Air rudder and aircraft

Abstract

The invention discloses an air rudder and an aircraft, and relates to the technical field of aircrafts, the air rudder comprises an integrated rudder body, a rudder leading edge and a thermal barrier coating, the integrated rudder body comprises a rudder frame, a rudder shaft and a rib connected with the rudder frame, and a rudder surface wrapping the rudder frame and the rib, and the integrated rudder body is configured to be formed through 3D printing; the rudder leading edge is installed at the front end of the rudder frame, and the control surface is coated with the thermal barrier coating. The rudder body is formed through 3D printing, mechanical connection between a rudder shaft and a rudder surface in a traditional air rudder is omitted, the risk that the air rudder is overheated and large in deformation amount and finally breaks down due to mechanical connection between the rudder shaft and the rudder surface along with the increase of the speed of an aircraft is improved, and the integrated rudder body can bear higher force loads and thermal loads under the flight working condition; it is ensured that the front edge of the rudder meets the requirement for bearing heat flow scouring, the short-time 1000 DEG C heat protection performance and the long-time 600 DEG C heat protection performance can be achieved through the thermal barrier coating, and the air rudder provided by the invention guarantees the bearing capacity and the heat protection capacity under the condition that the requirement for light weight is met.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to an air rudder and an aircraft. Background Art

[0002] The air rudder is the executive component of the aircraft's attitude control. It is distributed outside the aircraft's servo cabin and provides it with maneuverable flight control torque.

[0003] As the speed of the aircraft increases, the air rudder is required to withstand greater force loads and greater thermal loads under flight conditions. The existing air rudder structure cannot meet the load-bearing and heat-protection requirements. When the aircraft flies for a long time, the air rudder overheats and deforms greatly, causing the mechanical connection between the conventional air rudder shaft and the rudder surface to fail, resulting in air rudder failure. It is necessary to provide a new air rudder structure to meet the increasingly high load-bearing and heat-protection requirements. Summary of the invention

[0004] The present application provides an air rudder and an aircraft, which solve the technical problem in the prior art that the existing air rudder cannot meet the heat protection requirements and the load-bearing requirements as the speed of the aircraft increases.

[0005] The present application provides an air rudder, comprising an integrated rudder body, a rudder leading edge and a thermal barrier coating, wherein the integrated rudder body comprises a rudder frame, a rudder shaft and ribs connected to the rudder frame, and a rudder surface covered outside the rudder frame and the ribs, the integrated rudder body is configured to be 3D printed, the rudder leading edge is installed at the front end of the rudder frame, and the thermal barrier coating is covered on the rudder surface.

[0006] In some embodiments, the tendons include:

[0007] A plurality of longitudinal ribs are provided, and the plurality of longitudinal ribs are radially distributed outwards with the junction of the rudder shaft and the rudder frame as the center;

[0008] There is at least one annular rib, which is distributed in an annular direction. The intersection of the rudder shaft and the rudder frame is located at the center of the annular shape in the annular distribution, and the annular rib is connected to the longitudinal rib.

[0009] In some embodiments, the longitudinal reinforcement is provided with:

[0010] The length direction is the radiation direction radiating from the center to the outside;

[0011] In width direction, the rudder surface covers the opposite sides of the rudder frame, and the width direction is the same as the direction of the rudder surface on one side of the rudder frame pointing to the rudder surface on the other side;

[0012] The thickness direction is perpendicular to both the length and width directions;

[0013] The longitudinal reinforcement is provided with a thickness dimension along the thickness direction, and the thickness dimension of the longitudinal reinforcement gradually decreases along the radial direction.

[0014] In some embodiments, the longitudinal reinforcement includes a first longitudinal reinforcement connected to the upper chord of the rudder frame and a second longitudinal reinforcement connected to the front end or the rear end of the rudder frame;

[0015] The longitudinal reinforcement is provided with a tip connected to the upper chord or the front end or the rear end of the rudder frame and a root relatively far from the tip;

[0016] The thickness dimension of the root of the first longitudinal rib is greater than the thickness dimension of the root of the second longitudinal rib, and the thickness dimension of the tip of the first longitudinal rib is greater than the thickness dimension of the tip of the second longitudinal rib.

[0017] In some embodiments, at least one annular rib divides the rudder surface located on the same side of the rudder frame into at least two partitions, and the thicknesses of the at least two partitions decrease sequentially along a radial direction radiating from the center to the outside.

