Mounting assembly for empennage of aircraft

Abstract

The invention relates to the technical field of aircrafts, in particular to a mounting assembly for an empennage of an aircraft, comprising: a connecting assembly comprising a connecting hole and a connecting pin; the limiting assembly comprises a limiting screw rod, an inserting groove, a threaded sleeve and a non-return assembly; and the pre-tightening assembly is connected with the threaded sleeve and the non-return assembly, and when the threaded sleeve rotates, the pre-tightening assembly can be driven to move to apply pre-tightening force to the non-return assembly. In the whole using process, a limiting screw rod and a connecting pin only need to be inserted into an inserting groove and a connecting hole correspondingly, then fixation can be automatically kept under the action of a limiting assembly and a pre-tightening assembly, and a user only needs to hold a fuselage and an empennage mounting part of the aircraft with the two hands to conduct opposite insertion operation; the three parts do not need to be operated by two hands at the same time, the operation process is greatly simplified, and use is more convenient.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a mounting assembly for an aircraft tail wing. Background Art

[0002] An aircraft refers to any device or machine that can fly in the atmosphere. Depending on its purpose, it can be roughly divided into military aircraft and civilian aircraft. Among civilian aircraft, there are more common airplanes, and some aircraft used for special purposes such as scientific research and meteorological detection.

[0003] In the manufacturing process of the above-mentioned aircraft, the assembly of the tail wing and the fuselage is an important process step. For some smaller aircraft, it is generally assembled manually. In this process, there will be corresponding installation components between the tail wing and the fuselage, and the assembly can be achieved by manually aligning and tightening the installation components.

[0004] At present, most of the installation components on conventional small aircraft are connected by means of positioning pins and lock buckles. This structure is simple to use and manufacture, and is very convenient, but it still has certain shortcomings:

[0005] During the installation process, the tail wing needs to be aligned with the fuselage first to align the lock, and then the lock is locked. This process is rather cumbersome. If one person is operating, one hand is required to hold the fuselage and tail wing steady at the same time, and the other hand to lock the lock, which is equivalent to using two hands to control three scattered parts. The operation is difficult and usually requires help from others or related auxiliary equipment. Overall, the installation and use still have certain inconveniences. Summary of the invention

[0006] In order to overcome the deficiencies of the prior art, the present invention provides a mounting assembly for an aircraft tail wing.

[0007] In order to solve the above technical problems, the present invention provides the following technical solutions: a mounting assembly for an aircraft tail wing, comprising: a connecting assembly, the connecting assembly comprising a connecting hole and a connecting pin, the connecting hole being arranged at the end of the fuselage of the aircraft, the connecting pin being fixedly mounted at the end of the tail wing mounting portion of the aircraft, and the connecting pin being insertable into the connecting hole; a limiting assembly, the limiting assembly comprising a limiting screw, a slot, a threaded sleeve and a non-return assembly, the limiting screw being fixedly mounted at the end of the tail wing mounting portion of the aircraft, the slot being arranged at the end of the fuselage of the aircraft, the threaded sleeve being rotatably mounted in the slot, and the threaded sleeve being threadably connected to the limiting screw, and the threaded connection between the threaded sleeve and the limiting screw being not self-locking, the non-return assembly being connected to the threaded sleeve, and under the action of the non-return assembly, the threaded sleeve can only rotate when the limiting screw moves toward the slot; a pre-tightening assembly, the pre-tightening assembly being connected to the threaded sleeve and the non-return assembly, and when the threaded sleeve rotates, the pre-tightening assembly can be driven to move to apply a pre-tightening force to the non-return assembly.

[0008] As a preferred technical solution of the present invention, the length of the connecting pin is smaller than the length of the limiting screw, and the connecting pin can be inserted into the connecting hole only when the limiting screw cooperates with the threaded sleeve.

[0009] As a preferred technical solution of the present invention, the check assembly includes a ratchet, a pawl, a coil spring and a limit ring. A cavity is opened inside the body, the limit ring is fixedly installed in the cavity, and the threaded sleeve is rotatably installed in the middle of the limit ring. The ratchet is fixedly installed on the surface of the threaded sleeve, the pawl is rotatably set in the cavity, and the pawl is connected to the preload assembly, the coil spring is connected to the pawl, and the pawl is clamped with the ratchet under the action of the coil spring.

