Air rudder

Abstract

The invention provides an air rudder, and belongs to the technical field of air rudders. The control surface skin is arranged outside the rudder skeleton and surrounds the rudder skeleton, the control surface skin is connected with the rudder skeleton, and a mounting cavity is formed between the control surface skin and the rudder skeleton; the rudder shaft is connected with the rudder framework and located at the bottom of the rudder framework; the rudder skeleton, the rudder surface skin and the rudder shaft are integrally formed through three-dimensional printing. The air rudder has the beneficial effects that the rudder framework, the rudder surface skin and the rudder shaft are integrally formed through three-dimensional printing, connection of the air rudder and an aircraft can be achieved, no screw or rivet or other connecting structures exist among the rudder framework, the rudder surface skin and the rudder shaft, the rigidity of the air rudder can be enhanced, the assembling clearance of the air rudder is reduced, the machining and assembling procedures are reduced, and the cost is reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of air rudders and relates to an air rudder. Background Art

[0002] The air rudder is a key component of the aircraft. It controls the flight attitude of the aircraft by rotating. The air rudder is installed on the outside of the aircraft.

[0003] In order to improve the combat effectiveness of the weapon platform, to carry as many missiles as possible under a limited load, and to meet the flight maneuverability requirements of the missiles, the use of low-cost and lightweight air rudders is an inevitable choice. In addition, my country's aircraft research has fully entered the hypersonic era. As a key component for flight attitude adjustment, air rudders are subjected to harsh thermal environments and high force loads during hypersonic flight, and often require complex structures to meet the use requirements, resulting in heavy weight and high cost of air rudders.

[0004] How to optimize the air rudder structure design to ensure the load-bearing capacity of the air rudder under thermal-mechanical coupling conditions, enhance the rigidity of the rudder surface skin to avoid flutter, while reducing the weight of the air rudder and the processing cost of the rudder surface skin to meet the needs of supersonic launches in large airspace is a key issue that needs to be solved urgently and has a lot of room for improvement. Summary of the invention

[0005] The purpose of the present invention is to propose an air rudder in view of the above problems existing in the prior art.

[0006] The object of the present invention can be achieved by the following technical solutions: an air rudder, comprising:

[0007] Rudder frame;

[0008] A rudder surface skin is arranged outside the rudder frame and surrounds the rudder frame, the rudder surface skin is connected to the rudder frame, and an installation cavity is formed between the rudder surface skin and the rudder frame;

[0009] A rudder shaft connected to the rudder frame and located at the bottom of the rudder frame;

[0010] The rudder frame, the rudder surface skin and the rudder shaft are integrally formed by three-dimensional printing.

[0011] In the above-mentioned air rudder, the rudder frame includes a transition portion and reinforcement ribs, the transition portion is connected to the bottom of the rudder surface skin and extends from the bottom of the rudder surface skin toward the mounting cavity, the transition portion is connected to the rudder surface skin through the reinforcement ribs, and the rudder shaft is connected to the transition portion.

[0012] In the above-mentioned air rudder, a weight-reducing chamber is provided in the transition portion, an air flow channel is provided on the rudder shaft, and the weight-reducing chamber is communicated with the outside through the air flow channel.

[0013] In the above-mentioned air rudder, the number of the reinforcing ribs is at least two, the reinforcing ribs separate the installation cavity and form sub-cavities whose number is one more than the number of the reinforcing ribs, and the wall of the sub-cavity is provided with a flow hole, which is connected to the weight reduction cavity or the outside world.

[0014] In the above-mentioned air rudder, the installation cavity is provided with a plurality of support units, and the support units include at least eight support half-rods, wherein one ends of the eight support half-rods are connected to one point, and the other ends of the eight support half-rods are respectively inclined to the XYZ three axes and are different from each other, and one support half-rod of one support unit is connected to one support half-rod of another support unit, and each support unit is connected to each other to form a rib-beam lattice structure, and the rib-beam lattice structure supports the rudder surface skin.

