Aircraft tail vane and preparation method

Abstract

The invention discloses an aircraft tail vane and a preparation method. The aircraft tail vane comprises a vane body. Comprising a rudder body; the rudder body comprises a supporting framework and two first skins; the supporting framework is provided with a through groove and at least one exhaust hole communicated with the through groove, and the through groove is used for reducing the weight of the supporting framework; the two first skins are arranged on the two opposite sides of the supporting framework correspondingly and seal the through groove. According to the aircraft tail vane, the exhaust hole communicated with the through groove is formed in the supporting framework of the vane body, so that the external pressure of the vane body can be kept consistent with the pressure in the through groove, and the situation that normal use is affected due to the fact that the vane body deforms in the flight process of an aircraft is avoided.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft equipment, and specifically relates to an aircraft tail rudder and a preparation method thereof. Background Art

[0002] A rudder refers to an aerodynamic wing surface that uses deflection in the airflow to generate aircraft balance and control force to control the flight of an aircraft. It is also called a control surface.

[0003] At present, most control surfaces are mainly controlled by servos, which are installed in the fuselage of the aircraft. The aircraft control surfaces rotate around the rudder axis during flight to adjust the aircraft's position and generate control force and control torque on the aircraft, so that the aircraft can adjust its flight trajectory in time.

[0004] In the prior art, in order to reduce the weight of the rudder, a plurality of through slots are provided on the supporting body of the rudder, and then the supporting body is directly covered with a skin; after the skin is covered, the through slots on the supporting body are completely covered, so that the through slots form a closed cavity. During the flight of the aircraft, the pressure inside the rudder is different from that outside, which easily causes the rudder to deform, affecting the normal use of the rudder. Therefore, inventing a rudder with a simple structure and not prone to deformation is a technical problem that needs to be solved urgently by those skilled in the art. Summary of the invention

[0005] In order to solve the above technical problems, the present application provides an aircraft tail rudder on one hand, so as to solve the technical problem in the prior art that the rudder surface provided with through grooves is easily deformed during flight and affects the normal flight of the aircraft.

[0006] The technical solution adopted to achieve the purpose of this application is:

[0007] An aircraft tail rudder comprises a rudder body;

[0008] The rudder body comprises a supporting frame and two first skins;

[0009] The support frame is provided with a through slot and an exhaust hole connected to the through slot, and the through slot is used to reduce the weight of the support frame;

[0010] The two first skins are respectively arranged on two opposite sides of the supporting frame and close the through slot.

[0011] In order to better implement the present application, further optimization is made in the above structure, and the rudder body further includes:

[0012] A separator, the number of which is at least one, is arranged in the through groove, and is used to divide the through groove into a plurality of sub-through grooves, two adjacent sub-through grooves are connected through a through hole, and one of the plurality of sub-through grooves is connected to the exhaust hole.

[0013] In order to better implement the present application, further optimization is made in the above structure, and the exhaust hole is arranged on a side of the support frame close to the aircraft body.

[0014] In order to better implement the present application, the above structure is further optimized, and a mounting groove is provided on the support frame, and a counterweight block is provided in the mounting groove;

[0015] The two first covering skins respectively block two opposite sides of the installation groove.

[0016] In order to better implement the present application, further optimization is made in the above structure, and the rudder body further includes:

[0017] A second skin is provided between the counterweight block and the first skin.

[0018] In order to better implement the present application, further optimization is made in the above structure, and the installation groove and the through groove are arranged at intervals along the windward direction.

[0019] In order to better implement the present application, further optimization is made in the above structure, and the tail rudder of the aircraft also includes:

[0020] A steering gear, wherein the steering gear is arranged on the aircraft, and the rudder body is arranged on the rotating shaft of the steering gear;

[0021] A sealing assembly is arranged between the aircraft and the rotating shaft.

