A control surface connection device, an aircraft tail fin, and an aircraft

Abstract

This invention discloses a control surface connection device, an aircraft tail fin, and an aircraft, belonging to the technical field of aircraft control surface and stabilizer installation. This invention solves the problem that existing control surface and stabilizer connections require opening mounting holes in the control surface, resulting in a reduction in the aerodynamic force-bearing area of ​​the control surface. The control surface connection device of this invention includes a connector, an axial limiting member, a rotating stud, and a limiting connector; the connector has an internal mounting cavity; the axial limiting member and the rotating stud are disposed within the mounting cavity; the limiting connector is disposed outside the connector; the axial limiting member is connected to the connector; one end of the rotating stud is connected to the axial limiting member, and the other end protrudes from the connector and connects to the limiting connector. This invention eliminates the need for openings on the control surface, ensuring control surface integrity and increasing control surface aerodynamic efficiency.

Description

Technical Field

[0001] This invention relates to the field of aircraft control surface and stabilizer installation technology, and more particularly to a control surface connection device, an aircraft tail fin, and an aircraft. Background Technology

[0002] The connection between the aircraft stabilizer and control surface is one of the key aspects of aircraft design. Existing stabilizer-control surface connections typically consist of single-ear, double-ear, and mating bolts. The advantage is simplicity and ease of maintenance, but the disadvantage is that an opening needs to be made in the control surface to install the bolts and achieve the connection between the aircraft stabilizer and control surface. However, openings in the control surface compromise the integrity of the control surface, reduce the aerodynamic stress area, and also result in an unsightly control surface appearance. Summary of the Invention

[0003] Based on the above analysis, the present invention aims to provide a control surface connection device, an aircraft tail fin, and an aircraft to solve the problem that when connecting the existing control surface to the stabilizer, mounting holes need to be opened on the control surface, resulting in a reduction in the aerodynamic force-bearing area of ​​the control surface.

[0004] The objective of this invention is mainly achieved through the following technical solutions:

[0005] In a first aspect, the present invention provides a rudder surface connection device, including a connector, an axial limiting member, a rotating stud, and a limiting connector;

[0006] The connector has an internal mounting cavity;

[0007] The axial limiting component and the rotating stud are disposed inside the mounting cavity;

[0008] The connector is restricted to be located outside the joint;

[0009] The axial limiting component is connected to the connector;

[0010] One end of the rotating stud is connected to the axial limiting component, and the other end passes through the connector and is connected to the limiting connector.

[0011] Furthermore, the joint includes a vertical support, an inclined support, and a housing;

[0012] The mounting cavity is formed by the vertical support, the diagonal support, and the outer shell.

[0013] Furthermore, the axial limiting member includes a horizontal portion and a suspended portion fixedly connected to the horizontal portion;

[0014] The horizontal section is connected to the outer casing;

[0015] The suspended part is connected to the rotating stud.

[0016] Furthermore, grooves are provided on the inclined support member;

[0017] The bottom end of the suspended part matches the groove and is set inside the groove.

[0018] Furthermore, the axial limiting component also includes a fixing component and a pin;

[0019] The fastener is set on the top surface of the horizontal part and engages with the slot provided on the outer shell;

[0020] A first protrusion is provided on the fastener, and a second protrusion matching the first protrusion is provided on the outer shell. The first protrusion and the second protrusion are connected by a pin.

[0021] Furthermore, it also includes a limiting cover and a spring;

[0022] The spring is positioned between the limiting cover and the axial limiting element.

[0023] Furthermore, it also includes spherical bearings;

[0024] The spherical plain bearing transitions onto the joint;

[0025] The rotating stud passes through the spherical bearing and connects to the limiting connector.

[0026] In a second aspect, the present invention also provides an aircraft tail fin, including control surfaces, a stabilizer, and a control surface connecting device;

[0027] The rudder surface connection device is the rudder surface connection device described in the first aspect;

[0028] The control surface is connected to the stabilizer via the control surface connection device.

[0029] Furthermore, the aircraft's tail fin can be a vertical tail, a horizontal tail, or a V-tail.

[0030] Thirdly, the present invention also provides an aircraft, including an aircraft body and an aircraft tail fin; the aircraft tail fin is the aircraft tail fin described in the second aspect;

[0031] The tail fin of the aircraft is mounted on the main body of the aircraft.