[0015] In the above-mentioned air rudder, the rudder surface skin includes a first compression surface, a second compression surface and a third compression surface, the first compression surface is provided with a first heat-resistant coating, the second compression surface and the third compression surface are provided with a second heat-resistant coating, and the maximum withstanding temperature of the first heat-resistant coating is greater than the maximum withstanding temperature of the second heat-resistant coating.

[0016] Secondly, an air rudder, comprising:

[0017] Rudder frame;

[0018] A rudder surface skin is arranged outside the rudder frame and surrounds the rudder frame, the rudder surface skin is connected to the rudder frame, and an installation cavity is formed between the rudder surface skin and the rudder frame;

[0019] A rudder shaft connected to the rudder frame and located at the bottom of the rudder frame;

[0020] The rudder surface skin includes a first compression surface, a second compression surface and a third compression surface. The first compression surface is provided with a first heat-resistant coating, and the second compression surface and the third compression surface are provided with a second heat-resistant coating. The maximum withstand temperature of the first heat-resistant coating is greater than the maximum withstand temperature of the second heat-resistant coating.

[0021] In the above-mentioned air rudder, the first heat protection coating is a coating combining zirconium oxide and a high-radiation coating or a zirconium oxide coating.

[0022] In the above-mentioned air rudder, the second heat protection coating is an epoxy coating.

[0023] In the above-mentioned air rudder, the rudder frame, the rudder surface skin and the rudder shaft are integrally formed by three-dimensional printing.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] 1. The rudder frame, rudder surface skin and rudder shaft are integrally formed by three-dimensional printing, which can realize the connection between the air rudder and the aircraft, and there is no connection structure such as screws or rivets between the three, which is conducive to enhancing the rigidity of the air rudder, reducing the assembly gap of the air rudder, reducing the processing and assembly procedures, and reducing costs.

[0026] 2. The key part of the rudder frame connecting the rudder shaft is the transition part. The transition part is connected to the bottom of the rudder surface skin and extends from the bottom of the rudder surface skin toward the installation cavity, which can enhance the strength of the transition part without affecting the shape of the bottom of the rudder surface skin. The transition part is connected to the rudder surface skin through reinforcing ribs, which enhances the connection strength between the transition part and the rudder surface skin.

[0027] 3. The weight-reducing cavity provided in the transition part reduces its own weight. The weight-reducing cavity provided in the transition part is connected with the outside world through the air flow channel in the rudder shaft to prevent the air from not circulating in the weight-reducing cavity under high temperature conditions, which may affect the transition part and cause deformation or even damage.

[0028] 4. Each supporting unit is interconnected to form a rib-beam lattice structure. The internal rib-beam lattice structure after topological optimization can achieve high load-bearing capacity of the air rudder in a high temperature environment and adapt to the aerodynamic and thermal load environment of high Mach number aircraft.

[0029] 5. A first heat-resistant coating with a higher maximum withstand temperature is arranged on the first compression surface of the rudder surface skin, and a second heat-resistant coating with a lower maximum withstand temperature but lower cost is arranged on the second compression surface and the third compression surface of the rudder surface skin. Different heat-resistant coatings are arranged at different positions of the rudder surface skin according to actual heating conditions to ensure the heat resistance of the air rudder and keep the cost low. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a schematic structural diagram of the air rudder of the present invention.

[0031] Figure 2 It is a top view of the air rudder of the present invention.

[0032] Figure 3 for Figure 2 Cross-sectional view from AA perspective.

[0033] Figure 4 for Figure 2 Cross-sectional view from BB perspective.

[0034] Figure 5It is a schematic structural diagram of the support unit of the present invention.

[0035] In the figure, 100, rudder frame; 110, transition part; 111, weight reduction cavity; 120, reinforcing rib; 200, rudder surface skin; 210, first compression surface; 220, second compression surface; 230, third compression surface; 300, installation cavity; 310, sub-cavity; 311, flow hole; 320, rib-beam lattice structure; 321, support unit; 3211, support half rod; 400, rudder shaft; 410, air flow channel. DETAILED DESCRIPTION

[0036] The following are specific embodiments of the present invention and the accompanying drawings to further describe the technical solution of the present invention, but the present invention is not limited to these embodiments.