[0022] In order to better implement the present application, further optimization is made in the above structure, and the tail rudder of the aircraft also includes:

[0023] A folding assembly, wherein the rudder body is arranged on the steering gear through the folding assembly, and the rotation axis of the folding assembly is perpendicular to the axis of the steering gear;

[0024] The folding assembly includes a clamping block, a hinge shaft, a torsion spring and a limit assembly;

[0025] The clamp block is detachably arranged on the rudder body, and an extension portion is arranged on a side of the clamp block away from the rudder body, a limiting hole is arranged on a side wall of the extension portion, the hinge shaft is inserted on the extension portion, and the axis of the hinge shaft is parallel to the length direction of the support frame;

[0026] A countersunk hole is provided in the middle of the rotating shaft, a through hole matching the hinge shaft is provided on the side wall of the countersunk hole, the axis of the through hole is perpendicular to the axis of the rotating shaft, and the rudder body is hinged to the rotating shaft of the steering gear through the cooperation between the hinge shaft and the through hole;

[0027] The torsion spring is sleeved on the hinge shaft, and one end of the torsion spring abuts against the rotating shaft, and the other end of the torsion spring is arranged on the clamping block, and the torsion spring is always in a compressed state;

[0028] The limiting assembly is arranged on the rotating shaft, and the limiting end of the limiting assembly can cooperate with the limiting hole to limit the deployment angle of the rudder body.

[0029] In order to better implement the present application, further optimization is made in the above structure, wherein the limit assembly includes a limit shaft and a return spring;

[0030] A storage groove is provided at the bottom of the countersunk hole, and the return spring and the limit shaft are both arranged in the storage groove. The two ends of the return spring are respectively against the bottom of the storage groove and the end of the limit shaft, and can push the limit shaft away from the bottom of the storage groove. One end of the limit shaft away from the return spring is against the side wall of the extension part; when the rudder body is fully unfolded, the end of the limit shaft away from the return spring is stuck in the limit hole.

[0031] On the other hand, the present application also provides a method for preparing an aircraft tail rudder, the preparation method comprising the following steps:

[0032] The support frame is prepared by 3D printing, and during the printing process, a support member is arranged on the bottom surface of the support frame to reduce the overhanging surface of the support frame;

[0033] Processing exhaust holes on the support frame by mechanical processing, and adjusting the structure and precision of the support frame;

[0034] Preparing a first skin by 3D printing, and filing the prepared first skin;

[0035] The edge of the first skin is welded to the edge of the support frame so that the first skin is attached to two opposite sides of the support frame. After the first skin and the support frame are welded, annealing is performed to remove residual stress.

[0036] It can be seen from the above technical solution that the supporting frame of the rudder body in the tail rudder of the aircraft provided in the present application is provided with an exhaust hole connected to the through groove, so that the external pressure of the rudder body can be consistent with the pressure in the through groove, thereby avoiding the situation where the rudder body is deformed during the flight of the aircraft and affects its normal work. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 A schematic diagram of the structure of a tail rudder of an aircraft provided in this application;

[0038] Figure 2An exploded view of a rudder body in a tail rudder of an aircraft provided in the present application;

[0039] Figure 3 A schematic diagram of the structure of a support frame in a tail rudder of an aircraft provided in this application;

[0040] Figure 4 A cross-sectional view of a tail rudder of an aircraft provided in the present application;

[0041] Figure 5 for Figure 4 A partial enlarged view of the middle A part;

[0042] Figure 6 A schematic diagram of the structure of a rotating shaft in a tail rudder of an aircraft provided in this application;

[0043] Figure 7 A schematic diagram of the structure of a sealing assembly in a tail rudder of an aircraft provided in the present application;

[0044] Figure 8 A schematic diagram of the structure of a limit assembly in a tail rudder of an aircraft provided in this application;

[0045] Fig. 9 A schematic structural diagram of a clamping block in a tail rudder of an aircraft provided in the present application.

