Push-pull rod and aircraft

Abstract

The utility model provides a push-pull rod and an aircraft. The aircraft comprises the push-pull rod. The push-pull rod comprises a first connecting rod, a connecting module and a second connecting rod, the components are sequentially and coaxially arranged, the connecting module comprises a connecting piece and a fixing piece, the connecting piece is provided with a first end, a second end and a body, and the first end and the second end are respectively provided with external threads; a first threaded hole is formed in one end of the first connecting rod, and the first threaded hole is meshed with the external thread of the first end so as to fixedly connect the first connecting rod with the connecting piece; a second threaded hole is formed in one end of the fixing piece, and the second threaded hole is meshed with the external thread of the second end so as to fixedly connect the connecting piece and the fixing piece; the other end of the fixing piece is provided with a containing cavity used for containing one end of the second connecting rod. The device is simple in structure, safe, reliable and convenient to maintain.

Description

Technical field

[0001] The utility model relates to the technical field of aircraft, in particular to a push-pull rod and an aircraft. [Background Technology]

[0002] The tail rotor on an aircraft is an important part of the mechanism for controlling the flight direction. When designing and modifying an aircraft, the design of the push-pull rod is an important consideration to ensure the flight stability and controllability of the aircraft.

[0003] A common method for assembling push-pull rods on the market today involves screwing a standard bolt into a through-hole in a connecting sleeve, with the bolt head contained within the through-hole and the bolt shaft extending out of the through-hole. A ball-end connecting rod is then screwed onto the bolt extending from the connecting sleeve, and the carbon fiber rod is inserted into the connecting sleeve and cured with glue. In this structure, since the bolt head is contained in the through-hole, which also houses the fixed carbon rod, the size of the bolt head cannot differ significantly from the diameter of the carbon fiber rod.

[0004] When a bolt model with a strong load capacity is selected for assembly, the bolt head diameter is larger, and the diameter of the connecting sleeve through-hole and the carbon fiber rod also needs to be increased accordingly. Since the length of the carbon fiber rod accounts for a large proportion of the total fuselage length, the weight of the entire aircraft will increase as the diameter of the carbon fiber rod increases, affecting the load-bearing performance of the aircraft. When selecting a bolt model to match the diameter of the carbon fiber rod, the optional bolt model often has a limited load capacity. During the operation of the push-pull rod, the bolt connection between the connecting rod and the carbon fiber rod needs to face a complex stress environment. Bolts with insufficient load capacity are at risk of breaking after long-term use or when subjected to impact. Once a bolt breaks, the entire push-pull rod needs to be replaced, which is inconvenient and costly to maintain.

[0005] Therefore, it is necessary to provide a push-pull rod to solve the above problems. [Utility Model Content]

[0006] The embodiments of the present invention provide a push-pull rod and an aircraft to solve the problem that the sizes of the bolts and the carbon fiber rods of the push-pull rod are mutually restricted, thereby affecting the performance of the aircraft.

[0007] An embodiment of the present utility model provides a push-pull rod, which includes a first connecting rod, a connecting module and a second connecting rod, and the components are coaxially arranged in sequence, wherein: the connecting module includes a connecting piece and a fixing piece, and the connecting piece includes a first end, a second end and a body, and the first end and the second end are respectively provided with external threads; a first threaded hole is provided at one end of the first connecting rod, and the first threaded hole is engaged with the external thread of the first end to connect the first connecting rod and the connecting piece; a second threaded hole is provided at one end of the fixing piece, and the second threaded hole is engaged with the external thread of the second end to connect the connecting piece and the fixing piece; a receiving cavity is provided at the other end of the fixing piece for accommodating one end of the second connecting rod, and the second threaded hole and the receiving cavity are arranged at two ends of the fixing piece coaxially facing each other.

[0008] At the same time, an aircraft is provided, which includes a push-pull rod, a tail rotor mechanism and a servo. The servo drives the push-pull rod, and the push-pull rod is used to connect the tail rotor mechanism and the servo. The push-pull rod includes a first connecting rod, a connecting module and a second connecting rod, and the components are coaxially arranged in sequence, wherein: the connecting module includes a connecting member and a fixing member, the connecting member includes a first end, a second end and a body, and the first end and the second end are respectively provided with external threads; a first threaded hole is provided at one end of the first connecting rod, and the first threaded hole is engaged with the external thread of the first end to connect the first connecting rod and the connecting member; a second threaded hole is provided at one end of the fixing member, and the second threaded hole is engaged with the external thread of the second end to connect the connecting member and the fixing member; the other end of the fixing member is provided with a receiving cavity for accommodating one end of the second connecting rod, and the second threaded hole and the receiving cavity are arranged at two ends of the fixing member that are coaxially opposed to each other.

