High-bearing heat prevention and insulation integrated control surface structure

Abstract

The invention discloses a high-bearing heat prevention and insulation integrated control surface structure, and belongs to the technical field of aircraft control surface structures. The control surface structure solves the problem that a control surface structure in the prior art is difficult to meet the comprehensive performance requirements of high bearing and heat prevention and insulation at the same time. The device specifically comprises a metal control surface, and a first heat-proof skin and a second heat-proof skin are arranged on the two sides of the metal control surface respectively; a first heat insulation skin is arranged between the metal control surface and the first heat protection skin, and a second heat insulation skin is arranged between the metal control surface and the second heat protection skin; the front end of the metal control surface is connected with a front edge assembly. According to the invention, the metal control surface is used as a main force bearing structure of the control surface structure, so that the overall bearing capacity and stability of the control surface structure can be enhanced; two sides of the metal control surface are respectively provided with two heat-proof skins for protection, so that the phenomena of thermal expansion, thermal fatigue and the like of the metal control surface in a high-speed flight or high-temperature environment are avoided; and the problems of connecting piece failure and structural damage caused by deformation difference after the metal material and the heat-proof skin material are heated are also prevented.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft control surface structures, and in particular to a high-load-bearing, heat-insulating integrated control surface structure. Background Art

[0002] With the rapid development of aerospace technology, the requirements for aircraft control surfaces are becoming increasingly stringent. Traditional control surfaces are usually made of metal or alloy materials. Although they have certain load-bearing capacity and durability, metal control surfaces are prone to thermal expansion and thermal fatigue when flying at high speeds or in high-temperature environments, leading to structural deformation, cracks, and even failure. Therefore, metal control surfaces often cannot meet the requirements of high load-bearing capacity and heat insulation performance at the same time, which greatly limits the application of aircraft in extreme environments.

[0003] In order to solve this problem, composite materials are used instead of metal materials to prepare aircraft control surfaces in the prior art. For example, high-performance materials such as ceramics and carbon fibers are used to replace traditional metal materials to improve the high temperature resistance of the control surfaces. However, these high-performance composite materials are not only expensive, but also have an extreme load-bearing capacity that is inferior to that of metal materials. It is difficult to simultaneously meet the comprehensive requirements of the control surface structure for high load-bearing and heat-insulating performance; therefore, the control surface structure of the composite material still cannot meet the use requirements of the aircraft. Therefore, the present invention provides a new control surface structure that integrates high load-bearing capacity and heat-insulating performance, which is of great significance for improving the overall performance and reliability of the aircraft. Summary of the invention

[0004] In view of the deficiencies in the prior art, the present invention provides a high-load-bearing and heat-insulating integrated rudder surface structure, which solves the problem that the rudder surface structure in the prior art is difficult to simultaneously meet the comprehensive performance requirements of high load-bearing and heat-insulating.

[0005] In order to achieve the above object, the technical solution adopted by the present invention is:

[0006] A high-load-bearing, heat-insulating integrated rudder surface structure comprises a metal rudder surface, wherein a first heat-insulating skin and a second heat-insulating skin are respectively provided on both sides of the metal rudder surface; a first heat-insulating skin is provided between the metal rudder surface and the first heat-insulating skin, and a second heat-insulating skin is provided between the metal rudder surface and the second heat-insulating skin; a leading edge assembly is connected to the front end of the metal rudder surface.

[0007] In this scheme, the metal rudder surface serves as the main load-bearing structure of the rudder surface structure. The use of metal materials can effectively enhance the overall load-bearing capacity and stability of the rudder surface structure. The first heat-proof skin and the second heat-proof skin are respectively arranged on both sides of the metal rudder surface for protection to prevent the metal rudder surface from thermal expansion, thermal fatigue and the like during high-speed flight or high-temperature environment. At the same time, the design of the first heat-proof skin and the second heat-proof skin is convenient for later assembly. The first thermal insulation skin can prevent heat from being transferred to the metal rudder surface, thereby preventing the metal rudder surface from being deformed due to heat, and also preventing the failure of connectors and structural damage caused by the difference in deformation between the metal material and the heat-proof skin material after heating.