[0046] Description of reference numerals:

[0047] 1-rudder body, 11-support frame, 111-through slot, 112-installation slot, 113-through hole, 114-exhaust hole, 12-counterweight block, 131-first skin, 132-second skin, 14-partitioning piece;

[0048] 2-servo, 21-rotating shaft, 211-storage slot, 22-sealing assembly, 221-rotating ring, 2211-sealing groove, 222-sealing ring, 223-rubber gasket, 224-graphite gasket, 225-sliding gasket;

[0049] 3-folding assembly, 31-hinge shaft, 32-torsion spring, 33-limiting assembly, 331-limiting shaft, 332-reset spring, 34-clamping block, 341-extension part. DETAILED DESCRIPTION

[0050] In order to enable technicians in the technical field to which the present application belongs to understand the present application more clearly, the technical solution of the present application is described in detail below through specific embodiments in conjunction with the accompanying drawings.

[0051] In the embodiments of the present application, Figures 1 to 9 As shown: the aircraft tail rudder includes a rudder body 1; wherein,

[0052] The rudder body 1 includes a support frame 11 and two first skins 131; the support frame 11 is a plate-like structure, and two through slots 111 that penetrate the support frame 11 and are opposite to each other are opened on the support frame 11, and the through slots 111 are used to reduce the weight of the support frame 11, and the axis of the through slots 111 is perpendicular to the windward direction of the rudder body 1, and the support frame 11 is also provided with an exhaust hole 114, and the through slots 111 are connected to the exhaust hole 114, see Figure 2 and Figure 3 ;

[0053] The two first skins 131 are respectively arranged on opposite sides of the support frame 11 and close the through groove 111, so that the through groove 111 forms a cavity. The through groove 111 is connected with the external environment through the exhaust hole 114 to ensure that the pressure in the cavity is the same as the external pressure; to avoid the rudder body 1 from deforming during the flight of the aircraft and affecting the normal work, thereby effectively improving the service life of the tail rudder of the aircraft and improving the safety of the aircraft during flight.

[0054] It is worth noting that the number of the above-mentioned exhaust holes 114 can be multiple, and the multiple exhaust holes 114 are respectively arranged on a side of the support frame 11 close to the aircraft body. This arrangement can reduce air resistance and the generation of cyclones, so that the aircraft is more stable during flight.

[0055] In some embodiments, the rudder body 1 further includes a separator 14; wherein,

[0056] The separator 14 is arranged in the through groove 111, which can increase the structural strength of the supporting frame 11 as a whole. The number of the separators 14 is N, and the N separators 14 divide the through groove 111 into N+1 sub-through grooves. Two adjacent sub-through grooves are connected to each other through the through hole 113, and at least one of the plurality of sub-through grooves is connected to the exhaust hole. Figure 2 and Figure 3 The through hole 113 is formed on the partition 14 .

[0057] If there are more than two partitions 14, the spacing between the ends of the multiple partitions 14 close to the rudder body 1 is greater than the spacing between the ends of the multiple partitions 14 away from the rudder body 1, that is, the multiple partitions 14 are arranged in a divergent manner, and the ends of the multiple partitions 14 close to the rudder body 1 are concentrated at the connection between the rudder body 1 and the steering gear 2, which can better disperse the stress to ensure the structural strength of the rudder body 1.

[0058] In some embodiments, the support frame 11 is provided with a mounting groove 112, a counterweight 12 is provided in the mounting groove 112, and the two first skins 131 are respectively blocked on opposite sides of the mounting groove 112, and the counterweight 12 is covered in the mounting groove 12; the mass center of mass of the rudder body 1 can be adjusted by the counterweight 12, so that the rotation of the rudder body 1 is more stable and smooth. Preferably, the rudder body 1 further includes a second skin 132, which is provided between the support frame 11 and the first skin 131.

[0059] In some embodiments, the above-mentioned installation grooves 112 and through grooves 111 are arranged at intervals along the windward direction so that the counterweight block 12 can play a corresponding role, thereby adjusting the mass center of the rudder body 1; Figure 1 and Figure 2 As shown, along the rotation axis of the rudder body 1, the volume of the part of the rudder body 1 close to the windward surface is much smaller than the volume of the part of the rudder body 1 away from the windward surface. The counterweight 12 is arranged at the part of the rudder body 1 close to the windward surface to adjust the mass center of mass of the rudder body 1 so that the rudder body 1 can rotate more smoothly.