[0032] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0033] 1. In the rudder surface connection device of the present invention, the connector is fixedly connected to the rudder surface and the axial limiting member and the rotating stud are located in the mounting cavity of the connector. By setting the axial limiting member, the rotating stud and the limiting connector, the rudder surface is connected to the stabilizing surface. By setting the axial limiting member and the rotating stud, the rudder surface can rotate along the central axis of the rotating stud. Compared with the existing structure that connects the rudder surface and the stabilizing surface by a single ear or a double ear, the rudder surface connection device of the present invention does not require an opening on the rudder surface, thus ensuring the integrity of the rudder surface, increasing the aerodynamic efficiency of the rudder surface, and making the rudder surface more aesthetically pleasing.

[0034] 2. In the rudder surface connection device of the present invention, the vertical support of the joint is fixedly connected to the rudder surface frame, and the outer shell is fixedly connected to the rudder surface skin, avoiding openings on the rudder surface, realizing the connection between the rudder surface and the stabilizer, ensuring the integrity of the rudder surface, and increasing the aerodynamic efficiency of the rudder surface.

[0035] 3. In the rudder surface connecting device of the present invention, the connection between the axial propulsion component and the rotating stud, the connection between the axial propulsion component and the joint, the connection between the rotating stud and the limiting connector, and the connection between the limiting cover and the joint are all screwed connections, which are easy to disassemble and install.

[0036] 4. The control surface connection device of the present invention is provided with a limiting connector, and the rotating stud and the limiting connector further limit the position of the rotating stud, ensuring the reliability and stability of the connection between the control surface and the stabilizer, and further ensuring the safety of the aircraft during flight.

[0037] 5. The control surface connection device of the present invention can be used to connect the control surfaces and stabilizers of various aircraft, including helicopters, fixed-wing aircraft and tiltrotor aircraft.

[0038] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages may become apparent from the description or be learned by practicing the invention. The objects and other advantages of this invention can be realized and obtained through the embodiments described and the accompanying drawings, which are particularly pointed out. Attached Figure Description

[0039] The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0040] Figure 1 This is an exploded view of the structure of a rudder surface connection device according to the present invention;

[0041] Figure 2 for Figure 1 A schematic diagram showing the connection between the central axis limiting component and the limiting cover;

[0042] Figure 3 This is a schematic diagram of the structure of the rudder surface connection device, the stabilizer joint, and the rudder surface after connection according to the present invention;

[0043] Figure 4 for Figure 3 Explosion-proof diagram of the structure;

[0044] Figure 5 This is a schematic diagram illustrating the process of connecting a rudder surface to a stabilizer joint using a rudder surface connection device according to the present invention.

[0045] Figure 6 This is a schematic diagram of the structure of a vertical tail fin according to the present invention;

[0046] Figure 7 This is a schematic diagram of the structure of a horizontal tail fin according to the present invention;

[0047] Figure label:

[0048] 1-Rudder surface connection device; 2-Rudder surface; 3-Stabilized surface connector; 4-Vertical stabilizer; 5-Rudder; 6-Horizontal stabilizer; 7-Elevator;

[0049] 11-Connector, 12-Axial limiting component, 13-Rotating stud, 14-Restricting connector, 15-Limiting cover, 16-Spherical bearing, 17-Spring;

[0050] 111-Mounting cavity, 112-Vertical support, 113-Diagonal support, 114-Outer shell;

[0051] 1141 - Second bump;

[0052] 121-Horizontal part, 122-Suspended part, 123-Fixed part, 124-Pin;

[0053] 1231 - First bump. Detailed Implementation

[0054] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0055] Example 1

[0056] A specific embodiment of the present invention discloses a rudder surface connecting device 1, referring to... Figure 1 It includes a connector 11, an axial limiting member 12, a rotating stud 13, and a limiting connector 14; the connector 11 has an internal mounting cavity 111; the axial limiting member 12 and the rotating stud 13 are disposed in the mounting cavity 111; the axial limiting member 12 is connected to the connector 11; one end of the rotating stud 13 is connected to the axial limiting member 12; the other end protrudes from the connector 11 and is connected to the limiting connector 14.

[0057] In the control surface connection device of this embodiment, the connector 11 is fixedly connected to the control surface, and the axial limiting member 12 and the rotating stud 13 are located in the mounting cavity 111 of the connector 11. By setting the axial limiting member 12, the rotating stud 13 and the limiting connector 14, the control surface is connected to the stabilizing surface. By setting the axial limiting member 12 and the rotating stud 13, the control surface can rotate along the central axis of the rotating stud 13. Compared with the existing structure that connects the control surface and the stabilizing surface by a single ear or a double ear, it does not require an opening on the control surface, thus ensuring the integrity of the control surface and increasing the aerodynamic efficiency of the control surface.