[0010] As a preferred technical solution of the present invention, the check assembly also includes a push rod, a first sliding cavity, a limit plate and a compression spring. The first sliding cavity is opened in the middle of the fuselage. The push rod is slidably installed in the first sliding cavity, and the push rod can push the pawl to rotate to separate from the ratchet. The limit plate is slidably installed in the first sliding cavity and fixedly connected to the push rod. The compression spring is connected between the side wall of the first sliding cavity and the limit plate, and the limit plate drives the push rod away from the pawl under the action of the compression spring.

[0011] As a preferred technical solution of the present invention, the check assembly also includes a second sliding cavity and a button. The second sliding cavity is opened on the surface of the fuselage. The button is slidably installed in the second sliding cavity, and the end of the button penetrates into the first sliding cavity and is fixedly connected to the end of the push rod. At the same time, the end surface of the button away from the push rod and the surface of the fuselage are a smooth transition surface.

[0012] As a preferred technical solution of the present invention, the preload assembly includes a guide groove, a preload spring, a slider, a load-bearing shaft and a transmission assembly. The guide groove is fixedly installed inside the cavity, the slider is slidably installed in the guide groove, the preload spring is connected between the slider and the inner wall of the guide groove, the load-bearing shaft is fixedly installed on the side of the slider, the pawl is rotatably sleeved on the load-bearing shaft, the coil spring is sleeved on the load-bearing shaft, and the inner ring and outer ring of the coil spring are respectively fixedly connected to the load-bearing shaft and the pawl, the transmission assembly is connected between the ratchet and the load-bearing shaft, and the rotation of the ratchet can drive the load-bearing shaft to move through the transmission assembly.

[0013] As a preferred technical solution of the present invention, the transmission assembly includes a gear, which is rotatably installed in the cavity and meshes with the ratchet. When the gear rotates, the bearing shaft can be moved to drive the slider to slide in the guide groove.

[0014] As a preferred technical solution of the present invention, when the limiting screw is inserted into the threaded sleeve, the threaded sleeve will drive the gear to rotate through the ratchet, and the gear will drive the pawl to slide away from the ratchet through the load-bearing shaft and disengage from the ratchet.

[0015] Compared with the prior art, the present invention can achieve the following beneficial effects:

[0016] 1. During the entire use process, you only need to insert the limit screw and connecting pin into the slot and the connecting hole respectively, and then they will be automatically fixed under the action of the limit assembly and the pre-tightening assembly. The user only needs to hold the fuselage and tail wing mounting part of the aircraft with both hands to perform the insertion operation. There is no need to operate the three parts with both hands at the same time, which greatly simplifies the operation process and is more convenient to use.

[0017] 2. During use, in the limit assembly and preload assembly, the pawl will automatically find the best engagement tooth position with the ratchet when the fuselage and the tail wing mounting part are in contact, thereby avoiding structural loosening. This process will also automatically store energy for the preload spring so that the pawl exerts force on the ratchet, thereby causing the threaded sleeve to generate preload force, which can further avoid loosening and ensure the stability of the structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention;

[0019] Figure 2 It is a schematic diagram of the internal structure of the present invention;

[0020] Figure 3 For the present invention Figure 2 The enlarged structural diagram at A in the middle;

[0021] Figure 4 This is a schematic diagram of the split structure of the present invention from a first viewing angle;

[0022] Figure 5 For the present invention Figure 4 The enlarged structural diagram at B in the middle;

[0023] Figure 6 For the present invention Figure 5 The enlarged structural diagram at C in the middle;

[0024] Figure 7 It is a schematic diagram of the split structure of the present invention from a second viewing angle;

[0025] Figure 8 For the present invention Figure 7 Enlarged structural diagram at D in the middle.