[0018] In some embodiments, the longitudinal reinforcement is an I-shaped structure, and the annular reinforcement is a plurality of I-shaped structures connected in sequence and is distributed in an annular direction as a whole;

[0019] Lightening holes are provided in both longitudinal and annular reinforcements;

[0020] The ribs also include fan-shaped ribs, which are located at the junction of the rudder shaft and the rudder frame. The fan-shaped ribs are connected to the rudder shaft, the radius side of the fan-shaped ribs is located at the lower chord of the rudder frame, and the longitudinal ribs are connected to the fan-shaped ribs and connected to the arc side of the fan-shaped ribs.

[0021] In some embodiments, the rudder shaft is provided with a plurality of hollow holes in the cylinder portion, the hollow holes are distributed along the axial direction of the cylinder portion, and the plurality of hollow holes are evenly spaced along the circumference of the cylinder portion.

[0022] In some embodiments, the rudder leading edge is fixedly connected to the front end of the rudder frame by rivets.

[0023] In some embodiments, the leading edge of the rudder is provided with a plurality of mounting holes sequentially distributed along the length direction, the mounting holes are used for rivet assembly, the mounting holes include a circular hole located in the middle and waist-shaped holes located on both sides of the circular hole, the diameter of the circular hole is equal to the diameter of the rivet, the width of the waist-shaped hole is equal to the diameter of the rivet, and the length of the waist-shaped hole is greater than the diameter of the rivet;

[0024] The rudder frame is provided with a rivet hole having a diameter equal to that of the rivet, and the rivet hole is butted with the mounting hole and is used together for assembling the rivet.

[0025] An aircraft comprises the above-mentioned air rudders distributed on the outer surface of a servo cabin.

[0026] The beneficial effects of the present application are as follows: an air rudder is provided, comprising an integrated rudder body, a rudder leading edge and a thermal barrier coating, wherein a rudder frame, a rudder shaft, ribs and a rudder surface are arranged in the integrated rudder body, the structural strength of the rudder body is strengthened by the ribs, and the integrated rudder body is formed by 3D printing, thereby eliminating the mechanical connection between the rudder shaft and the rudder surface in the traditional air rudder, thereby improving the risk of the air rudder overheating and deformation and eventual failure due to the mechanical connection between the rudder shaft and the rudder surface as the aircraft speed increases; there is no mechanical gap between the rudder shaft and the rudder frame of the integrated structure, which can reduce the mechanical gap in the torque transmission process of the steering gear control, making the rudder surface angle control more accurate; the rudder is formed by 3D printing of metal materials The integrated rudder body can withstand higher force loads and thermal loads under flight conditions; the leading edge of the rudder is installed at the front end of the rudder frame, and the front end of the rudder frame belongs to the windward edge of the air rudder. The leading edge of the rudder is designed to be heat-resistant and reinforced separately to ensure that the leading edge of the rudder meets the requirements of withstanding the erosion of heat flow; materials are sprayed on the rudder surface of the integrated rudder body to form a thermal barrier coating, thereby realizing large-area thermal protection of the rudder surface. The thickness of the thermal barrier coating can be changed according to the thermal environment and heat protection requirements, and can achieve short-term 1000°C and long-term 600°C heat protection performance; in summary, the present application provides an air rudder that meets the requirements of lightweight and guarantees its load-bearing capacity and heat protection capability, and can be applied to aircraft with increasingly faster speeds. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for describing the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention.

[0028] Figure 1 A schematic diagram of the structure of an air rudder provided in this application;

[0029] Figure 2 A cross-sectional view of an air rudder provided for the present application;

[0030] Figure 3 A partial enlarged view of the longitudinal ribs and annular ribs of an air rudder provided in the present application;

[0031] Figure 4 A cross-sectional view of a rudder shaft of an air rudder provided in the present application;

[0032] Figure 5 A schematic diagram of the installation of the leading edge of an air rudder provided in the present application.

[0033] The attached drawings are marked with: 10-integrated rudder body, 11-rudder frame, 111-upper chord, 112-lower chord, 113-front end, 114-rear end, 12-rudder shaft, 121-hollow hole, 13-rib, 131-longitudinal rib, 1311-first longitudinal rib, 1312-second longitudinal rib, 1313-tip, 1314-root, 132-annular rib, 133-fan-shaped rib, 134-lightening hole, 14-rudder surface, 141-rudder surface thickness change line, 20-rudder leading edge, 21-rivet, 211-circular hole, 212-waist hole, 30-thermal barrier coating. DETAILED DESCRIPTION

[0034] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application.

[0035] In addition, the present application may repeat reference numbers and / or reference letters in different examples, and such repetition is for the purpose of simplicity and clarity, and does not in itself indicate the relationship between the various embodiments and / or settings discussed. In addition, the present application provides various specific examples of processes and materials, but those of ordinary skill in the art may recognize the application of other processes and / or the use of other materials.

