left fuselage 1 and the right fuselage 2 is cancelled. This device does not need to open connecting through holes on the outer periphery of the left fuselage 1 and the right fuselage 2, will not destroy the streamlined structure between the left fuselage 1 and the right fuselage 2, and the connection and disassembly operation between the left fuselage 1 and the right fuselage 2 is simple and quick, and is convenient for replacement.

[0035] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any other form. Any technician familiar with the profession may use the technical content disclosed above to change or modify it into an equivalent embodiment with equivalent changes for application in other fields. However, any simple modification, equivalent change and modification of the above embodiment made according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall still fall within the scope of protection of the technical solution of the present invention.

Claims

1. A bionic aircraft fuselage that is easily replaceable, comprising a left fuselage (1) and a right fuselage (2), characterized in that: The left fuselage (1) and the right fuselage (2) are arranged opposite to each other, and a plurality of evenly distributed jacks (4) are provided in the vertical side wall of the side wall of the right fuselage (2), and the corresponding jacks (4) of the left fuselage (1) are fixedly connected with an insertion rod (15), and a fixing hole (16) is provided in the insertion rod (15), and a plurality of fixing pins (6) are provided on the arc surface of the inner wall of the right fuselage (2), and the plurality of fixing pins (6) are arranged in a one-to-one correspondence with the plurality of jacks (4), and the fixing pins (6) are slidably connected to the corresponding jacks (4), and a sliding ring cavity (12) is provided in the right fuselage (2), and a sliding ring (3) is slidably connected in the sliding ring cavity (12), and the sliding ring (3) is fixedly connected to each fixing pin (6) of the sliding ring (3), and an extrusion wedge (9) is fixedly connected to each fixing pin (6), and the inclined surface of the extrusion wedge (9) abuts against the inclined surface of the rear end of the fixing pin (6), and the fixing pin (6) is inserted into the insertion rod (15).

2. The easily replaceable fuselage of a bionic aircraft according to claim 1, characterized in that: A ring disk (7) is fixedly sleeved on the outer periphery of the rear end of the fixing pin (6), and a first spring (8) is fixedly connected between the ring disk (7) and the inner wall.

3. The easily replaceable fuselage of a bionic aircraft according to claim 1, characterized in that: The rear end of the sliding ring (3) is fixedly connected to two symmetrically distributed pulling frames (10).

4. The easily replaceable fuselage of a bionic aircraft according to claim 1, characterized in that: A plurality of evenly distributed mounting plates (13) are fixedly connected inside the left fuselage (1), a second spring (11) is fixedly connected to the end surface of the mounting plate (13), and a movable end of the second spring (11) is fixedly connected to the sliding ring (3).

5. The easily replaceable fuselage of a bionic aircraft according to claim 1, characterized in that: A plurality of evenly distributed guide rods (5) are fixedly connected inside the right fuselage (2), and the guide rods (5) are slidably connected to the sliding ring (3).

6. The easily replaceable fuselage of a bionic aircraft according to claim 1, characterized in that: The left fuselage (1) and the right fuselage (2) are both streamlined in design.

7. The easily replaceable fuselage of a bionic aircraft according to claim 1, characterized in that: The left fuselage (1) and the right fuselage (2) are made of carbon fiber reinforced plastic (CFRP) material.

8. The easily replaceable fuselage of a bionic aircraft according to claim 1, characterized in that: A counterweight (17) is fixedly connected to the interior of the left fuselage (1), and the counterweight (17) has the same weight as the various accessories in the right fuselage (2).

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