[0026] Among them: 1. connecting hole; 2. connecting pin; 3. fuselage; 4. tail wing mounting part; 5. limiting screw; 6. slot; 7. threaded sleeve; 8. ratchet; 9. pawl; 10. coil spring; 11. limiting ring; 12. cavity; 13. push rod; 14. first sliding cavity; 15. limiting plate; 16. compression spring; 17. second sliding cavity; 18. button; 19. guide groove; 20. preload spring; 21. slider; 22. load-bearing shaft; 23. gear. DETAILED DESCRIPTION

[0027] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention is further described below in conjunction with specific embodiments, but the following embodiments are only preferred embodiments of the present invention, not all. Based on the embodiments in the implementation mode, other embodiments obtained by those skilled in the art without creative work all belong to the protection scope of the present invention. The experimental methods in the following embodiments, unless otherwise specified, are conventional methods, and the materials, reagents, etc. used in the following embodiments, unless otherwise specified, can all be obtained from commercial channels.

[0028] Embodiment: Figure 1-8 As shown, a mounting assembly for an aircraft tail wing comprises: a connecting assembly, the connecting assembly comprises a connecting hole 1 and a connecting pin 2, the connecting hole 1 is arranged at the end of a fuselage 3 of the aircraft, the connecting pin 2 is fixedly mounted at the end of a tail wing mounting portion 4 of the aircraft, and the connecting pin 2 can be inserted into the connecting hole 1; a limiting assembly, the limiting assembly comprises a limiting screw 5, a slot 6, a threaded sleeve 7 and a non-return assembly, the limiting screw 5 is fixedly mounted at the end of the tail wing mounting portion 4 of the aircraft, the slot 6 is arranged at the end of a fuselage 3 of the aircraft, the threaded sleeve 7 is rotatably mounted in the slot 6, and the threaded sleeve 7 can be threadedly connected with the limiting screw 5, and the threaded connection between the threaded sleeve 7 and the limiting screw 5 is not self-locking, the non-return assembly is connected with the threaded sleeve 7, and under the action of the non-return assembly, the threaded sleeve 7 can only rotate when the limiting screw 5 moves toward the slot 6; a pre-tightening assembly, the pre-tightening assembly is connected with the threaded sleeve 7 and the non-return assembly, and when the threaded sleeve 7 rotates, the pre-tightening assembly can be driven to move to apply a pre-tightening force to the non-return assembly.

[0029] The connecting pin 2 can be inserted into the connecting hole 1 only when the length of the connecting pin 2 is smaller than the length of the limiting screw 5 and the limiting screw 5 cooperates with the threaded sleeve 7. In this way, a good cooperation between the limiting screw 5 and the threaded sleeve 7 can be ensured, thereby ensuring the connection between the fuselage 3 and the tail mounting part 4.

[0030] The non-return assembly includes a ratchet 8, a pawl 9, a coil spring 10 and a limit ring 11. A cavity 12 is provided inside the body 3. The limit ring 11 is fixedly installed in the cavity 12, and the threaded sleeve 7 is rotatably installed in the middle of the limit ring 11. The ratchet 8 is fixedly installed on the surface of the threaded sleeve 7. The pawl 9 is rotatably set in the cavity 12, and the pawl 9 is connected to the preload assembly, and the coil spring 10 is connected to the pawl 9. The pawl 9 is engaged with the ratchet 8 under the action of the coil spring 10.

[0031] In this way, the limiting screw 5 can only be inserted into the threaded sleeve 7 in one direction, so that the limiting screw 5 is automatically fixed after being inserted into the slot 6, thereby facilitating the operation of the user.

[0032] The check assembly also includes a push rod 13, a first sliding cavity 14, a limit plate 15 and a compression spring 16. The first sliding cavity 14 is opened in the middle of the fuselage 3. The push rod 13 is slidably installed in the first sliding cavity 14, and the push rod 13 can push the pawl 9 to rotate to separate from the ratchet 8. The limit plate 15 is slidably installed in the first sliding cavity 14 and is fixedly connected to the push rod 13. The compression spring 16 is connected between the side wall of the first sliding cavity 14 and the limit plate 15, and the limit plate 15 drives the push rod 13 away from the pawl 9 under the action of the compression spring 16.