[0058] The rudder surface is mounted on the stabilizer surface using the rudder surface connection device 1 in this embodiment, as shown in the reference. Figure 3 and Figure 4 Specifically, the end of the rotating stud 13 that is to be connected to the limiting connector 14 passes through the connector 11 and the stabilizer connector 3 on the stabilizer in sequence and then connects to the limiting connector 14, thereby realizing the connection between the rudder surface and the stabilizer surface.

[0059] In this embodiment, considering the stability of the connection between the control surface and the stabilizer, two control surface connection devices are arranged opposite to each other at both ends of a control surface, and the connection between the control surface and the stabilizer is achieved through the two control surface connection devices.

[0060] Furthermore, referring to Figure 1 The connector 11 includes a vertical support 112, an inclined support 113, and a housing 114. The area enclosed by the vertical support 112, the inclined support 113, and the housing 114 is the mounting cavity.

[0061] Specifically, refer to Figure 1 The inclined support 113 is connected to the vertical support 112 to form a Y-shaped structure. The outer shell 114 is set outside the Y-shaped structure and is fixedly connected to the vertical support 112 and the inclined support 113. The opening of the Y-shaped structure and the outer shell 114 enclose the mounting cavity 111, which provides mounting space for the axial limiting member 12 and the rotating stud 13, so as to realize the rotation of the rudder surface around the central axis of the rotating stud 13. Compared with the existing structure that connects the rudder surface and the stabilizer through a single ear or a double ear, the space required for the connection structure is reduced.

[0062] Specifically, considering the smoothness of the rotation of the control surface 2, the side of the outer shell 114 facing the stabilizer is set to be arc-shaped to avoid the outer shell 114 from contacting the stabilizer, and further to avoid the outer shell 114 from colliding with the stabilizer during the rotation of the control surface.

[0063] Considering the consistency of rotation between the connector 11 and the rudder surface 2, both are relatively stationary. The connector 11 is connected to the rudder surface 2, specifically through a fixed connection, which can include adhesive bonding or screwing. Specifically, the outer shell 114 is fixedly connected to the skin of the rudder surface 2, and the vertical support 112 is fixedly connected to the frame of the rudder surface. This achieves the connection between the connector 11 and the rudder surface 2, allowing the rudder surface 2 to rotate about the rotating stud 13 as its axis of rotation.

[0064] In this embodiment, refer to Figure 1 Since the axial limiting member 12 and the rotating stud 13 are located in the mounting cavity 111 of the connector 11, the axial limiting member 12 and the rotating stud 13 do not protrude from the rudder surface, so there is no need to open holes on the rudder surface, thus maintaining the integrity of the rudder surface.

[0065] Furthermore, referring to Figure 1 and Figure 2 The rudder surface connection device also includes a limiting cover 15, which is disposed on the opening of the mounting cavity 111 and connected to the inclined support member 113 and the vertical support member 112. The mounting cavity 111 is enclosed by the vertical support member 112, the inclined support member 113, the outer shell 114, and the limiting cover 15. This provides installation space for the axial limiting member 12 and the rotating stud 13, and also limits the axial displacement of the axial limiting member 12 and the rotating stud 13 in the axial direction of the rotating stud 13.

[0066] Specifically, the axial limiting member 12 is connected to the limiting cover 15 for limiting, and the axial limiting member 12 is limited in the axial direction of the rotating stud 13 by the limiting cover 15.

[0067] Furthermore, referring to Figure 2 The axial limiting member 12 has an L-shaped structure, which includes a horizontal part 121 and a suspended part 122 connected to the horizontal part. The horizontal part 121 is connected to the outer shell 114; the suspended part 122 is connected to the rotating stud 13. The axial limiting member 12 is connected to the connector 11, which on the one hand provides fixed support for the rotating stud 13, and on the other hand, because the connector 11 is connected to the rudder surface, the axial limiting member 12 is relatively stationary with respect to the rudder surface, further enabling the rudder surface to rotate around the rotating stud 13 as the rotation axis.