[0036] The air rudder is the executive component of the aircraft's attitude control. During the flight of the aircraft, the air rudder must withstand aerodynamic forces and aerodynamic heat, and its working environment is harsh. At the same time, in order to ensure that the servo can work normally within the rated load, strict requirements are imposed on the air rudder's strength, stiffness, weight, moment of inertia and other indicators. The air rudder is required to have strong stiffness to reduce the risk of flutter during flight, and at the same time, it should be as light as possible and have as small a moment of inertia as possible.

[0037] As the speed of the aircraft increases, the air rudder is required to withstand greater force loads and greater thermal loads under flight conditions. The existing air rudder structure cannot meet the load-bearing and heat-protection requirements. When the aircraft flies for a long time, the air rudder overheats and deforms greatly, causing the mechanical connection between the conventional air rudder shaft and the rudder surface to fail, resulting in air rudder failure. It is necessary to provide a new air rudder structure to meet the increasingly high load-bearing and heat-protection requirements.

[0038] In order to adapt to higher flight speeds, this application provides an air rudder, please refer to Figure 1 The air rudder includes an integrated rudder body 10 , a rudder leading edge 20 and a thermal barrier coating 30 . The rudder leading edge 20 is installed at the front end 113 of the integrated rudder body 10 , and the thermal barrier coating 30 is covered on the integrated rudder body 10 .

[0039] Please refer to Figure 2 The integrated rudder body 10 includes a rudder frame 11, a rudder shaft 12, ribs 13 and a rudder surface 14. The rudder frame 11 is a frame structure of the integrated rudder body 10. The rudder frame 11 has an upper chord 111, a lower chord 112, a front end 113 and a rear end 114. The upper chord 111, the lower chord 112, the front end 113 and the rear end 114 of the rudder frame 11 are existing concepts and will not be described in detail here. The rudder shaft 12 is connected to the rudder frame 11. The rudder shaft 12 is specifically connected to one side of the lower chord 112 of the rudder frame 11. The air rudder is connected to the aircraft through the rudder shaft 12. The ribs 13 are connected to the rudder frame 11. The ribs 13 are distributed between the rudder frame 11. The structural strength of the rudder body 10 is strengthened by the ribs 13. The rudder surface 14 is covered outside the rudder frame 11 and the ribs 13. The rudder surface 14 is distributed on opposite sides of the rudder frame 11. The rudder surface 14 maintains the appearance of the air rudder and withstands the dynamic pressure during the flight of the aircraft. Accordingly, please refer to Figure 1 and Figure 2 The rudder leading edge 20 is installed on the front end 113 of the rudder frame 11 , and the thermal barrier coating 30 is covered on the rudder surface 14 .

[0040] The integrated rudder body 10 in the air rudder provided in the present application is formed by 3D printing. The rudder body formed by 3D printing is an integrated structure, which eliminates the mechanical connection between the rudder shaft 12 and the rudder surface 14 in the traditional air rudder, thereby improving the risk of overheating and deformation of the air rudder due to the mechanical connection between the rudder shaft 12 and the rudder surface 14 and eventually causing failure as the aircraft speed increases.

[0041] The integrated rudder body 10 is formed by 3D printing of metal materials, and the metal material can be TC4 titanium alloy material. The composition of TC4 titanium alloy material is Ti-6Al-4V, which belongs to (α+β) type titanium alloy, has good comprehensive mechanical properties, has a high specific strength and low thermal conductivity. The integrated rudder body 10 formed by 3D printing of TC4 titanium alloy powder can withstand higher force loads and thermal loads under flight conditions.

[0042] The rudder surfaces 14 on both sides of the integrated rudder body 10 are uniformly sprayed with materials, thereby forming a thermal barrier coating 30 covering the rudder surfaces 14. The thermal barrier coating 30 is a ceramic coating, which is deposited on the surface of the integrated rudder body 10. The thermal barrier coating 30 plays a role in heat insulation for the integrated rudder body 10. The thermal barrier coating 30 withstands the scouring of the heat flow on the rudder surface 14, plays a role in isolating heat transfer, and realizes large-area thermal protection of the rudder surface 14. The thickness of the thermal barrier coating 30 can be changed according to the thermal environment and heat protection requirements. By uniformly spraying materials on the rudder surface 14 in the integrated rudder body 10 formed by 3D printing of metal materials to form a thermal barrier coating 30, it is possible to achieve short-term 1000°C and long-term 600°C heat protection performance. In some embodiments, the spraying material of the thermal barrier coating 30 is zirconium oxide, and the thickness can be 1.2mm.