[0033] In this way, the limit on the threaded sleeve 7 can be released by sliding the push rod 13 to push open the pawl 9, so that the user can directly pull out the limit screw 5 to separate the fuselage 3 from the tail wing mounting part 4.

[0034] The check assembly also includes a second sliding cavity 17 and a button 18. The second sliding cavity 17 is opened on the surface of the fuselage 3. The button 18 is slidably installed in the second sliding cavity 17, and the end of the button 18 penetrates into the first sliding cavity 14 and is fixedly connected to the end of the push rod 13. At the same time, the end surface of the button 18 away from the push rod 13 is a smooth transition surface with the surface of the fuselage 3. In this way, the push rod 13 can be driven to slide by simply pressing the button 18.

[0035] The preload assembly includes a guide groove 19, a preload spring 20, a slider 21, a load-bearing shaft 22 and a transmission assembly. The guide groove 19 is fixedly installed inside the cavity 12, the slider 21 is slidably installed in the guide groove 19, the preload spring 20 is connected between the slider 21 and the inner wall of the guide groove 19, the load-bearing shaft 22 is fixedly installed on the side of the slider 21, the pawl 9 is rotatably sleeved on the load-bearing shaft 22, the coil spring 10 is sleeved on the load-bearing shaft 22, and the inner ring and outer ring of the coil spring 10 are fixedly connected to the load-bearing shaft 22 and the pawl 9 respectively, the transmission assembly is connected between the ratchet 8 and the load-bearing shaft 22, and the rotation of the ratchet 8 can drive the load-bearing shaft 22 to move through the transmission assembly.

[0036] In this way, when the threaded sleeve 7 rotates, the load-bearing shaft 22 can be driven to move through the transmission assembly, thereby driving the slider 21 to slide in the guide groove 19. At this time, the sliding of the load-bearing shaft 22 will also synchronously drive the pawl 9 to move. Afterwards, under the action of the preload spring 20, the slider 21 is reset, driving the pawl 9 to re-engage with the ratchet 8. In this process, the pawl 9 will find a suitable tooth position with the ratchet 8 again, thereby ensuring that when the tail wing mounting part 4 is in contact with the end of the fuselage 3, the pawl 9 can be just stuck in the tooth groove of the ratchet 8 to achieve compactness after fixation. At the same time, under the action of the preload spring 20, a preload force can also be applied to the pawl 9 to ensure that the threaded sleeve 7 always drives the limit screw 5 to be inserted into the direction of the slot 6, thereby further ensuring the stability of the structure.

[0037] The transmission assembly includes a gear 23, which is rotatably installed in the cavity 12 and meshes with the ratchet 8. When the gear 23 rotates, the bearing shaft 22 can be moved to drive the slider 21 to slide in the guide groove 19. In this way, the rotation of the threaded sleeve 7 will drive the gear 23 to rotate, and the rotation of the gear 23 will move the bearing shaft 22.

[0038] When the limiting screw 5 is inserted into the threaded sleeve 7 , the threaded sleeve 7 drives the gear 23 to rotate through the ratchet 8 , and the gear 23 drives the pawl 9 to slide away from the ratchet 8 through the bearing shaft 22 and disengage from the ratchet 8 .

[0039] Therefore, the complete usage process is to first hold the fuselage 3 and the tail mounting part 4 of the aircraft with both hands respectively, and then align the limit screw 5 with the slot 6 and insert it. During the insertion process, the fuselage 3 or the tail mounting part 4 can be rotated so that the limit screw 5 and the threaded sleeve 7 can cooperate. At this time, ensure that the connecting pin 2 is aligned with the connecting hole 1, and continue to push the limit screw 5 to insert it, so that the connecting pin 2 is inserted into the connecting hole 1 until the end of the tail mounting part 4 is in contact with the end of the fuselage 3. In the process of inserting the limit screw 5 into the slot 6, the threaded sleeve 7 will be driven to rotate continuously. However, when the limit screw 5 is pulled out in the direction away from the slot 6, the threaded sleeve 7 will not be able to rotate due to the engagement of the pawl 9 and the ratchet 8. In this way, the automatic fixation of the limit screw 5 can be completed.