[0060] In some embodiments, a thermal barrier coating is provided on a side of the first skin 131 facing away from the support frame 11 . The thermal barrier coating can provide good thermal insulation for the support frame 11 and reduce the impact of temperature on the support frame 11 .

[0061] In some embodiments, the aircraft tail rudder further includes a steering gear 2; wherein,

[0062] The steering gear 2 is arranged on the aircraft, and the rudder body 1 is arranged on the rotating shaft 21 of the steering gear 2. Figure 1 and Figure 4 The servo 2 drives the rudder body 1 to move, thereby realizing the movement change of the rudder body 1, thereby realizing the control of the balance force and direction of the aircraft.

[0063] In some embodiments, a sealing assembly 22 is disposed on the rotating shaft 21. Figure 5 The sealing component 22 can isolate the cabin environment of the aircraft from the cabin environment to meet the heat insulation requirements of the equipment (servo 2) and provide good sealing protection for the cabin structure.

[0064] Specifically, the sealing assembly 22 includes a rotating ring 221, a sealing ring 222, a rubber gasket 223, a graphite gasket 224 and a sliding gasket 225. Figure 7 ;in,

[0065] The rotating ring 221 is made of high temperature alloy and is sleeved on the rotating shaft 21. The outer edge of the rotating ring 221 is provided with a protrusion extending away from the rotating shaft 21. The upper end surface of the protrusion is provided with a sealing groove 2211. The sealing ring 222 is provided between the rotating ring 221 and the rotating shaft 21 to seal the gap between the rotating ring 221 and the rotating shaft 21.

[0066] The upper end surface of the protrusion is fitted with the aircraft body, and the rubber gasket 223, the graphite gasket 224 and the sliding gasket 225 are stacked in sequence from the bottom of the sealing groove 2211 to the groove opening of the sealing groove 2211 to achieve sealing of the gap between the protrusion and the aircraft body;

[0067] It should be noted that the rubber gasket 223 is mainly used for sealing, shock absorption and isolation; the graphite gasket 224 has good resilience, chemical stability, high temperature resistance and corrosion resistance, and can provide a good sealing effect; the sliding gasket 225 is formed by processing chromium stainless steel material, which has excellent corrosion resistance and heat resistance. The end of the sliding gasket 225 away from the graphite gasket 224 is connected to the body of the aircraft;

[0068] When the rotating ring 221 rotates, the sliding washer 225 will not rotate relative to the aircraft body due to the friction force on the surface of the aircraft body, that is, the graphite washer 224 and the sliding washer 225 will rotate relative to each other, so that the rotating ring 221 can rotate normally and the gap between the rotating ring 221 and the aircraft body can be sealed. In this embodiment, the lower end of the rotating ring 221 is installed on the upper end of the high-temperature alloy rudder shaft sleeve, the rudder shaft sleeve is connected with the rotating shaft 21 with a clearance fit, and its outer side is connected with the inner ring of the bearing, and the outer ring of the bearing is connected with the aircraft body. Through the cooperation of the above-mentioned structural parts, the effective rotation of the rotating shaft 21 and the sealing of the rudder shaft connection can be achieved.

[0069] In some embodiments, the aircraft tail rudder further comprises a folding assembly 3, see Figure 1 , Figure 5 and Fig. 9 ;in,

[0070] The rudder body 1 is arranged on the steering gear 2 of the aircraft through a folding component 3, and the rotation axis of the folding component 3 is perpendicular to the axis of the steering gear 2, so that the rudder body 1 can be folded around the rotation axis of the folding component 3 to reduce the external dimensions of the aircraft during storage and transportation, and reduce the storage and transportation space; when necessary, the rudder body 1 on the aircraft can be unfolded to meet the aerodynamic requirements of the aircraft.