[0068] Specifically, the connection between the axial limiting member 12 and the rotating stud 13 is a fixed connection, which is a screw connection, facilitating the installation and disassembly of the axial limiting member 12 and the rotating stud 13.

[0069] Specifically, a groove is provided on the inclined support member 113, and the bottom end of the suspended part 122 matches the groove and is set in the groove, thereby restricting the rotation of the suspended part, thereby restricting the rotation of the axial limiting member 12, so that the rudder surface and the axial limiting member 12 remain relatively stationary during the rotation of the rudder surface.

[0070] Specifically, refer to Figure 2 The axial limiting member 12 also includes a fixing member 123. The fixing member 123 is disposed on the top surface of the horizontal part 121. The outer shell 114 is provided with a slot that matches the fixing member 123. The fixing member 123 engages with the slot to block the slot. On the one hand, this ensures the integrity of the control surface and increases the aerodynamic efficiency of the control surface. On the other hand, because the fixing member 123 is fixed to the horizontal part of the axial limiting member 12, after the fixing member 123 is engaged in the slot, it restricts the axial rotation of the axial limiting member 12.

[0071] Specifically, refer to Figure 1 and Figure 2 The axial limiting member 12 also includes a pin 124. A first protrusion 1231 is provided on the fixing member 123, and a second protrusion 1141 matching the first protrusion 1231 is provided on the outer shell 114. The first protrusion 1231 and the second protrusion 1141 are connected by the pin 124, so that the axial limiting member 12 is fixedly connected to the connector 11, ensuring that the axial limiting member 12 and the connector 11 are relatively stationary during the rotation of the rudder surface. At the same time, since the connector 11 is fixedly connected to the rudder surface, the connector 11 and the rudder surface are relatively stationary, and thus the axial limiting member 12 and the rudder surface are relatively stationary, thereby achieving the rotation of the rudder surface around the rotating stud 13 as the rotation axis.

[0072] Furthermore, referring to Figure 1 The rudder surface connection device also includes a spherical bearing 16, which is fitted onto the joint 11. The rotating stud 13 and the spherical bearing 16 are in clearance fit to ensure the smooth rotation of the rotating stud 13 and further realize the stability and safety of the rudder surface rotation.

[0073] In this embodiment, refer to Figure 3 , Figure 4 and Figure 5 The rotating stud 13 passes through the spherical bearing 16 and is connected to the stabilizer joint 3.

[0074] Furthermore, referring to Figure 1 The rudder surface connection device also includes a spring 17, which is disposed between the limiting cover 15 and the axial limiting member 12 to increase the axial preload between the axial limiting member 12 and the limiting cover 15 in the axial direction of the rotating stud 13, and to ensure the fit between the axial limiting member 12 and the connector 11.

[0075] Specifically, a limiting seat matching the spring 17 is provided on the limiting cover 15, and a positioning post matching the spring 17 is provided on the side of the axial limiting member 12 facing the limiting cover 15. The limiting seat and the positioning post are arranged opposite to each other and a gap is provided between them. One end of the spring 17 is sleeved on the limiting seat and the other end is sleeved on the positioning post. The limiting seat and the positioning post limit the spring 17 so that the spring 17 is always located between the axial limiting member 12 and the limiting cover 15 during the use of the rudder surface connecting device, thereby increasing the axial preload between the axial limiting member 12 and the limiting cover 15 in the axial direction of the rotating stud 13.

[0076] The following further describes the connection process between the rudder surface and the stabilizer joint using the rudder surface connection device of the present invention.

[0077] Figure 5 A schematic diagram of the process of connecting a rudder surface to a stabilizer using the rudder surface connection device of the present invention is shown, such as... Figure 5 As shown, the process of connecting the rudder surface to the stabilizer using the rudder surface connection device of the present invention is as follows:

[0078] S1, the rotating stud 13, the axial limiting member 12 and the limiting cover 15 are connected in sequence;

[0079] S2, along the axial direction of the rotating stud 13, the axial limiting member 12 is pushed towards the direction of the stabilizing surface, so that the rotating stud 13 passes through the joint 11 and the stabilizing surface joint 3 in sequence and is connected to the limiting connecting member 14.

[0080] In S2, a spherical bearing 16 is provided on the connector 11. The spherical bearing 16 is clearance-fitted with the rotating stud 13. The rotating stud 13 passes through the spherical bearing 16 and the stabilizer connector 3 in sequence and is then connected to the limiting connector 14.