[0040] When it is necessary to separate the fuselage 3 and the tail wing mounting part 4, it is only necessary to press the button 18, the button 18 will push the push rod 13 to move, and the push rod 13 will push the pawl 9 to rotate to separate from the ratchet 8. At this time, the threaded sleeve 7 loses its limit and can rotate freely, and then the limit screw 5 and the connecting pin 2 can be directly pulled out to achieve the separation of the fuselage 3 and the tail wing mounting part 4.

[0041] During the process of inserting the limiting screw 5 into the slot 6, the rotation of the threaded sleeve 7 will also drive the gear 23 to rotate. The rotation of the gear 23 will drive the load-bearing shaft 22 to move, thereby driving the slider 21 to slide in the guide groove 19. At this time, the sliding of the load-bearing shaft 22 will also synchronously drive the pawl 9 to move. Afterwards, under the action of the preload spring 20, the slider 21 is reset, driving the pawl 9 to re-engage with the ratchet 8. During this process, the pawl 9 will find a suitable tooth position with the ratchet 8 again, thereby ensuring that when the tail wing mounting part 4 is in contact with the end of the fuselage 3, the pawl 9 can be just stuck in the tooth groove of the ratchet 8 to achieve compactness after fixation. At the same time, under the action of the preload spring 20, a preload force can also be applied to the pawl 9 to ensure that the threaded sleeve 7 always drives the limiting screw 5 to be inserted into the slot 6. Force is further guaranteed to ensure the stability of the structure.

[0042] It should be noted that the sliding direction of the slider 21 in the guide groove 19 is perpendicular to the direction of the force applied by the ratchet 8 , so that the bearing shaft 22 can only be moved by the gear 23 and cannot be driven in the reverse direction by the ratchet 8 .

[0043] In summary, during the entire use process, it is only necessary to insert the limit screw 5 and the connecting pin 2 into the slot 6 and the connecting hole 1 respectively, and then they will be automatically kept fixed under the action of the limit assembly and the pre-tightening assembly. The user only needs to hold the fuselage 3 and the tail mounting part 4 of the aircraft with both hands to perform the insertion operation. There is no need to operate the three parts with both hands at the same time, which greatly simplifies the operation process and is more convenient to use.

[0044] In addition, during use, in the limit assembly and the pre-tightening assembly, the pawl 9 will automatically find the best engagement tooth position with the ratchet 8 when the fuselage 3 and the tail mounting part 4 are in contact, thereby avoiding structural loosening. This process will also automatically store energy for the pre-tightening spring 20 so that the pawl 9 exerts a force on the ratchet 8, thereby causing the threaded sleeve 7 to generate a pre-tightening force, which can further avoid loosening and ensure the stability of the structure.

[0045] The embodiments of the present invention are described in detail above with reference to the accompanying drawings, but the present invention is not limited thereto, and various changes can be made within the knowledge scope of technicians in the relevant technical field without departing from the purpose of the present invention.

Claims

1. A mounting assembly for an aircraft tail wing, characterized in that: include: A connection assembly, the connection assembly comprising a connection hole (1) and a connection pin (2), the connection hole (1) being opened at the end of a fuselage (3) of an aircraft, the connection pin (2) being fixedly mounted at the end of a tail wing mounting portion (4) of the aircraft, and the connection pin (2) being insertable into the connection hole (1); A limit assembly, the limit assembly comprising a limit screw (5), a slot (6), a threaded sleeve (7) and a non-return assembly, the limit screw (5) being fixedly mounted at the end of a tail wing mounting portion (4) of an aircraft, the slot (6) being arranged at the end of a fuselage (3) of the aircraft, the threaded sleeve (7) being rotatably mounted in the slot (6), and the threaded sleeve (7) being threadably connected to the limit screw (5), and the threaded connection between the threaded sleeve (7) and the limit screw (5) not being self-locking, the non-return assembly being connected to the threaded sleeve (7), and under the action of the non-return assembly, the threaded sleeve (7) can only rotate when the limit screw (5) moves toward the slot (6); A pre-tightening component is connected to the threaded sleeve (7) and the non-return component, and when the threaded sleeve (7) rotates, the pre-tightening component can be driven to move to apply a pre-tightening force to the non-return component.