[0071] Specifically, the folding assembly 3 includes a clamping block 34, a hinge shaft 31, a torsion spring 32 and a limit assembly 33, see Figure 5 ;

[0072] The clamp block 34 is detachably arranged on the support frame 11, and an extension portion 341 is arranged on a side of the clamp block 34 away from the support frame 11, and a limiting hole is arranged on the outer wall of the extension portion 341; the hinge shaft 31 is inserted into the extension portion 341, and both ends of the hinge shaft 31 are located outside the extension portion 341, and the axis of the hinge shaft 31 is parallel to the length direction of the support frame 11;

[0073] A countersunk hole is provided in the middle of the rotating shaft 21 of the steering gear 2. Figure 6 , two opposite through holes are arranged on the side wall of the countersunk hole, the through holes match the hinge shaft 31, the axis of the through holes is perpendicular to the axis of the rotating shaft 21, the rudder body 1 is hinged on the rotating shaft 21 of the steering gear 2 through the cooperation of the hinge shaft 31 and the through holes, that is, the two ends of the hinge shaft 31 are respectively inserted into the two through holes to realize the cooperation between the rudder body 1 and the rotating shaft 21, see Figure 5 ;

[0074] The torsion spring 32 is sleeved on the hinge shaft 31, and one end of the torsion spring 32 abuts against the rotating shaft 21, and the other end of the torsion spring 32 is arranged on the clamping block 34, and the torsion spring 32 is always in a compressed state;

[0075] The limiting component 33 is arranged on the rotating shaft 21, and the limiting end of the limiting component 33 can cooperate with the limiting hole to limit the unfolding angle of the rudder body 1, that is, when the rudder body 1 rotates from the folded state to the unfolded state, the angle between the plane where the rudder body 1 is located and the rotating shaft 21 gradually decreases; when the plane where the rudder body 1 is located coincides with the rotating shaft 21, the rudder body 1 is in the unfolded state. At this time, the limiting component 33 cooperates with the limiting hole to fix the position of the rudder body 1 to meet the aerodynamic requirements of the aircraft.

[0076] In some embodiments, the above-mentioned limiting assembly 33 includes a limiting shaft 331 and a return spring 332, see Figure 8 ;

[0077] The bottom of the countersunk hole is provided with a storage groove 211, and the return spring 332 and the limit shaft 331 are both arranged in the storage groove 211, see Figure 5 The two ends of the return spring 332 are respectively disposed on the bottom of the storage slot 211 and the end of the limiting shaft 331, and the limiting shaft 331 is pushed away from the bottom of the storage slot 211, and one end of the limiting shaft 331 away from the return spring 332 is disposed on the side wall of the extension portion 341;

[0078] The axis of the above-mentioned limiting hole is parallel to the plane where the rudder body 1 is located;

[0079] When the rudder body 1 is fully unfolded, the end of the limit shaft 331 away from the return spring 332 is inserted into the limit hole to fix the position of the rudder body 1. Preferably, a first pin hole is provided on the side wall of the rotating shaft 21, the axis of the first pin hole is perpendicular to the axis of the rotating shaft 21, and the first pin hole passes through the storage slot 211; the limit shaft 331 is provided with a second pin hole, see Figure 8 , the axis of the second pin hole is perpendicular to the axis of the limiting shaft 331, and the second pin hole passes through the limiting shaft 331; when the first pin hole is opposite to the second pin hole, the end of the limiting shaft 331 away from the return spring 332 is located in the storage groove 211, at this time, the limiting shaft 331 can be fixed by passing the pin shaft through the first pin hole and the second pin hole, and the aircraft can be loaded into the box; after the loading is completed, the pin shaft can be pulled out;

[0080] After the aircraft is launched out of the box, the rudder body 1 changes from a folded state to an unfolded state under the action of the torsion spring 32 until the rudder body 1 is fully unfolded, and the end of the limit shaft 331 away from the return spring 332 is inserted into the limit hole to fix the position of the rudder body 1.