[0037] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0038] In addition, in the present invention, descriptions such as "first", "second", "one", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0039] In the present invention, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0040] In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the fact that ordinary technicians in the field can implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0041] The specific embodiments described herein are merely examples of the spirit of the present invention. Those skilled in the art may make various modifications or additions to the specific embodiments described or replace them in similar ways, but they will not deviate from the spirit of the present invention or exceed the scope defined by the appended claims.

[0042] Embodiment 1

[0043] like Figure 1-Figure 5 As shown, an air rudder comprises a rudder frame 100 , a rudder surface skin 200 and a rudder shaft 400 .

[0044] The rudder surface skin 200 is arranged outside the rudder frame 100 and surrounds the rudder frame 100 . The rudder surface skin 200 is connected to the rudder frame 100 . An installation cavity 300 is formed between the rudder surface skin 200 and the rudder frame 100 .

[0045] The rudder shaft 400 is connected to the rudder frame 100 and is located at the bottom of the rudder frame 100 .

[0046] The rudder frame 100, the rudder surface skin 200 and the rudder shaft 400 are integrally formed by three-dimensional printing.

[0047] In this embodiment, the rudder frame 100, the rudder surface skin 200 and the rudder shaft 400 are integrally formed through three-dimensional printing, which can realize the connection between the air rudder and the aircraft without any connecting structure such as screws or rivets between the three, which is beneficial to enhance the rigidity of the air rudder, reduce the assembly clearance of the air rudder, reduce the processing and assembly steps, and reduce the cost.

[0048] Based on the above embodiment, the rudder frame 100 includes a transition portion 110 and a reinforcement rib 120. The transition portion 110 is connected to the bottom of the rudder surface skin 200 and extends from the bottom of the rudder surface skin 200 toward the mounting cavity 300. The transition portion 110 is connected to the rudder surface skin 200 through the reinforcement rib 120, and the rudder shaft 400 is connected to the transition portion 110.

[0049] In this embodiment, the key part of the rudder frame 100 connected to the rudder shaft 400 is the transition part 110. The transition part 110 is connected to the bottom of the rudder surface skin 200 and extends from the bottom of the rudder surface skin 200 toward the installation cavity 300, which can enhance the strength of the transition part 110 without affecting the shape of the bottom of the rudder surface skin 200. The transition part 110 is connected to the rudder surface skin 200 through the reinforcing ribs 120, which enhances the connection strength between the transition part 110 and the rudder surface skin 200.

[0050] On the basis of the above-mentioned embodiment, a weight-reducing chamber 111 is provided in the transition portion 110 , and an air flow channel 410 is provided in the rudder shaft 400 . The weight-reducing chamber 111 is communicated with the outside through the air flow channel 410 .

[0051] In this embodiment, the weight-reducing chamber 111 provided in the transition portion 110 reduces its own weight. The weight-reducing chamber 111 provided in the transition portion 110 is connected with the outside through the air flow channel 410 in the rudder shaft 400, thereby preventing the air from not circulating in the weight-reducing chamber 111 under high temperature conditions from affecting the transition portion 110, causing deformation or even damage.

[0052] Based on the above embodiment, the number of the reinforcing ribs 120 is at least two, and the reinforcing ribs 120 separate the installation cavity 300 and form a sub-cavity 310 whose number is one more than the number of the reinforcing ribs 120, and the wall of the sub-cavity 310 is provided with a flow hole 311, and the flow hole 311 is connected to the weight reduction cavity 111 or the outside world.

[0053] Specifically, the sub-chamber 310 close to the outside is communicated with the outside through the circulation hole 311 , and the remaining sub-chambers 310 are communicated with the weight reduction chamber 111 through the circulation hole 311 .