2. The mounting assembly for an aircraft tail wing according to claim 1, characterized in that: The length of the connecting pin (2) is smaller than the length of the limiting screw (5), and the connecting pin (2) can only be inserted into the connecting hole (1) when the limiting screw (5) and the threaded sleeve (7) are matched.

3. The mounting assembly for an aircraft tail wing according to claim 1, characterized in that: The non-return assembly comprises a ratchet (8), a pawl (9), a coil spring (10) and a limiting ring (11); a cavity (12) is provided inside the body (3); the limiting ring (11) is fixedly installed in the cavity (12); and the threaded sleeve (7) is rotatably installed in the middle of the limiting ring (11); the ratchet (8) is fixedly installed on the surface of the threaded sleeve (7); the pawl (9) is rotatably arranged in the cavity (12); the pawl (9) is connected to the preload assembly; the coil spring (10) is connected to the pawl (9); and the pawl (9) is engaged with the ratchet (8) under the action of the coil spring (10).

4. The mounting assembly for an aircraft tail wing according to claim 3, characterized in that: The non-return assembly further comprises a push rod (13), a first sliding cavity (14), a limit plate (15) and a compression spring (16). The first sliding cavity (14) is arranged in the middle of the body (3). The push rod (13) is slidably mounted in the first sliding cavity (14), and the push rod (13) can push the pawl (9) to rotate to separate from the ratchet (8). The limit plate (15) is slidably mounted in the first sliding cavity (14) and is fixedly connected to the push rod (13). The compression spring (16) is connected between the side wall of the first sliding cavity (14) and the limit plate (15), and the limit plate (15) drives the push rod (13) away from the pawl (9) under the action of the compression spring (16).

5. The mounting assembly for an aircraft tail wing according to claim 4, characterized in that: The non-return assembly further comprises a second sliding cavity (17) and a button (18). The second sliding cavity (17) is opened on the surface of the body (3). The button (18) is slidably installed in the second sliding cavity (17). The end of the button (18) penetrates into the first sliding cavity (14) and is fixedly connected to the end of the push rod (13). At the same time, the end surface of the button (18) away from the push rod (13) and the surface of the body (3) form a smooth transition surface.

6. A mounting assembly for an aircraft tail wing according to any one of claims 3 to 5, characterized in that: The preload assembly comprises a guide groove (19), a preload spring (20), a slider (21), a bearing shaft (22) and a transmission assembly. The guide groove (19) is fixedly installed inside the cavity (12). The slider (21) is slidably installed in the guide groove (19). The preload spring (20) is connected between the slider (21) and the inner wall of the guide groove (19). The bearing shaft (22) is fixedly installed on the side of the slider (21). The pawl (9) is rotatably sleeved on the bearing shaft (22). The coil spring (10) is sleeved on the bearing shaft (22). The inner ring and the outer ring of the coil spring (10) are respectively fixedly connected to the bearing shaft (22) and the pawl (9). The transmission assembly is connected between the ratchet (8) and the bearing shaft (22). The rotation of the ratchet (8) can drive the bearing shaft (22) to move through the transmission assembly.

7. The mounting assembly for an aircraft tail wing according to claim 6, characterized in that: The transmission assembly comprises a gear (23) which is rotatably mounted in the cavity (12) and meshes with the ratchet (8). When the gear (23) rotates, it can move the bearing shaft (22) to drive the slider (21) to slide in the guide groove (19).

8. The mounting assembly for an aircraft tail wing according to claim 7, characterized in that: When the limiting screw (5) is inserted into the threaded sleeve (7), the threaded sleeve (7) drives the gear (23) to rotate through the ratchet (8), and the gear (23) drives the ratchet pawl (9) to slide in a direction away from the ratchet (8) and disengage from the ratchet (8) through the bearing shaft (22).

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