[0008] Furthermore, the leading edge assembly includes a metal leading edge, which is connected to the front end of the metal rudder surface; the metal leading edge is wrapped with a heat-insulating leading edge; and the heat-insulating leading edge is wrapped with a heat-resistant leading edge.

[0009] Furthermore, the heat protection leading edge includes a first heat protection leading edge and a second heat protection leading edge, and the first heat protection leading edge and the second heat protection leading edge are wrapped on the heat insulation leading edge; a tenon is provided at the end of the first heat protection leading edge, and the tenon is embedded in the tenon groove at the end of the second heat protection leading edge for connection.

[0010] In this scheme, the thermal stress is greater when the leading edge of the rudder structure is longer, and the heat-proof leading edge is designed to be a first heat-proof leading edge and a second heat-proof leading edge to avoid excessive internal stress and fracture caused by heating of the leading edge; the first heat-proof leading edge and the second heat-proof leading edge are connected by mortise and tenon joints to prevent the airflow from directly eroding the insulation leading edge through the connection gap between the two, and to prevent the airflow from washing into the interior of the rudder structure, effectively resisting the impact and ablation of the external extreme thermal environment, and ensuring the overall structural integrity of the rudder.

[0011] Furthermore, a 0.5 mm expansion joint is reserved at the connection between the first heat protection front edge and the second heat protection front edge.

[0012] In this solution, when the leading edge position is heated, the first heat-proof leading edge and the second heat-proof leading edge can make adaptive deformation toward the expansion joint to avoid damage to the leading edge structure.

[0013] Furthermore, the positions of the splicing seam between the first heat-proof skin and the second heat-proof skin and the splicing seam between the first heat-insulating skin and the second heat-insulating skin are staggered.

[0014] In this solution, the design can effectively prevent external high-temperature airflow from penetrating into the interior of the rudder surface structure and directly corroding the metal rudder surface, thereby avoiding damage to the interior of the rudder surface structure.

[0015] Furthermore, the metal rudder surface, the first heat protection skin, the second heat protection skin, the first heat insulation skin and the second heat insulation skin are connected by a plurality of double-head rivets.

[0016] Furthermore, each double-headed rivet is provided with two ring-mounted gaskets, which are respectively embedded in circular grooves opened on the surfaces of the first thermal insulation skin and the second thermal insulation skin; one end of the double-headed rivet is embedded in the countersunk hole opened on the surface of the first thermal insulation skin, and the other end of the double-headed rivet is welded to the second thermal insulation skin.

[0017] In this solution, ring-mounted gaskets are embedded in the surfaces of the first thermal insulation skin and the second thermal insulation skin. Under the eccentric load of aerodynamic pressure on the two outer thermal insulation skins, the two thermal insulation skins may be compressed on one side, causing the outer thermal insulation skin to shift and be unable to move with the metal rudder surface. The ring-mounted gasket can support the flexible thermal insulation skin to prevent the outer thermal insulation skin from shifting and causing aerodynamic shape instability.

[0018] Furthermore, a gap of 0.2 mm is reserved between the center hole of the ring-mounted gasket and the double-headed rivet.

[0019] In this solution, the reserved gap can solve the problem of thermal adaptation between metal materials and composite materials, and prevent the failure of connectors and structural damage caused by differences in thermal expansion.

[0020] Furthermore, the material of the first heat-proof skin and the second heat-proof skin is C / SiC composite material; the material of the first heat-insulating skin and the second heat-insulating skin is aerogel composite material.

[0021] Furthermore, a plurality of weight-reducing holes are provided on the metal rudder surface.

[0022] In this solution, the design of the weight-reducing holes can make the overall rudder structure lighter.

