A fuselage structure for a model aircraft

Abstract

The utility model discloses a cabin body fuselage structure of airplane model, including main beam, connecting block, wing spar, filler plate and shell, main beam is hollow tubular structure, connecting block is set on the main beam, and the main beam is set with a plurality of detachable connecting block, wing spar detachable setting is in the main beam, and the main beam is provided with a pair of detachable wing spar, filler plate is set on the connecting block, and the filler plate of corresponding position is arranged on every connecting block, and the shell is pasted on the filler plate, through the setting of main beam, wing spar can bear the torsion that exists in the testing process of fuselage to some extent, through the setting of connecting block, filler plate can reduce fuselage load, provide the torsional node, analyze internal torsion concentration point, through the setting of shell can form the effect of rear loading and detachable, so that the maintenance use is dismantled.

Description

Technical Field

[0001] This utility model relates to the field of aircraft model technology, and in particular to a cabin and fuselage structure for an aircraft model. Background Technology

[0002] Currently, the requirements for the fuselage structure of aircraft models (especially high-performance models used for model aircraft competitions, load tests, or high-maneuverability flight) are becoming increasingly clear: they must simultaneously meet four core requirements: lightweight (to ensure range and maneuverability), high strength / torsion resistance (to cope with severe flight attitudes), internal layout flexibility (to adapt to different flight controllers, batteries, and servos), and ease of maintenance (to reduce repair costs after a crash).

[0003] Currently, the main structures of model aircraft fuselages are skin-frame type, hard-shell type, simple box type, and segmented modular type. However, each of the four types of structures has its own advantages and disadvantages. They share common pain points: it is difficult to balance strength and weight, either the weight exceeds the standard or the strength is insufficient. The current lack of efficient load-bearing frames cannot cope with the torque load in high-maneuverability flight. After the data acquisition devices set on the surface are fixed, the internal wiring is messy and most of them are integrated structures that cannot be formed and are not easy to maintain. Utility Model Content

[0004] The purpose of this utility model is to overcome the shortcomings of the prior art and provide a cabin fuselage structure for an aircraft model, and a cross-shaped frame cabin structure for an aircraft model.

[0005] The objective of this utility model is achieved through the following technical solution: a fuselage structure for an aircraft model, comprising a main beam, connecting blocks, wing spars, filling plates, and an outer shell; the main beam is a hollow tubular structure; connecting blocks are sleeved on the main beam, and a plurality of detachably mounted connecting blocks are mounted on the main beam; wing spars are detachably mounted on the main beam, and a pair of detachable wing spars are mounted on the main beam; filling plates are sleeved on the connecting blocks, and each connecting block has a corresponding filling plate; the outer shell is adhered to the filling plates.

[0006] The main beam and wing spars can share the torque that exists in the fuselage during testing to a certain extent. The connecting blocks and filler plates can reduce the load on the fuselage, provide anti-torsion nodes, analyze the internal torque concentration points, and the shell can form a retrofit and detachable effect for disassembly, maintenance and use.

[0007] The present invention is further configured such that a plurality of first line holes are formed on the outer wall of the main beam along the axial direction.

[0008] All conductors can be routed through the main beam via the first wire hole.

[0009] The present invention is further configured such that: a sleeve hole is provided in the middle of the connecting block for the main beam to pass through; a plurality of evenly distributed fixing holes are provided on the connecting block along the radial direction of the sleeve hole; at least one second line hole is provided on the connecting block along the axial direction of the main beam; and a positioning hole is provided on the connecting block along the axial direction of the main beam.

[0010] By setting several fixing holes on the connecting block, it is possible to connect to the main beam in more ways, achieving the effect of testing or fixing.

[0011] The present invention is further configured such that: the connecting block is a square plate-shaped structure, and each of the four corners of the connecting block is provided with a rounded chamfer coaxial with the circumferential axis of the main beam; the connecting block is provided with eight fixing holes, which are distributed at the four circumferential corners and four circumferential surfaces of the connecting block, and each fixing hole is connected to the sleeve hole.

[0012] With eight fixing holes, it can provide all-around fixing points. Forming the connecting block into a standardized part can provide a very convenient design effect for subsequent testing in the factory.

[0013] The present invention is further configured such that: the wing beam includes a mounting part and a wing rod part, the mounting part has a positioning opening with the same radius as the main beam, and the wing rod part is provided on the side of the mounting part away from the positioning opening.

[0014] By opening positioning ports, the mounting section can be placed as close as possible to the main beam to achieve concentric installation. Furthermore, the wing rod section can effectively provide support for the wing and provide anti-torsional effect.

[0015] The present invention is further configured such that: the mounting part is provided with connecting holes on both sides near the wing rod part, and the wing rod part is a hollow structure through which the mounting part passes.