[0009] Compared to push-pull rods in related assembly methods, the push-pull rod provided by this utility model uses a double-threaded connector, allowing for different thread sizes at each end. This allows for a wide range of applications. Its main body is not restricted by the size of other components and can withstand complex stress environments without breaking. This utility model offers a simple structure, safety, reliability, and easy maintenance.

Brief Description of the Drawings

[0010] Figure 1 The present invention provides a three-dimensional structural diagram of an aircraft according to an embodiment of the present invention.

[0011] Figure 2 for Figure 1 Schematic diagram of the three-dimensional structure of the push-pull rod shown.

[0012] Figure 3 for Figure 1 Exploded view of the push-pull rod shown.

[0013] Figure 4 for Figure 1 A cross-sectional view of the fixing member is shown. [Specific implementation method]

[0014] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiment is only one embodiment of the present invention, rather than all embodiments.

[0015] In addition, if the embodiments of the present invention include descriptions of "first," "second," etc., these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, features specified as "first" or "second" may explicitly or implicitly include at least one of these features.

[0016] See also Figure 1 , Figure 1 The figure is a schematic diagram of the three-dimensional assembly structure of an aircraft 1 provided by the present invention. The aircraft 1 includes a tail rotor mechanism 15, a push-pull rod 13, and a servo 11. The push-pull rod 13 connects the tail rotor mechanism 15 and the servo 11. The servo 11 drives the push-pull rod 13, applying force to the tail rotor mechanism 15, thereby adjusting the flight attitude of the aircraft 1.

[0017] Please refer to Figures 2 to 4 , Figure 2 for Figure 1 The three-dimensional structure diagram of the push-pull rod shown in FIG. Figure 3 for Figure 1 The exploded diagram of the push-pull rod is shown in FIG. Figure 4 for Figure 1 The push-pull rod 13 comprises a first connecting rod 131, a connecting module 133 and a second connecting rod 135, which are coaxially arranged and connected in sequence, wherein:

[0018] A first threaded hole 1311 is provided at one end of the first connecting rod 131. In this embodiment, the first connecting rod 131 can be made of plastic.

[0019] The connection module 133 includes a connector 1331 and a fixing member 1333. The connector 1331 includes a body 13311, a first end 13313 with external threads, and a second end 13315. The first end 13313 and the second end 13315 are located on opposite sides of the body 13311. The first threaded hole 1311 is provided to correspond to the external threads of the first end 13313. The first threaded hole 1311 engages with the external threads of the first end 13313 to achieve a stable connection between the connector 1331 and the first connecting rod 131. In this embodiment, the connector 1331 can be made of metal.

[0020] One end of the fixing member 1333 is provided with a second threaded hole 13335. The second threaded hole 13335 corresponds to the external thread of the second end 13315. The second threaded hole 13335 engages with the external thread of the second end 13315 to achieve a stable connection between the connecting member 1331 and the fixing member 1333. The fixing member 1333 also has a receiving cavity 13333 for receiving and securing one end of the second connecting rod 135. The receiving cavity 13333 and the second threaded hole 13335 are located at opposite ends of the fixing member 1333. In this embodiment, the fixing member 1333 may be made of metal, and the second connecting rod 135 may be made of a carbon fiber composite material.

[0021] It should be noted that the diameter of the second connecting rod 135 is matched with the inner wall size of the receiving cavity 13333. Due to the existence of processing errors, in order to prevent one end of the second connecting rod 135 from exiting the receiving cavity 13333, the connecting module 133 further includes a fastener 1335.

[0022] The fastener 1335 includes a fastening portion 13351 and a locking portion 13353. In this embodiment, the fastening portion 13351 is roughly U-shaped and includes a base 133511 and an arm 133513, wherein the number of the arm 133513 is two. The base 133511 is sleeved on the fixing member 1333 and is arranged corresponding to the position of the receiving cavity 13333. The two arms 133513 arranged at intervals are parallel to each other, and the arms 133513 extend from the base 133511 and extend in a direction away from the receiving cavity 13333. The arm 133513 is provided with a third threaded hole 133515, and the center lines of the through holes 133515 of the two arms 133513 are aligned. One end of the locking portion 13353 is provided with an external thread, and the external thread is arranged corresponding to the internal thread of the third threaded hole 133515. After the locking portion 13353 is locked into the through holes 133515 of the two arm portions 133513, the two spaced-apart arm portions 133513 are brought closer together, thereby deforming the base portion 133511 and tightening the receiving cavity 13333. As a result, one end of the second connecting rod 135 is clamped and fixed by the inner wall of the receiving cavity 13333. In this embodiment, the locking portion 13353 may be a bolt.