[0023] The beneficial effects of the present invention are:

[0024] In the high-load-bearing heat-insulating integrated rudder surface structure provided by the present invention, the first heat-proof skin and the second heat-proof skin made of C / SiC composite material are used to protect the metal rudder surface, which not only realizes the high load-bearing capacity of the rudder surface structure, but also improves the heat-insulating property of the rudder surface structure, breaking through the limitations of the traditional rudder surface structure in load-bearing capacity and heat-insulating performance. A heat-insulating skin is designed between the two heat-proof skins and the metal rudder surface to block the transfer of heat to the metal rudder surface, avoid heating of the metal rudder surface, solve the problem of thermal adaptation between the metal material and the C / SiC composite material, and effectively prevent the failure of the connector and structural damage caused by the difference in the extension of the two materials when heated. A ring-mounted gasket is designed on the flexible heat-insulating skin to support the heat-insulating skin to prevent the aerodynamic shape from being instability due to the displacement of the external heat-proof skin caused by unilateral compression and the inability to move with the metal rudder surface. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 An exploded view of a high-load-bearing, heat-insulating integrated rudder surface structure of the present invention;

[0026] Figure 2 This is a structural schematic diagram of a high-load-bearing, heat-insulating integrated rudder surface structure of the present invention;

[0027] Figure 3 Schematic diagram of the structure of the first heat protection front edge and the second heat protection front edge of the present invention;

[0028] Figure 4 It is a schematic diagram of the structure of the double-head rivet and the ring-mounted gasket of the present invention.

[0029] Reference numerals:

[0030] 1. Metal rudder surface; 11. Weight reduction hole; 2. First heat protection skin; 3. Second heat protection skin; 4. First heat insulation skin; 5. Second heat insulation skin; 6. Leading edge assembly; 61. Metal leading edge; 62. Heat insulation leading edge; 63. Heat protection leading edge; 631. First heat protection leading edge; 632. Second heat protection leading edge; 7. Double-headed rivet; 71. Ring-mounted gasket; 72. Circular groove; DETAILED DESCRIPTION

[0031] The present invention is further described below in conjunction with the accompanying drawings and specific embodiments. The specific implementation of the present invention is described below to facilitate the understanding of the present invention by those skilled in the art, but it should be clear that the present invention is not limited to the scope of the specific implementation. For those of ordinary skill in the art, as long as various changes are within the spirit and scope of the present invention defined and determined by the attached claims, these changes are obvious, and all inventions and creations using the concept of the present invention are protected.

[0032] like Figure 1 and Figure 2 As shown, this embodiment provides a high-load-bearing and heat-insulating integrated rudder structure, in which the load-bearing structure of the rudder structure is prepared by metal materials, and the load-bearing structure is protected by a heat-proof skin made of C / SiC composite material, so that the high load-bearing capacity of the rudder structure is achieved, and the heat-insulating property of the rudder structure is improved, breaking through the limitations of the traditional rudder structure in load-bearing capacity and heat-insulating performance; it specifically includes:

[0033] Metal control surface 1, first heat protection skin 2, second heat protection skin 3, first heat insulation skin 4, second heat insulation skin 5 and leading edge assembly 6;

[0034] Among them, the metal control surface 1 is the main load-bearing structure of the control surface structure; the first heat-proof skin 2 and the second heat-proof skin 3 are respectively provided on both sides of the metal control surface 1, and the first heat-proof skin 2 and the second heat-proof skin 3 can protect the metal control surface 1 to prevent the metal control surface 1 from thermal expansion, thermal fatigue and other phenomena during high-speed flight or high-temperature environment; a first thermal insulation skin 4 is provided between the metal control surface 1 and the first thermal insulation skin 2, and a second thermal insulation skin 5 is provided between the metal control surface 1 and the second thermal insulation skin 3. The first thermal insulation skin 4 and the second thermal insulation skin 5 are used to prevent heat from being transferred to the metal control surface 1; the front end of the metal control surface 1 is connected to a leading edge assembly 6.