[0081] In S2, during the connection or disassembly of the rotating stud 13 and the stabilizer joint 3, the axial pusher 12 drives the rotating stud 13 to move along the axial direction of the rotating stud 13, thereby realizing the connection or disassembly of the rotating stud 13 and the stabilizer joint 3.

[0082] In S2, after the limiting connector 14 is connected to the rotating stud 13, the axial movement of the limiting rotating stud 13 is restricted.

[0083] S3, the horizontal part of the axial limiting member 12 is fixedly connected to the joint 11, and the rudder surface rotates around the rotating stud 13 as the rotation axis.

[0084] The axial limiting member 12 includes a horizontal part 121 and a suspended part 122, S3, specifically:

[0085] S31, the fastener 123 on the horizontal part 121 is engaged in the slot on the outer shell of the connector 11;

[0086] S32, using the pin 124, the first protrusion 1321 on the fixing member 123 is connected to the second protrusion 1141 on the outer shell, thus completing the connection between the axial limiting member 12 and the connector 11.

[0087] Because the fixing member 123 is engaged in the slot on the outer shell of the connector 11, and because the first protrusion 1321 and the second protrusion 1141 are fixedly connected, the rotation of the axial push member 12 is constrained by the fixing member 123, so that the axial push member 12 and the connector 11 are relatively stationary.

[0088] Thus, the connection between the rudder surface and the stabilizer is achieved through the rudder surface connection device, and at the same time, the rudder surface rotates around the rotating stud 13 as the rotation axis.

[0089] Example 2

[0090] Another specific embodiment of the present invention discloses an aircraft tail fin, including a control surface, a stabilizer, and a control surface connection device of embodiment 1; the control surface is connected to the stabilizer through the control surface connection device.

[0091] In this embodiment, the aircraft tail fin is a vertical tail fin, a horizontal tail fin, or a V-tail fin.

[0092] For example, when the aircraft's tail is a vertical tail, such as Figure 6 As shown, the vertical tail includes a vertical stabilizer 4, a rudder 5, and a rudder surface connecting device 1 as in Embodiment 1. The rudder 5 is connected to the vertical stabilizer 4 through the rudder surface connecting device 1; the rudder 5 also rotates relative to the vertical stabilizer 4 through the rudder surface connecting device 1.

[0093] It should be noted that the rudder 5 is connected to the vertical stabilizer 4 via the rudder surface connecting device 1, including:

[0094] The connection between the rudder 5 and the rudder surface connection device 1 is as follows: the rudder 5 includes a rudder frame and a rudder skin, and the rudder surface connection device 1 includes a joint, wherein the vertical support of the joint is fixedly connected to the rudder frame, and the outer shell of the joint is fixedly connected to the rudder skin, so that the joint is fixedly connected to the rudder. At this time, the joint and the rudder 5 are relatively stationary, and the joint and the rudder 5 move synchronously.

[0095] The connection between the vertical stabilizer 4 and the rudder surface connecting device 1 is specifically as follows: the rotating stud 13 in the rudder surface connecting device 1 passes through the outer shell of the connector and the stabilizer connector on the vertical stabilizer 4 in sequence, and then connects with the limiting connector to achieve the connection between the rudder surface connecting device 1 and the vertical stabilizer 4.

[0096] Among them, the stabilizer joint on the vertical stabilizer 4 provides support for the rudder surface connection device 1 during the connection process between the rudder 5 and the vertical stabilizer 4, specifically providing support for the rotating stud 13.

[0097] It should be noted that, through the rudder surface connecting device 1, the rudder 5 rotates relative to the vertical stabilizer 4, specifically as follows:

[0098] In the rudder surface connection device 1, the rotating stud 13 passes sequentially through the outer shell of the connector, the stabilizing surface connector on the vertical stabilizing surface 4, and then connects to the limiting connector. The rotating stud 13 is rotatably connected to the stabilizing surface connector on the vertical stabilizing surface 4. Specifically, firstly, because the rotating stud 13 is fixedly connected to the axial limiting component, the rotating stud 13 and the axial limiting component are relatively stationary; secondly, because the axial limiting component is fixedly connected to the connector, the axial limiting component and the connector are relatively stationary; thirdly, because the connector is fixedly connected to the rudder 5, the connector and the rudder 5 are relatively stationary, which is equivalent to the rotating stud 13 and the rudder 5 being relatively stationary; finally, because the rotating stud 13 is rotatably connected to the stabilizing surface connector on the vertical stabilizing surface 4, it is equivalent to the rudder 5 being rotatably connected to the stabilizing surface connector on the vertical stabilizing surface 4 via the rotating stud 13. When the rotating stud 13 rotates, it drives the rudder 5 to rotate relative to the vertical stabilizing surface 4.