[0043] The rudder body formed by 3D printing is an integrated structure, and there is no mechanical gap between the rudder shaft 12 and the rudder frame 11 of the integrated structure, which can reduce the mechanical gap in the process of torque transmission of the steering gear control and make the angle control of the rudder surface 14 more precise.

[0044] The rudder leading edge 20 is installed at the front end 113 of the rudder frame 11. The front end 113 of the rudder frame 11 belongs to the windward edge of the air rudder, so that the rudder leading edge 20 is arranged in the windward area of ​​the air rudder. Compared with the integrated rudder body 10, the rudder leading edge 20 is inclined. The rudder leading edge 20 is designed to be heat-resistant and strengthened separately to ensure that the rudder leading edge 20 meets the requirements of withstanding the scouring of heat flow. For the heat-resistant and strengthened design of the rudder leading edge 20, the rudder leading edge 20 can be produced by the process of 2.5D quartz braid + B80 phenolic resin compression molding. This type of rudder leading edge 20 can achieve the purpose of heat protection in key areas. In the molding process of the rudder leading edge 20, the material of the rudder leading edge 20 is 2.5D quartz braid and phenolic resin, and the mold is molded at high temperature. The 2.5D quartz braid is a special composite material structure, which combines quartz fiber and weaving technology. It is mainly made of quartz fiber through a specific weaving process and has excellent mechanical properties and specific structural characteristics. B80 phenolic resin is a special type of phenolic resin. The compression molding process uses the characteristics of each stage in the resin curing reaction to achieve product molding, that is, the molding material plasticizes, flows and fills the mold cavity, and the resin solidifies. In the process of the molding material filling the mold cavity, not only the resin flows, but also the reinforcing material flows with it.

[0045] In summary, the present application provides a new air rudder, which ensures its load-bearing capacity and heat protection capability while meeting the requirements of lightweight, and the air rudder can be applied to aircraft with increasingly faster speeds.

[0046] In some embodiments, see Figure 2 The ribs 13 include longitudinal ribs 131 and annular ribs 132. There are multiple longitudinal ribs 131, which are radially distributed outward with the intersection of the rudder shaft 12 and the rudder frame 11 as the center. The length direction of the longitudinal ribs 131 is the radial direction. The ends of the longitudinal ribs 131 are connected to the upper chord 111, the front end 113 or the rear end 114 of the rudder frame 11. These longitudinal ribs 131 play a role in facilitating the transfer of the load of the rudder surface 14 to the rudder shaft 12. There is at least one annular rib 132, which is distributed in an annular direction. In the annular distribution scheme, there is an annular center, and the annular center of the annular rib 132 is the intersection of the rudder shaft 12 and the rudder frame 11. In this mode, the annular rib 132 is connected to at least one longitudinal rib 131, and the annular rib 132 is connected to the longitudinal rib 131 and the rudder frame 11, so as to form an integral grid structure, which plays a role in enhancing the structural stability of the integrated rudder body 10.

[0047] Please note that, please refer to Figure 2 , the ring reinforcement 132 in this mode is not the form of a full circle. In addition, the ring reinforcement 132 should be connected with as many longitudinal reinforcements 131 as possible. Figure 2 The distribution scheme with two annular ribs 132 is shown, one annular rib 132 is connected to all longitudinal ribs 131, and both ends of the annular rib 132 are connected to the lower chord 112 of the rudder frame 11; the other annular rib 132 is connected to multiple longitudinal ribs 131 and the number of longitudinal ribs 131 connected to it is less than the total number of longitudinal ribs 131, and both ends of the annular rib 132 are respectively connected to the front end 113 and the rear end 114 of the rudder frame 11. The number and distribution of the annular ribs 132 can be adjusted according to the size of the rudder surface 14.

[0048] In some embodiments, the longitudinal ribs 131 are designed with variable thickness. In this method, please allow the definition of the distribution direction of the longitudinal ribs 131 to be first proposed. The longitudinal ribs 131 have a length direction, a width direction and a thickness direction. Figure 2 It can be understood that the length direction of the longitudinal rib 131 is the radiation direction radiating from the center to the outside; based on the basic feature that the rudder surface 14 covers the opposite sides of the rudder frame 11, the width direction of the longitudinal rib 131 is the same as the direction from the rudder surface 14 on one side of the rudder frame 11 to the rudder surface 14 on the other side. Figure 2 The width direction of the middle longitudinal rib 131 is perpendicular to the paper surface; the thickness direction of the longitudinal rib 131 is perpendicular to both the length direction and the width direction, and it can be seen that the thickness direction of each longitudinal rib 131 is different. Regarding the variable thickness design of the longitudinal rib 131, in detail, the thickness dimension of the longitudinal rib 131 is the dimension along the thickness direction, and the thickness dimension of the longitudinal rib 131 gradually decreases along the radial direction.