[0016] The connection holes can be matched with the fixing holes at the four corners of the connection block, allowing sensors to replace traditional bolts for testing torque at the wing and fuselage.

[0017] The present invention is further configured such that a plurality of third wire holes are evenly spaced on the wing rod portion.

[0018] The third wire hole is designed to effectively route the wing sensor wiring into the fuselage.

[0019] The present invention is further configured such that: the mounting part has an arc-shaped structure, and the mounting surface of the mounting part has a mounting groove that can at least partially cover the connecting block.

[0020] The mounting slots allow the circumferential sides of the connecting block to be covered, providing lateral torsional resistance. Torque can also be measured and calculated using pressure sensors.

[0021] The present invention has the following beneficial effects: the main beam and wing beam can share the torsional force of the fuselage during the test to a certain extent; the connecting block and filling plate can reduce the load on the fuselage, provide anti-torsion nodes, analyze the internal torsional concentration points; and the outer shell can form a retrofit and detachable effect for disassembly, maintenance and use. Attached Figure Description

[0022] Figure 1 This is an assembly drawing of the skeleton in an embodiment of this utility model; Figure 2 This is an assembly cross-sectional view of the skeleton in an embodiment of this utility model; Figure 3 This is a perspective view of the connecting block in an embodiment of this utility model; Figure 4 This is a first perspective view of the wing beam in an embodiment of this utility model; Figure 5 This is a second perspective view of the wing beam in an embodiment of this utility model.

[0023] In the picture: 1. Main beam; 11. First borehole; 2. Connecting block; 21. Fixing hole; 22. Second wire hole; 23. Positioning hole; 24. Sleeve hole; 3. Wing spars; 31. Third line hole; 32. Wing rod section; 33. Mounting section; 34. Mounting groove; 35. Positioning port; 36. Connecting hole; 4. Filler plate. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. The components of the embodiments of this utility model described and shown in the accompanying drawings can typically be arranged and designed in various different configurations.

[0025] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0026] It should be noted that, where there is no conflict, the embodiments and features in the embodiments of this utility model can be combined with each other.

[0027] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0028] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this utility model is in use, or the orientation or positional relationship commonly understood by those skilled in the art. They are only used for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. In addition, the terms "first," "second," etc., are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0029] In the description of this utility model, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0030] The following is in conjunction with the appendix Figure 1-5 The present invention will be described in further detail, but the scope of protection of the present invention is not limited to the following.

[0031] like Figure 1 As shown, the fuselage structure of an aircraft model includes a main beam 1, a connecting block 2, a wing spars 3, a filling plate 4, and an outer shell; the main beam 1 has a hollow tubular structure. Connecting block 2 is sleeved on main beam 1, and several detachable connecting blocks 2 are sleeved on main beam 1; The wing beam 3 is detachably mounted on the main beam 1, and a pair of detachable wing beams 3 are mounted on the main beam 1; The filler plate 4 is sleeved on the connecting block 2, and each connecting block 2 is provided with a filler plate 4 at a corresponding position; The outer shell is attached to the protective filler plate 4; In this scheme, a number of first wire holes 11 are provided on the outer wall of the main beam 1 along the axial direction; through the first wire holes 11, all wires can be routed through the main beam 1.

[0032] The connecting block 2 has a sleeve hole 24 in the middle for the main beam 1 to pass through. The connecting block 2 has several evenly distributed fixing holes 21 along the radial direction of the sleeve hole 24. The connecting block 2 has at least one second line hole 22 along the axial direction of the main beam 1. The connecting block 2 has a positioning hole 23 along the axial direction of the main beam 1. By setting several fixing holes 21 on the connecting block 2, it can be connected to the main beam 1 in more ways to achieve the effect of testing or fixing.

[0033] The connecting block 2 has a square plate-like structure. Each of the four corners of the connecting block 2 has a rounded chamfer that is coaxial with the main beam 1. The connecting block 2 has eight fixing holes 21, which are distributed at the four corners and four sides of the connecting block 2. All the fixing holes 21 are connected to the sleeve holes 24. The eight fixing holes 21 provide a full range of fixing points. The standardization of the connecting block 2 can provide a very convenient design effect for subsequent testing in the factory.

[0034] like Figure 3 As shown, the fixing holes 21 on the connecting block 2 are all threaded holes, and the second wire hole 22 and the positioning hole 23 are through holes.

[0035] The wing sparb 3 includes a mounting part 33 and a wing rod part 32. The mounting part 33 has a positioning opening 35 with the same radius as the main sparb 1. The wing rod part 32 is provided on the side of the mounting part 33 away from the positioning opening 35. The positioning opening 35 allows the mounting part 33 to be as close as possible to the main sparb 1 while achieving concentric installation. Furthermore, the wing rod part 32 effectively provides a support position for the wing and provides anti-torsion effect.