[0054] In this embodiment, at least two reinforcing ribs 120 can further enhance the connection strength between the transition portion 110 and the rudder surface skin 200, and the sub-cavities separated by the reinforcing ribs 120 are connected to the weight reduction cavity 111 or the outside through the circulation holes 311, thereby preventing the air in the sub-cavities 310 from being blocked under high temperature conditions, which may affect the rudder frame 100 or the rudder surface skin 200, causing deformation or even damage.

[0055] On the basis of the above embodiment, the installation cavity 300 is provided with a plurality of support units 320, and the support unit 320 includes at least eight support half rods 321, wherein one end of the eight support half rods 321 is connected to one point, and the other ends of the eight support half rods 321 are respectively inclined to the XYZ three axes and are different from each other, and a support half rod 321 of one support unit 320 is connected to a support half rod 321 of another support unit 320, and each support unit 320 is connected to each other to form a rib-beam lattice structure, and the rib-beam lattice structure supports the rudder skin 200.

[0056] In this embodiment, each support unit 320 is interconnected to form a rib-beam lattice structure. The internal rib-beam lattice structure after topological optimization can achieve high load-bearing capacity of the air rudder in a high temperature environment and adapt to the aerodynamic and thermal load environment of a high Mach number aircraft.

[0057] Based on the above embodiment, the rudder skin 200 includes a first compression surface 210, a second compression surface 220 and a third compression surface 230. The first compression surface 210 is provided with a first thermal protection coating, the second compression surface 220 and the third compression surface 230 are provided with a second thermal protection coating, and the maximum withstand temperature of the first thermal protection coating is greater than the maximum withstand temperature of the second thermal protection coating.

[0058] In this embodiment, a first heat-resistant coating with a higher maximum withstand temperature is provided on the first compression surface 210 of the rudder skin 200, and a second heat-resistant coating with a lower maximum withstand temperature but lower cost is provided on the second compression surface 220 and the third compression surface 230 of the rudder skin 200. In this way, different heat-resistant coatings are provided at different positions of the rudder skin 200 according to actual heating conditions to ensure the heat resistance of the air rudder and maintain low cost.

[0059] Embodiment 2

[0060] like Figure 1-Figure 5 As shown, an air rudder comprises a rudder frame 100 , a rudder surface skin 200 and a rudder shaft 400 .

[0061] The rudder surface skin 200 is arranged outside the rudder frame 100 and surrounds the rudder frame 100 . The rudder surface skin 200 is connected to the rudder frame 100 . An installation cavity 300 is formed between the rudder surface skin 200 and the rudder frame 100 .

[0062] The rudder shaft 400 is connected to the rudder frame 100 and is located at the bottom of the rudder frame 100 .

[0063] Among them, the rudder skin 200 includes a first compression surface 210, a second compression surface 220 and a third compression surface 230, the first compression surface 210 is provided with a first heat-resistant coating, the second compression surface 220 and the third compression surface 230 are provided with a second heat-resistant coating, and the maximum withstanding temperature of the first heat-resistant coating is greater than the maximum withstanding temperature of the second heat-resistant coating.

[0064] In this embodiment, a first heat-resistant coating with a higher maximum withstand temperature is provided on the first compression surface 210 of the rudder skin 200, and a second heat-resistant coating with a lower maximum withstand temperature but lower cost is provided on the second compression surface 220 and the third compression surface 230 of the rudder skin 200. In this way, different heat-resistant coatings are provided at different positions of the rudder skin 200 according to actual heating conditions to ensure the heat resistance of the air rudder and maintain low cost.

[0065] Based on the above implementation, the first heat protection coating is a coating combining zirconium oxide and a high-radiation coating or a zirconium oxide coating.

[0066] In this embodiment, the first heat-resistant coating is a coating combining zirconium oxide and a high-radiation coating or a zirconium oxide coating, which improves the heat resistance of the low-cost air rudder and can withstand high temperatures above 1200°C.

[0067] Based on the above implementation, the second heat-resistant coating is an epoxy coating.

[0068] In this embodiment, the second thermal protection coating is an epoxy coating, which has the characteristics of low thermal conductivity, low density and low cost. Replacing the first thermal protection coating on the entire air rudder with a local second thermal protection coating can effectively reduce the cost of the air rudder.