[0049] Figure 2 The figure shows the root 1314 and the tip 1313 of the longitudinal rib 131, which are the opposite ends of the longitudinal rib 131 in the length direction. The root 1314 is located at the junction of the rudder shaft 12 and the rudder frame 11, and the tip 1313 is relatively far away from the root 1314. The tip 1313 is located at the upper chord 111, the front end 113 or the rear end 114 of the rudder frame 11. Therefore, the variable thickness design of the longitudinal rib 131 is reflected in that the closer the longitudinal rib 131 is to the rudder shaft 12 area, the more mass distribution there is, and the closer the longitudinal rib 131 is to the tip 1313, the less mass distribution there is. This trend is consistent with the load-bearing trend of the air rudder when the aircraft is flying at high speed. By reducing the mass distribution of the air rudder tip 1313, the possibility of flutter of the air rudder in a vibration environment during high Mach number flight can be effectively reduced.

[0050] During the process of 3D printing of the integrated rudder body 10 using metal materials, the longitudinal ribs 131 are printed, and the printing direction starts from the rudder shaft 12 and develops toward the tip 1313. Therefore, when designing the longitudinal beam, the angle between the longitudinal beam and the lower chord 112 of the rudder frame 11 needs to be considered. In some embodiments, the angle between the longitudinal beam and the lower chord 112 of the rudder frame 11 is not less than 45°. For the printing of the annular ribs 132 during the printing process, a lattice structure support can be designed, and the printing direction can be adjusted when necessary. The lattice structure also has another function, which is to support the rudder surface to prevent the rudder surface from collapsing under the action of aerodynamic force.

[0051] In some embodiments, the longitudinal ribs 131 are designed with different thicknesses. Figure 2 , all longitudinal ribs 131 are divided into first longitudinal ribs 1311 and second longitudinal ribs 1312, the first longitudinal ribs 1311 are longitudinal ribs 131 connected to the upper chord 111 of the rudder frame 11, and the second longitudinal ribs 1312 are longitudinal ribs 131 connected to the front end 113 or the rear end 114 of the rudder frame 11, and the definitions of the root 1314 and the tip 1313 of the longitudinal ribs 131 have been described above, the thickness of the root 1314 of the first longitudinal rib 1311 is greater than the thickness of the root 1314 of the second longitudinal rib 1312, and the thickness of the tip 1313 of the first longitudinal rib 1311 is greater than the thickness of the tip 1313 of the second longitudinal rib 1312. The key point of this method is that the thickness of the longitudinal ribs 131 in each area is designed according to the load distribution of the air rudder rudder surface 14, and a lightweight design is performed without reducing the bearing capacity, thereby achieving the purpose of reliable structure and lightweight.

[0052] This application provides a specific design of the thickness differentiation of the longitudinal rib 131, please refer to Figure 2 , Figure 2 The four first longitudinal ribs 1311 have a root portion 1314 thickness of 6 mm and a tip portion 1313 thickness of 1 mm. Figure 2 The second longitudinal rib 1312 has a root portion 1314 with a thickness of 4 mm and a tip portion 1313 with a thickness of 0.8 mm.

[0053] In some embodiments, the rudder surface 14 is designed with variable thickness, and at least one annular rib 132 divides the rudder surface 14 on the same side of the rudder frame 11 into at least two partitions, and the thickness of at least two partitions decreases in the radial direction radiating from the center to the outside. Please allow additional explanation, please refer to Figure 2 , Figure 2The scheme of two annular ribs 132 is shown. According to the above-mentioned radial direction, the annular ribs 132 are divided into the first annular rib 132 and the second annular rib 132. The first annular rib 132 and the lower chord 112 of the rudder frame 11 form the first area, the first annular rib 132 and the second annular rib 132 form the second area, and the rest is the third area. The variable thickness design of the rudder surface 14 is reflected in that the thickness of the first area, the second area and the third area decreases in sequence. The present application provides a method based on Figure 2 In the specific scheme of the variable thickness design of the rudder surface 14 of the scheme shown, the thickness of the first area, the second area and the third area are 1.8mm, 1.2mm and 0.8mm respectively. If there are more than two annular ribs 132 in the scheme, the variable thickness design of the rudder surface 14 is analogous to the above rules.