[0035] The leading edge assembly 6 comprises a metal leading edge 61 , which is connected to the front end of the metal rudder surface 1 ; the metal leading edge 61 is wrapped with a heat-insulating leading edge 62 ; the heat-insulating leading edge 62 is wrapped with a heat-resistant leading edge 63 .

[0036] like Figure 3 As shown, the heat protection leading edge 63 includes a first heat protection leading edge 631 and a second heat protection leading edge 632, and the first heat protection leading edge 631 and the second heat protection leading edge 632 are wrapped on the heat insulation leading edge 62; when the leading edge of the rudder structure is long, the thermal stress is large, and the heat protection leading edge 63 is designed as the first heat protection leading edge 631 and the second heat protection leading edge 632 to avoid excessive internal stress and fracture caused by heating of the leading edge. A tenon is provided at the end of the first heat protection leading edge 631, and the tenon is embedded in the tenon groove at the end of the second heat protection leading edge 632 for connection; this design prevents the airflow from directly eroding the heat insulation leading edge 62 through the connection gap between the two, and prevents the airflow from washing into the interior of the rudder structure, effectively resisting the impact and ablation of the external extreme thermal environment, and ensuring the integrity of the overall structure of the rudder.

[0037] A 0.5 mm expansion joint is reserved at the connection between the first heat protection leading edge 631 and the second heat protection leading edge 632; when the leading edge is heated, the first heat protection leading edge 631 and the second heat protection leading edge 632 can make adaptive deformation toward the expansion joint to avoid damage to the leading edge structure.

[0038] The heat-insulating leading edge 62 is designed as an integral molding, and can be directly put on the front end of the metal rudder 1 during assembly; the leading edge is located at the front end of the aircraft, and needs to withstand severe high-temperature airflow erosion and ablation during the operation of the aircraft. The use of an integral heat-insulating leading edge 62 can effectively isolate the high-temperature airflow from entering the interior, protecting the internal structure from heat damage.

[0039] The positions of the splicing seams between the first heat-proof skin 2 and the second heat-proof skin 3 and the splicing seams between the first heat-insulating skin 4 and the second heat-insulating skin 5 are staggered with each other; this design can effectively prevent external high-temperature airflow from penetrating into the interior of the rudder surface structure and directly corroding the metal rudder surface 1, thereby avoiding damage to the interior of the rudder surface structure.

[0040] like Figure 4As shown, the metal rudder surface 1, the first heat-proof skin 2, the second heat-proof skin 3, the first heat-insulating skin 4 and the second heat-insulating skin 5 are connected by a plurality of double-headed rivets 7.

[0041] Two ring-mounted gaskets 71 are provided on each double-headed rivet 7, and the two ring-mounted gaskets 71 are respectively embedded in circular grooves 72 opened on the surfaces of the first thermal insulation skin 4 and the second thermal insulation skin 5; the ring-mounted gaskets 71 are embedded on the surfaces of the first thermal insulation skin 4 and the second thermal insulation skin 5. Under the eccentric load effect of aerodynamic pressure on the two external thermal insulation skins, the two thermal insulation skins may be compressed on one side, causing the external thermal insulation skin to deviate and fail to move with the metal rudder surface 1, while the ring-mounted gaskets 71 can support the flexible thermal insulation skin to avoid the external thermal insulation skin from deviating and causing aerodynamic shape instability.

[0042] One end of the double-head rivet 7 is embedded in the countersunk hole opened on the surface of the first heat-proof skin 2; the other end of the double-head rivet 7 is welded to the second heat-proof skin 3, and the welded end can be fused to form a structure similar to a countersunk nail, thereby fixing the second heat-proof skin 3.

[0043] A gap of 0.2 mm is reserved between the center hole of the ring gasket 71 and the double-headed rivet 7; a gap of 0.075 mm is reserved on one side between the double-headed rivet 7 and the first heat protection layer and the second heat protection layer; the reserved gap can solve the problem of thermal adaptation between metal materials and composite materials, and prevent the failure of connectors and structural damage caused by differences in thermal expansion.