[0036] The mounting part 33 is provided with connection holes 36 on both sides near the wing rod part 32. The wing rod part 32 is a hollow structure, and the hollow part passes through the mounting part 33. The connection holes 36 can be used to cooperate with the fixing holes 21 provided at the four corners of the connecting block 2. The torque of the wing and fuselage can be tested by replacing the traditional bolts with sensors.

[0037] Several third wire holes 31 are evenly spaced on the wing rod 32; the third wire holes 31 are provided to effectively guide the wing sensor wiring into the fuselage.

[0038] The mounting part 33 has an arc-shaped structure, and the mounting surface of the mounting part 33 has a mounting groove 34 that can at least partially cover the connecting block 2. The mounting groove 34 can cover the circumferential side of the connecting block 2, and can provide anti-torsional force in the side. The torque can also be measured and calculated by a pressure sensor.

[0039] In this scheme, the connecting block 2 for installing the two side wing beams 3 is a separate connecting block 2 identical to the one described above.

[0040] To further reduce the weight of the fuselage, the connecting block 2 can be a hollow part made of carbon fiber, and a pre-embedded threaded sleeve is pre-embedded in the fixing hole 21.

[0041] This design includes a set screw, which is a cylindrical body with external threads and an internal hexagonal groove at one end.

[0042] To increase the wing's torsional strength and support, the wing spars 3 and the main spars 1 have the same diameter, and corresponding filler plates 4 can also be added.

[0043] In this solution, dividing the filling plate into four pieces can effectively reduce the weight of the machine body, ensure the stability of the machine body, and provide support for the outer shell.

[0044] In this design, the fuselage shell is divided into two halves by the plane between the two wings, and the two halves are fixed together by bolts or glue.

[0045] Usage process: Place several connecting blocks 2 on the main beam 1, and screw at least one set screw into each connecting block 2 through all the positioning holes 23 in sequence by passing the positioning strip through them. Then fix the wing beam 3 and the connecting blocks 2 at the preset position by gluing the filling plate 4 or by using the outward protrusion of the set screw.

[0046] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A fuselage structure for an aircraft model, characterized in that: The main beam (1) has a hollow tubular structure; A connecting block (2) is sleeved on the main beam (1), and a plurality of detachable connecting blocks (2) are sleeved on the main beam (1); A pair of detachable wing beams (3) are provided on the main beam (1); A filler plate (4) is sleeved on the connecting block (2), and each connecting block (2) is provided with a filler plate (4) at a corresponding position; The outer shell is attached to the protective filler plate (4).

2. The fuselage structure of an aircraft model according to claim 1, characterized in that: Several first line holes (11) are provided on the outer wall of the main beam (1) along its axial direction.

3. The fuselage structure of an aircraft model according to claim 1, characterized in that: The connecting block (2) has a sleeve hole (24) in the middle for the main beam (1) to pass through. The connecting block (2) has a plurality of evenly distributed fixing holes (21) along the radial direction of the sleeve hole (24). The connecting block (2) has at least one second line hole (22) along the axial direction of the main beam (1). The connecting block (2) has a positioning hole (23) along the axial direction of the main beam (1).

4. The fuselage structure of an aircraft model according to claim 3, characterized in that: The connecting block (2) has a square sheet structure. The four corners of the connecting block (2) are provided with rounded chamfers that are coaxial with the main beam (1) in the circumferential direction. The connecting block (2) is provided with eight fixing holes (21). The eight fixing holes (21) are distributed at the four corners and four sides of the connecting block (2) in the circumferential direction. The fixing holes (21) are all connected to the sleeve hole (24).

5. The fuselage structure of an aircraft model according to claim 1, characterized in that: The wing beam (3) includes a mounting part (33) and a wing rod part (32). The mounting part (33) has a positioning hole (35) with the same radius as the main beam (1). The wing rod part (32) is provided on the side of the mounting part (33) away from the positioning hole (35).

6. The fuselage structure of an aircraft model according to claim 5, characterized in that: The mounting part (33) is provided with connecting holes (36) on both sides near the wing rod part (32), and the wing rod part (32) is a hollow structure with the hollow part passing through the mounting part (33).

7. The fuselage structure of an aircraft model according to claim 6, characterized in that: The wing rod portion (32) is provided with a plurality of third wire holes (31) at even intervals.

8. The fuselage structure of an aircraft model according to claim 7, characterized in that: The mounting part (33) has an arc-shaped structure, and the mounting surface of the mounting part (33) has a mounting groove (34) that can at least partially cover the connecting block (2).

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