[0054] Please refer to Figure 2 , Figure 2 The critical position of two adjacent regions is shown by the rudder surface thickness change line 141. It should be noted that at the critical point between the first region and the second region, the thickness of the rudder surface 14 does not change suddenly but changes gradually in a transitional manner, and the same is true for the critical point between the second region and the third region.

[0055] It should also be noted that the root 1314 of the rudder surface 14 corresponds to the root 1314 of the longitudinal rib 131, and the tip 1313 of the rudder surface 14 corresponds to the tip 1313 of the longitudinal rib 131, which respectively embody the root 1314 and the tip 1313 of the integrated rudder body 10. By designing the rudder surface 14 with variable thickness, the closer the rudder surface 14 is to the rudder shaft 12, the more mass distribution there is, and the closer the rudder surface 14 is to the tip 1313, the less mass distribution there is. This trend is consistent with the load-bearing trend of the air rudder when the aircraft is flying at high speed. By reducing the mass distribution of the air rudder tip 1313, the possibility of flutter of the air rudder in a vibration environment during high Mach number flight can be effectively reduced.

[0056] The above describes in detail the variable thickness design of the longitudinal rib 131 and the variable thickness design of the rudder surface 14, to which the concept of equal stiffness design can be applied, and these design schemes can be successfully manufactured through the process of integrated rudder body 3D printing.

[0057] By designing with equal stiffness, the mass distribution of the tip of the air rudder 1313 is reduced, and the possibility of flutter of the air rudder in a vibration environment during high Mach number flight can be effectively reduced. Equal stiffness design has a wide range of applications in material and structural design, making the stiffness distribution of the entire structure uniform, thereby improving the overall performance of the structure. In the scheme of the air rudder provided in the present application, the beneficial effect of the equal stiffness design is to reduce the mass distribution of the tip of the air rudder 1313, and effectively reduce the possibility of flutter of the air rudder in a vibration environment during high Mach number flight.

[0058] In some embodiments, please refer to Figure 2 and Figure 3 The longitudinal reinforcement 131 is an I-shaped structure, and the annular reinforcement 132 is connected in sequence by a plurality of I-shaped structures and is distributed in an annular direction as a whole. The I-shaped structure has good structural strength and structural strength, and in this scheme, the longitudinal reinforcement 131 and the annular reinforcement 132 of the I-shaped structure can ensure the smooth connection between the ribs 13 and the rudder surfaces 14 on both sides, which can be called a preferred scheme.

[0059] For further information, please refer to Figure 3 The longitudinal ribs 131 and the annular ribs 132 are both provided with lightening holes 134, and the purpose of reducing weight is achieved through the lightening holes 134. In some embodiments, the lightening holes 134 of the longitudinal ribs 131 are smaller, and the lightening holes 134 of the annular ribs 132 are larger, and the lightening holes 134 of the annular ribs 132 are hollowed out on the basis of the annular ribs 132.

[0060] In some embodiments, see Figure 2 The ribs 13 also include fan-shaped ribs 133, which are located at the junction of the rudder shaft 12 and the rudder frame 11, and are connected to the rudder shaft 12. The radius side of the fan-shaped ribs 133 is located at the lower chord 112 of the rudder frame 11, and the longitudinal ribs 131 are all connected to the fan-shaped ribs 133 and connected to the arc side of the fan-shaped ribs 133. The rudder shaft 12 is an important load-bearing and installation component. During the flight of the aircraft, the load of the rudder surface 14 is transmitted to the rudder shaft 12 through the longitudinal ribs 131 and the rudder surface 14, and the steering engine control torque is transmitted to the rudder surface 14 through the rudder shaft 12. The role of the fan-shaped ribs 133 in this embodiment is to perform a structural reinforcement design on the intersection area of ​​the roots 1314 of multiple longitudinal ribs 131, so as to ensure the reliability of the weak area in the load transmission path of the air rudder during the high Mach number flight of the aircraft.

[0061] In some embodiments, see Figure 4 The rudder shaft 12 is provided with a plurality of hollow holes 121 in the cylinder, and the hollow holes 121 are distributed along the axial direction of the cylinder. The plurality of hollow holes 121 are evenly spaced along the circumference of the cylinder. The cross section of a single hollow hole 121 perpendicular to the length direction of the hole is fan-shaped. The hollow holes 121 of the rudder shaft 12 are distributed in an axisymmetric manner. The purpose of providing the hollow holes 121 in the rudder shaft 12 is to reduce the weight of the air rudder while ensuring the strength and rigidity of the rudder shaft 12.