[0099] Considering the smoothness of the rotation of the rotating stud 13, the rotating stud 13 is fitted with the stabilizer joint of the vertical stabilizer 4 with a clearance.

[0100] Considering the connection between the rotating stud 13 and the stabilizer connector on the vertical stabilizer 4, a through hole is provided on the side of the connector facing the stabilizer connector, and the rotating stud 13 passes through the through hole. Therefore, the setting of the through hole has little effect on the aerodynamic efficiency of the control surface.

[0101] When the rudder 5 is connected to the vertical stabilizer 4 through the rudder surface connection device 1, it is not necessary to open the rudder surface of the rudder 5, thus ensuring the integrity of the rudder surface and increasing the aerodynamic efficiency of the rudder surface.

[0102] For example, when the aircraft's tail is a horizontal tail, such as Figure 7 As shown, the horizontal tail includes a horizontal stabilizer 6, an elevator 7, and a control surface connecting device 1 as described in Embodiment 1. The elevator 7 is rotatably connected to the horizontal stabilizer 6 through the control surface connecting device 1.

[0103] It should be noted that the elevator 7 is connected to the horizontal stabilizer 6 via the control surface connection device 1, including:

[0104] The connection between the elevator 7 and the control surface connection device 1 is as follows: the elevator 7 includes an elevator frame and an elevator skin, and the control surface connection device 1 includes a joint, wherein the vertical support of the joint is fixedly connected to the elevator frame, and the outer shell of the joint is fixedly connected to the elevator skin, so that the joint is fixedly connected to the elevator 7. At this time, the joint and the elevator 7 are relatively stationary, so that the joint and the elevator 7 move synchronously.

[0105] The connection between the horizontal stabilizer 6 and the rudder surface connecting device 1 is specifically as follows: the rotating stud 13 in the rudder surface connecting device 1 passes through the outer shell of the connector and the stabilizer connector on the horizontal stabilizer 6 in sequence, and then connects with the limiting connector to achieve the connection between the rudder surface connecting device 1 and the horizontal stabilizer 6.

[0106] Among them, the stabilizer joint on the horizontal stabilizer 6 provides support for the rudder surface connection device 1 during the connection process between the elevator 7 and the horizontal stabilizer 6, specifically providing support for the rotating stud 13 in the rudder surface connection device 1.

[0107] It should be noted that, through the control surface connecting device 1, the elevator 7 rotates relative to the horizontal stabilizer 6, specifically as follows:

[0108] In the rudder surface connection device 1, the rotating stud 13 passes sequentially through the outer shell of the connector and the stabilizing connector on the horizontal stabilizing surface 6 before connecting to the limiting connector. The rotating stud 13 is rotatably connected to the stabilizing connector on the horizontal stabilizing surface 6. Since the rotating stud 13 is fixedly connected to the axial limiting component and is relatively stationary, the axial limiting component is relatively stationary to the connector, and the connector is relatively stationary to the elevator 7. This is equivalent to the rotating stud 13 being relatively stationary to the elevator 7. Furthermore, since the rotating stud 13 is rotatably connected to the stabilizing connector on the horizontal stabilizing surface 6, it is equivalent to the elevator 7 being rotatably connected to the stabilizing connector on the horizontal stabilizing surface 6 through the rotating stud 13. When the rotating stud 13 rotates, it drives the elevator 7 to rotate relative to the horizontal stabilizing surface 6.

[0109] To ensure the smooth rotation of the rotating stud 13, the rotating stud 13 is fitted with a clearance joint to the horizontal stabilizer 6.

[0110] Considering the connection between the rotating stud 13 and the stabilizer connector on the horizontal stabilizer 6, a through hole is provided on the side of the connector facing the stabilizer connector, and the rotating stud 13 passes through the through hole. Therefore, the setting of the through hole has little impact on the aerodynamic efficiency of the control surface.

[0111] When the elevator 7 is connected to the horizontal stabilizer 6 through the control surface connection device 1, it is not necessary to open the control surface of the elevator 7, thus ensuring the integrity of the control surface of the elevator 7 and increasing the aerodynamic efficiency of the control surface of the elevator 7.