[0081] Based on the above-mentioned aircraft tail rudder, the present application also provides a method for preparing the aircraft tail rudder, and the preparation method comprises the following steps:

[0082] The support frame 11 is prepared by 3D printing; wherein, the support frame 11 is made of titanium alloy material to ensure that the support frame 11 has good strength, rigidity and weight to meet the requirements of the rudder body 1 in the flight environment; combined with the structural characteristics of the support frame 11 itself, it adopts a symmetrical growth method to reduce deformation. During the printing process of the support frame 11, a support member is set on the bottom surface of the support frame 11 to reduce the suspended surface of the support frame 11, so as to reduce the deformation of the support frame 11;

[0083] Considering that the printed product is difficult to meet the precision requirements of the size, shape and position tolerance of the final support skeleton 11, the overall 3D printing blank is used, and the precision of the support skeleton 11 is ensured by machining. At the same time, considering the operability of the processing, the printed blank is added with a process boss, and the processing amount is reserved according to the actual precision requirements of the support skeleton 11.

[0084] After printing, a vent hole 113 connected to the through groove 111 is processed on the support frame 11;

[0085] The counterweight block 12 is installed in the installation groove 112 of the support frame 11, and the counterweight block 12 is spot welded in the installation groove 112;

[0086] The first skin 131 is prepared by 3D printing, and a processing allowance is reserved, and the prepared first skin 131 is filed to control the accuracy of the first skin 131;

[0087] The edge of the first skin 131 is fixed to the edge of the support frame 11 by laser welding and meets the level I weld. The first skin 131 is welded to the support frame 11 at the corner (the bending part of the edge) by argon arc welding so that the first skin 131 is attached to the two sides of the support frame 11. After the first skin 131 is welded to the support frame 11, annealing is performed to remove residual stress.

[0088] Considering the requirements for heat insulation, the rudder body 1 is first sprayed with a thermal barrier coating and then painted. Before spraying the insulation layer, both the spraying area and the painting area need to be pre-treated with sandblasting. Before sandblasting, the holes with precision requirements are protected, and the time interval between spraying and sandblasting is controlled. Through the above structural design and processing procedures, it can be ensured that the folding rudder meets the aerodynamic load and aerodynamic heat requirements and realizes the folding and unfolding function.

[0089] Through the above embodiments, the present application has the following beneficial effects or advantages:

[0090] 1) The support frame 11 of the rudder body 1 in the tail rudder of the aircraft is provided with an exhaust hole 113 connected with the through groove 111, so that the external pressure of the rudder body 1 can be consistent with the pressure at the through groove 111, thereby avoiding the deformation of the rudder body 1 during the flight of the aircraft and affecting the normal use.

[0091] 2) The rudder body 1 of the tail rudder of the aircraft is arranged on the steering gear 2 of the aircraft through the folding assembly 3, so that the rudder body 1 can meet the requirements of reducing the overall size of the aircraft, reduce the storage and transportation space, and meet the starting requirements of the aircraft.

[0092] 3) A sealing assembly 22 is provided at the servo 2 in the tail rudder of the aircraft. The sealing assembly 22 can effectively isolate the environment inside and outside the aircraft cabin to ensure that the servo 2 is not affected by the external temperature and ensure the overall performance of the tail rudder of the aircraft.

[0093] Although the preferred embodiments of the present application have been described, those skilled in the art may make other changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present application.

[0094] Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is also intended to include these modifications and variations.

Claims

1. An aircraft tail rudder, characterized in that: It comprises a rudder body (1); The rudder body (1) comprises a supporting frame (11) and two first skins (131); The support frame (11) is provided with a through slot (111) and an exhaust hole (114) connected to the through slot (111), and the through slot (111) is used to reduce the weight of the support frame (11); The two first covering skins (131) are respectively arranged on two opposite sides of the supporting frame (11) and close the through slot (111).

2. The aircraft tail rudder according to claim 1, characterized in that: The rudder body (1) further comprises: A separator (14), the number of the separator (14) is at least one, the separator (14) is arranged in the through groove (111), and is used to separate the through groove (111) into a plurality of sub-through grooves, two adjacent sub-through grooves are connected via a through hole (113), and one of the plurality of sub-through grooves is connected to the exhaust hole.