[0062] In some embodiments, the rudder leading edge 20 is fixedly connected to the front end 113 of the rudder frame 11 by a rivet 21. Figure 1 , Figure 2 and Figure 5, showing the rivet 21 and the installation position of the rivet 21, the rivet 21 is used to rivet the rudder leading edge 20 on the integrated rudder body 10, so that the rudder leading edge 20 is fixed and stably on the integrated rudder body 10, ensuring the ability of the rudder leading edge 20 to withstand the erosion of heat flow during flight.

[0063] It should be noted that the rivet 21 also needs to be resistant to high temperatures, so a high-temperature alloy rivet 21 is used to rivet the rudder leading edge 20 and the rudder frame 11. For example, the rivet 21 made of GH4169 can be used. GH4169 is a precipitation-strengthened nickel-based high-temperature alloy, which has good comprehensive properties in the temperature range of -253 to 650°C, and the yield strength below 650°C ranks first among deformed high-temperature alloys, and has good fatigue resistance, radiation resistance, oxidation resistance, corrosion resistance, and good processing and welding properties.

[0064] In some embodiments, the rivet 21 is a countersunk rivet 21, which ensures that the rudder surface 14 is smooth and has no protrusions after riveting, thereby ensuring that there is no local aerodynamic heating point on the rudder surface 14. In this embodiment, the thermal barrier coating 30 is only coated on the rudder surface 14 and does not cover the rudder leading edge 20, but the thermal barrier coating 30 must cover the rivet 21.

[0065] In some embodiments, please refer to Figure 1 , Figure 2 and Figure 5 The rudder leading edge 20 is provided with a plurality of mounting holes, which are sequentially distributed along the length direction of the rudder leading edge 20, and the rivet 21 is assembled through the mounting holes. The mounting holes include a round hole 211 and a waist-shaped hole 212. The diameter of the round hole 211 is equal to the diameter of the rivet 21, the width of the waist-shaped hole 212 is equal to the diameter of the rivet 21, and the length of the waist-shaped hole 212 is greater than the diameter of the rivet 21. In the process of riveting the rudder leading edge 20 and the rudder frame 11, the rudder frame 11 is provided with a rivet hole ( Figure 5 The rivet hole is not marked in the figure), and the rivet hole is butted with the mounting hole and is used together for the assembly of the rivet 21. A round hole 211 is butted with a rivet hole and a rivet 21 is installed. At this time, the round hole 211 plays a positioning role, and the waist-shaped hole 212 is longer than the diameter of the rivet hole. Under the condition that the rivet 21 is installed in the rivet hole, the installation position of the rivet 21 in the waist-shaped hole 212 can be adjusted. Therefore, the waist-shaped hole 212 can coordinate the deformation matching problem of the integrated rudder body 10 and the rudder leading edge 20 under high temperature conditions.

[0066] For example, when a rivet 21 with a diameter of 3 mm is used, the diameter of the round hole 211 is 3 mm, and the width and length of the waist-shaped hole 212 are 3 mm and 4 mm respectively.

[0067] In some embodiments, the mounting holes of the rudder leading edge 20 include two circular holes 211 and a plurality of waist-shaped holes 212. In the distribution mode in which the mounting holes are arranged in sequence along the length direction of the rudder leading edge 20, the two circular holes 211 are located in the middle of the distribution mode. Specifically, the two circular holes 211 are located at the center position in the length direction of the rudder leading edge 20, and the waist-shaped holes 212 are arranged on opposite sides of the circular holes 211. This embodiment is the embodiment preferred by the inventor. The distribution mode of the circular holes 211 and the waist-shaped holes 212 can also adopt other modes other than the above-mentioned embodiment.

[0068] In some embodiments, in order to strengthen the riveting effect between the rudder leading edge 20 and the rudder frame 11, please refer to Figure 1 , Figure 2 and Figure 5 A U-shaped groove is provided at the front end 113 of the rudder frame 11, the length direction of the U-shaped groove is the same as the length direction of the front end 113 of the rudder frame 11, the U-shaped groove forms an opening at the end of the front end 113 of the rudder frame 11, and the rudder leading edge 20 is provided with a long strip boss, the long strip boss is penetrated through the U-shaped groove, and the long strip boss is a specific part of the rudder leading edge 20 where a mounting hole for riveting is provided. The riveting effect that can be enhanced by this embodiment includes but is not limited to the tightness of riveting, the convenience during assembly, and the docking accuracy of the rudder leading edge 20 and the rudder frame 11.