[0112] For example, when the aircraft tail is a V-tail, the V-tail includes a V-tail stabilizer, a V-tail control surface, and a control surface connecting device 1 in embodiment 1. The V-tail control surface is connected to the V-tail stabilizer through the control surface connecting device 1. The V-tail control surface also rotates relative to the V-tail stabilizer through the control surface connecting device 1.

[0113] The connection between the control surface connecting device 1 and the V-tail control surface is a fixed connection. Specifically, the vertical support of the joint in the control surface connecting device 1 is fixedly connected to the frame of the V-tail control surface, and the outer shell of the joint is fixedly connected to the skin of the V-tail control surface.

[0114] The connection method between the control surface connecting device 1 and the V-tail stabilizer is as follows: the rotating stud 13 in the control surface connecting device 1 passes through the outer shell of the connector and the stabilizer connector on the V-tail stabilizer in sequence, and then connects with the limiting connector to achieve the rotational connection between the control surface connecting device 1 and the V-tail stabilizer.

[0115] Example 3

[0116] Another specific embodiment of the present invention discloses an aircraft, including an aircraft body and an aircraft tail fin as in Embodiment 2, wherein the aircraft tail fin is mounted on the aircraft body.

[0117] In this embodiment, the tail fin of the aircraft includes a control surface, a stabilizer, and a control surface connection device as described in Embodiment 1. Because the joint in the control surface connection device is fixedly connected to the control surface, and because the rotating stud 13 that passes through the inside of the joint passes through the stabilizer joint and is connected to the limiting connector, without opening on the control surface, the connection between the control surface and the stabilizer is achieved, ensuring the integrity of the control surface, increasing the aerodynamic efficiency of the control surface, and further enhancing the flight performance of the aircraft.

[0118] As can be seen from the above, the overall structure of the control surface connection device of the present invention is simple. It does not have an opening on the control surface, which can realize the connection between the control surface and the corresponding stabilizing surface. Furthermore, because there is no opening on the control surface, the integrity of the control surface is guaranteed, the aerodynamic efficiency of the control surface is increased, and the shape of the control surface is more aesthetically pleasing.

[0119] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A rudder surface connection device, characterized in that, Includes connectors, axial limiting components, rotating studs, and limiting connectors; The connector has an internal mounting cavity; the axial limiting member and the rotating stud are disposed within the mounting cavity; the limiting connector is disposed outside the connector; the axial limiting member is connected to the connector; one end of the rotating stud is connected to the axial limiting member, and the other end protrudes from the connector and is connected to the limiting connector. The connector includes a housing; the axial limiting member includes a horizontal part and a suspended part fixedly connected to the horizontal part, the horizontal part is connected to the housing, and the suspended part is connected to the rotating stud; The axial limiting component further includes a fixing component and a pin; the fixing component is disposed on the top surface of the horizontal part and engages with a slot provided on the outer shell; a first protrusion is provided on the fixing component, and a second protrusion matching the first protrusion is provided on the outer shell, and the first protrusion and the second protrusion are connected by the pin.

2. The rudder surface connecting device according to claim 1, characterized in that... ； The joint also includes vertical support members and diagonal support members; The vertical support, the inclined support, and the outer shell enclose the mounting cavity.

3. The rudder surface connecting device according to claim 2, characterized in that, The inclined support member is provided with a groove; The bottom end of the suspended part matches the groove and is disposed within the groove.

4. The rudder surface connecting device according to claim 1, characterized in that, It also includes a limit cover and a spring; The spring is disposed between the limiting cover and the axial limiting member.

5. The rudder surface connecting device according to claim 1, characterized in that, This also includes spherical bearings; The spherical bearing transitionally fits onto the joint; The rotating stud passes through the spherical bearing and connects to the limiting connector.

6. A tail fin for an aircraft, characterized in that, Includes control surfaces, stabilizers, and control surface connection devices; The rudder surface connection device is the rudder surface connection device according to any one of claims 1-5; The control surface is connected to the stabilizer via the control surface connection device.

7. The aircraft tail fin according to claim 6, characterized in that, The tail of the aircraft can be a vertical tail, a horizontal tail, or a V-tail.

8. An aircraft, characterized in that, Including the main body of the aircraft and the tail fin; The tail fin of the aircraft is the tail fin of the aircraft as described in claim 6 or 7; The tail fin of the aircraft is mounted on the main body of the aircraft.

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