[0069] On the basis of the above-mentioned embodiment, the rudder frame 100, the rudder surface skin 200 and the rudder shaft 400 are integrally formed by three-dimensional printing.

[0070] In this embodiment, the rudder frame 100, the rudder surface skin 200 and the rudder shaft 400 are integrally formed through three-dimensional printing, which can realize the connection between the air rudder and the aircraft without any connecting structure such as screws or rivets between the three, which is beneficial to enhance the rigidity of the air rudder, reduce the assembly clearance of the air rudder, reduce the processing and assembly steps, and reduce the cost.

Claims

1. An air rudder, characterized in that: include: Rudder frame; A rudder surface skin is arranged outside the rudder frame and surrounds the rudder frame, the rudder surface skin is connected to the rudder frame, and an installation cavity is formed between the rudder surface skin and the rudder frame; A rudder shaft connected to the rudder frame and located at the bottom of the rudder frame; The rudder frame, the rudder surface skin and the rudder shaft are integrally formed by three-dimensional printing.

2. An air rudder as claimed in claim 1, characterized in that: The rudder frame includes a transition portion and a reinforcing rib, wherein the transition portion is connected to the bottom of the rudder surface skin and extends from the bottom of the rudder surface skin toward the mounting cavity, the transition portion is connected to the rudder surface skin through the reinforcing rib, and the rudder shaft is connected to the transition portion.

3. An air rudder as claimed in claim 2, characterized in that: A weight-reducing chamber is arranged in the transition part, and an air flow channel is arranged in the rudder shaft, and the weight-reducing chamber is communicated with the outside through the air flow channel.

4. An air rudder as claimed in claim 3, characterized in that: The number of the reinforcing ribs is at least two, and the reinforcing ribs separate the installation cavity and form sub-cavities whose number is one more than the number of the reinforcing ribs. The wall of the sub-cavity is provided with a flow hole, and the flow hole is connected to the weight reduction cavity or the outside.

5. An air rudder as claimed in claim 1, characterized in that: The installation cavity is provided with a plurality of support units, and the support units include at least eight support half rods, wherein one ends of the eight support half rods are connected to one point, and the other ends of the eight support half rods are respectively inclined to the XYZ three axes and are different from each other, and one support half rod of one support unit is connected to one support half rod of another support unit, and the support units are connected to each other to form a rib-beam lattice structure, and the rib-beam lattice structure supports the rudder surface skin.

6. An air rudder as claimed in claim 1, characterized in that: The rudder surface skin includes a first compression surface, a second compression surface and a third compression surface. The first compression surface is provided with a first heat-resistant coating, and the second compression surface and the third compression surface are provided with a second heat-resistant coating. The maximum withstand temperature of the first heat-resistant coating is greater than the maximum withstand temperature of the second heat-resistant coating.

7. An air rudder, characterized in that: include: Rudder frame; A rudder surface skin is arranged outside the rudder frame and surrounds the rudder frame, the rudder surface skin is connected to the rudder frame, and an installation cavity is formed between the rudder surface skin and the rudder frame; A rudder shaft connected to the rudder frame and located at the bottom of the rudder frame; The rudder surface skin includes a first compression surface, a second compression surface and a third compression surface. The first compression surface is provided with a first heat-resistant coating, and the second compression surface and the third compression surface are provided with a second heat-resistant coating. The maximum withstand temperature of the first heat-resistant coating is greater than the maximum withstand temperature of the second heat-resistant coating.

8. An air rudder as claimed in claim 7, characterized in that: The first heat protection coating is a coating combining zirconium oxide and a high-radiation coating or a zirconium oxide coating.

9. An air rudder as claimed in claim 7, characterized in that: The second heat-resistant coating is an epoxy coating.

10. An air rudder as claimed in claim 7, characterized in that: The rudder frame, the rudder surface skin and the rudder shaft are integrally formed by three-dimensional printing.

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