[0069] The present application also provides an aircraft, which uses the above-mentioned air rudder, which is distributed on the outer surface of the servo cabin, and the air rudder bears the aerodynamic force and aerodynamic heat during the flight of the aircraft to achieve aircraft attitude control. The air rudder adopts the concept of lightweight, equal stiffness design and rudder body integration, and ensures the load-bearing capacity and heat protection capacity of the air rudder while meeting the requirements of lightweight, so that the aircraft with the air rudder can be applied to scenes with increasing speed.

[0070] In the present application, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0071] Although the preferred embodiments of the present invention 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 invention.

[0072] Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

Claims

1. An air rudder, characterized in that: include: An integrated rudder body, comprising a rudder frame, a rudder shaft and ribs connected to the rudder frame, and a rudder surface wrapped around the rudder frame and the ribs, wherein the integrated rudder body is configured to be formed by 3D printing; A rudder leading edge, mounted on the front end of the rudder frame; as well as A thermal barrier coating is coated on the rudder surface.

2. The air rudder according to claim 1, characterized in that: The ribs include: A plurality of longitudinal ribs are provided, and the plurality of longitudinal ribs are radially distributed outwards with the intersection of the rudder shaft and the rudder frame as the center; There is at least one annular rib, the annular rib is distributed in an annular direction, the intersection of the rudder shaft and the rudder frame is located at the annular center of the annular distribution, and the annular rib is connected to the longitudinal rib.

3. The air rudder according to claim 2, characterized in that: The longitudinal reinforcement is provided with: The length direction is the radiation direction radiating outward from the center; In the width direction, the rudder surface covers two opposite sides of the rudder frame, and the width direction is the same as the direction of the rudder surface on one side of the rudder frame pointing to the rudder surface on the other side; A thickness direction, perpendicular to both the length direction and the width direction; Wherein, the longitudinal ribs are provided with thickness dimensions along the thickness direction, and the thickness dimensions of the longitudinal ribs gradually decrease along the radiation direction.

4. The air rudder according to claim 3, characterized in that: The longitudinal reinforcement includes a first longitudinal reinforcement connected to the upper chord of the rudder frame and a second longitudinal reinforcement connected to the front end or the rear end of the rudder frame; The longitudinal rib is provided with a tip portion connected to the upper chord or the front end or the rear end of the rudder frame and a root portion relatively far away from the tip portion; The thickness dimension of the root portion of the first longitudinal rib is greater than the thickness dimension of the root portion of the second longitudinal rib, and the thickness dimension of the tip portion of the first longitudinal rib is greater than the thickness dimension of the tip portion of the second longitudinal rib.

5. The air rudder according to claim 2, characterized in that: At least one of the annular ribs divides the rudder surface located on the same side of the rudder frame into at least two partitions, and the thicknesses of at least the two partitions decrease successively along a radial direction radiating outward from the center.

6. The air rudder according to any one of claims 2 to 5, characterized in that: The longitudinal reinforcement is an I-shaped structure, and the annular reinforcement is a plurality of I-shaped structures connected in sequence and distributed in an annular direction as a whole; The longitudinal reinforcement and the annular reinforcement are both provided with lightening holes; The ribs also include fan-shaped ribs, which are located at the junction of the rudder shaft and the rudder frame, the fan-shaped ribs are connected to the rudder shaft, the radius side of the fan-shaped ribs is located at the lower chord of the rudder frame, and the longitudinal ribs are all connected to the fan-shaped ribs and connected to the arc side of the fan-shaped ribs.

7. The air rudder according to any one of claims 1 to 5, characterized in that: The rudder shaft is provided with a plurality of hollow holes in the cylinder portion, the hollow holes are distributed along the axial direction of the cylinder portion, and the plurality of hollow holes are evenly spaced and distributed along the circumference of the cylinder portion.

8. The air rudder according to any one of claims 1 to 5, characterized in that: The leading edge of the rudder is fixedly connected to the front end of the rudder frame through rivets.

9. The air rudder according to claim 8, characterized in that: The leading edge of the rudder is provided with a plurality of mounting holes sequentially distributed along the length direction, the mounting holes are used for assembling the rivets, the mounting holes include a circular hole located in the middle and waist-shaped holes located on both sides of the circular hole, the diameter of the circular hole is equal to the diameter of the rivet, the width of the waist-shaped hole is equal to the diameter of the rivet, and the length of the waist-shaped hole is greater than the diameter of the rivet; The rudder frame is provided with a riveting hole having a diameter equal to that of the rivet, and the riveting hole is butted against the mounting hole and is used together for assembling the rivet.

10. An aircraft, characterized in that: The utility model comprises air rudders as claimed in any one of claims 1 to 9 distributed on the outer surface of the servo cabin.

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