[0023] In this embodiment, the arm portion 133513 is configured as a fan-shaped column, and the fastening portion 13351 and the fixing member 1333 are configured as an integrated structure. In other embodiments, the arm portion 133513 can be a square column, and the fastening portion 13351 and the fixing member 1333 can be movably connected.

[0024] In other embodiments, the fastening portion 13351 may have a plurality of arms 133513, the number being at least two, and a soft material may be provided to fill or retain a gap between adjacent arms. The arms 133513 and the locking portion 13353 may have other locking methods, for example: the arm 133513 is provided with a through hole 133515, the center lines of the through holes 133515 of the plurality of arms 133311 are aligned one by one, the locking portion 13353 includes a set of corresponding bolts and nuts, the locking portion 13353 passes through the through holes 133515 and the bolts and nuts cooperate with each other to clamp the arms 133513, so that adjacent arms 133513 are close to each other, thereby achieving the effect of the base 133511 deforming and hugging the receiving cavity 13333. For another example, the locking portion 13353 locks the arm portion 133513 by snapping.

[0025] When the push-pull rod 13 needs to be maintained, it is only necessary to disassemble and separate the components connected by the bolts, and then the individual components can be maintained and replaced, thus saving maintenance costs.

[0026] In contrast to push-pull rods in related assembly methods, the push-pull rod 13 provided in this embodiment utilizes a double-threaded connector 1331. Both ends of connector 1331 can be provided with external threads of varying sizes, facilitating a wide range of applications. Its main body 13311 is not restricted by the dimensions of other components, and can withstand complex stress environments without breaking. The push-pull rod 13 provided in this embodiment can accommodate model helicopters 1 of varying sizes, offering a simple structure, safety, reliability, and ease of maintenance.

[0027] The embodiments described above are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A push-pull rod, characterized in that: include: a first connecting rod, wherein one end of the first connecting rod is provided with a first threaded hole; A connecting module is provided between the first connecting rod and the second connecting rod, and includes: a connecting member, the connecting member including a first end and a second end respectively provided with external threads, the external threads of the first end being provided corresponding to the first threaded hole to fixedly connect the connecting module and the first connecting rod; and A fixing member, wherein one end of the fixing member has a receiving cavity and the other end is provided with a second threaded hole, and the second threaded hole is correspondingly arranged to the external thread of the second end to fixedly connect the connecting member and the fixing member; and The second connecting rod has one end received in the receiving cavity.

2. The push-pull rod according to claim 1, characterized in that: The first connecting rod, the connecting module and the second connecting rod are coaxially arranged and connected in sequence.

3. The push-pull rod according to claim 1, characterized in that: The connecting member further includes a body, and the first end and the second end are arranged opposite to each other at two ends of the body.

4. The push-pull rod according to claim 1, characterized in that: The second threaded hole and the receiving cavity are arranged opposite to each other at two ends of the fixing member.

5. The push-pull rod according to claim 1, characterized in that: The fixing member further includes a fastener, which is sleeved on the fixing member and corresponds to the position of the receiving cavity.

6. The push-pull rod according to claim 5, characterized in that: The fastener includes a fastening portion and a locking portion. The fastening portion includes two or more arm portions. The two or more arm portions are arranged in parallel and at intervals. The two or more arm portions extend in a direction away from the receiving cavity. The locking portion causes the fastening portion to press the fixing member to fix the second connecting rod by bringing the arm portions closer to each other.

7. The push-pull rod according to claim 6, characterized in that: The arm portions are provided with third threaded holes, and the center lines of the third threaded holes of each arm portion are aligned one by one.

8. The push-pull rod according to claim 7, characterized in that: One end of the locking portion is provided with an external thread, and the external thread is arranged corresponding to the internal thread of the third threaded hole.

9. The push-pull rod according to claim 8, characterized in that: The fastener is locked into the third threaded hole, so that the adjacent arms are brought closer together, thereby deforming the fastening portion to compress the receiving cavity, so that the inner wall of the receiving cavity clamps and fixes one end of the second connecting rod.

10. An aircraft, characterized in that: include: tail rotor mechanism; The push-pull rod according to any one of claims 1 to 9, wherein the push-pull rod is connected to the tail rotor mechanism; The servo drives the push-pull rod and is connected to the push-pull rod.

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