3. The aircraft tail rudder according to claim 1, characterized in that: The exhaust hole (114) is arranged on a side of the support frame (11) close to the aircraft body.

4. The aircraft tail rudder according to claim 1, characterized in that: The support frame (11) is provided with a mounting groove (112), and a counterweight block (12) is arranged in the mounting groove (112); The two first covering skins (131) respectively block opposite sides of the mounting groove (112).

5. The aircraft tail rudder according to claim 4, characterized in that: The rudder body (1) further comprises: A second skin (132), wherein the second skin (132) is arranged between the counterweight block (12) and the first skin (131).

6. The aircraft tail rudder according to claim 4, characterized in that: The installation groove (112) and the through groove (111) are arranged at intervals along the windward direction.

7. The aircraft tail rudder according to claim 1, characterized in that: Also includes: A steering gear (2), the steering gear (2) being arranged on the aircraft, and the rudder body (1) being arranged on a rotating shaft (21) of the steering gear (2); A sealing component (22), wherein the sealing component (22) is arranged between the aircraft and the rotating shaft (21).

8. The aircraft tail rudder according to claim 7, characterized in that: Also includes: A folding assembly (3), wherein the rudder body (1) is arranged on the steering gear (2) through the folding assembly (3), and the rotation axis of the folding assembly (3) is perpendicular to the axis of the steering gear (2); The folding assembly (3) comprises a clamping block (34), a hinge shaft (31), a torsion spring (32) and a limiting assembly (33); The clamping block (34) is detachably arranged on the rudder body (1), and an extension portion (341) is arranged on a side of the clamping block (34) away from the rudder body (1), a limiting hole is arranged on a side wall of the extension portion (341), the hinge shaft (31) is inserted into the extension portion (341), and the axis of the hinge shaft (31) is parallel to the length direction of the support frame (11); A countersunk hole is provided in the middle of the rotating shaft (21), a through hole matching the hinge shaft (31) is provided on the side wall of the countersunk hole, the axis of the through hole is perpendicular to the axis of the rotating shaft (21), and the rudder body (1) is hinged to the rotating shaft (21) of the steering gear (2) through the matching of the hinge shaft (31) and the through hole; The torsion spring (32) is sleeved on the hinge shaft (31), and one end of the torsion spring (32) abuts against the rotating shaft (21), and the other end of the torsion spring (32) is arranged on the clamping block (34), and the torsion spring (32) is always in a compressed state; The limiting component (33) is arranged on the rotating shaft (21), and the limiting end of the limiting component (33) can cooperate with the limiting hole to limit the deployment angle of the rudder body (1).

9. The aircraft tail rudder according to claim 8, characterized in that: The limiting assembly (33) comprises a limiting shaft (331) and a return spring (332); A storage groove (211) is provided at the bottom of the countersunk hole, and the return spring (332) and the limit shaft (331) are both arranged in the storage groove (311). The two ends of the return spring (332) are respectively abutted against the bottom of the storage groove (211) and the end of the limit shaft (331), and are capable of pushing the limit shaft (331) in a direction away from the bottom of the storage groove (211). One end of the limit shaft (331) away from the return spring (332) is abutted against the side wall of the extension part (341); when the rudder body (1) is fully unfolded, one end of the limit shaft (331) away from the return spring (332) is inserted into the limit hole.

10. A method for preparing an aircraft tail rudder, characterized in that: The preparation method comprises the following steps: The support frame (11) is prepared by 3D printing, and during the printing process, a support member is arranged on the bottom surface of the support frame (11) to reduce the suspended surface of the support frame (11); Processing the exhaust hole (114) on the support frame (11) by mechanical processing, and adjusting the structure and precision of the support frame (11); Preparing a first skin (131) by 3D printing, and filing the prepared first skin (131); The edge of the first skin (131) is welded to the edge of the support frame (11) so that the first skin (131) is attached to two opposite sides of the support frame (11); and the first skin (131) and the support frame (11) are annealed after welding to remove residual stress.

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