[0044] The first heat protection skin 2 and the second heat protection skin 3 are made of C / SiC composite material; the first heat insulation skin 4 and the second heat insulation skin 5 are made of aerogel composite material.

[0045] A plurality of weight-reducing holes 11 are provided on the metal rudder surface 1; the design of the weight-reducing holes 11 can make the overall rudder structure lighter.

[0046] Those skilled in the art will appreciate that the embodiments herein are intended to help readers understand the principles of the present invention, and should be understood that the protection scope of the present invention is not limited to such specific statements and embodiments. Those skilled in the art can make various other specific variations and combinations that do not deviate from the essence of the present invention based on the technical revelations disclosed by the present invention, and these variations and combinations are still within the protection scope of the invention.

Claims

1. A high-load-bearing, heat-insulating integrated rudder structure, characterized by: The invention comprises a metal control surface (1), wherein a first heat-proof skin (2) and a second heat-proof skin (3) are respectively provided on both sides of the metal control surface (1); a first heat-insulating skin (4) is provided between the metal control surface (1) and the first heat-proof skin (2), and a second heat-insulating skin (5) is provided between the metal control surface (1) and the second heat-proof skin (3); and a leading edge assembly (6) is connected to the front end of the metal control surface (1).

2. The high-load-bearing heat-insulating integrated rudder surface structure according to claim 1 is characterized in that: The leading edge assembly (6) comprises a metal leading edge (61), wherein the metal leading edge (61) is connected to the front end of the metal rudder surface (1); the metal leading edge (61) is wrapped with a heat insulating leading edge (62); and the heat insulating leading edge (62) is wrapped with a heat-resistant leading edge (63).

3. The high-load-bearing heat-insulating integrated rudder surface structure according to claim 2 is characterized in that: The heat protection leading edge (63) comprises a first heat protection leading edge (631) and a second heat protection leading edge (632), wherein the first heat protection leading edge (631) and the second heat protection leading edge (632) are wrapped around the heat insulation leading edge (62); a tenon is provided at the end of the first heat protection leading edge (631), and the tenon is embedded in the tenon groove at the end of the second heat protection leading edge (632) for connection.

4. The high-load-bearing, heat-insulating integrated rudder structure according to claim 3 is characterized in that: A 0.5 mm expansion joint is reserved at the connection between the first heat protection front edge (631) and the second heat protection front edge (632).

5. The high-load-bearing heat-insulating integrated rudder surface structure according to claim 1 is characterized in that: The positions of the splicing seam between the first heat-proof skin (2) and the second heat-proof skin (3) and the splicing seam between the first heat-insulating skin (4) and the second heat-insulating skin (5) are staggered.

6. The high-load-bearing heat-insulating integrated rudder surface structure according to claim 1 is characterized in that: The metal rudder surface (1), the first heat-proof skin (2), the second heat-proof skin (3), the first heat-insulating skin (4) and the second heat-insulating skin (5) are connected via a plurality of double-headed rivets (7).

7. The high-load-bearing heat-insulating integrated rudder surface structure according to claim 6 is characterized in that: Each of the double-headed rivets (7) is provided with two annular gaskets (71), and the two annular gaskets (71) are respectively embedded in circular grooves (72) opened on the surfaces of the first heat-insulating skin (4) and the second heat-insulating skin (5); One end of the double-headed rivet (7) is embedded in a countersunk hole opened on the surface of the first heat-resistant skin (2), and the other end of the double-headed rivet (7) is welded to the second heat-resistant skin (3).

8. The high-load-bearing heat-insulating integrated rudder surface structure according to claim 7 is characterized in that: A gap of 0.2 mm is reserved between the center hole of the annular gasket (71) and the double-headed rivet (7).

9. The high-load-bearing heat-insulating integrated rudder structure according to any one of claims 1 to 8, characterized in that: The first heat-proof skin (2) and the second heat-proof skin (3) are made of C / SiC composite material; the first heat-insulating skin (4) and the second heat-insulating skin (5) are made of aerogel composite material.

10. The high-load-bearing heat-insulating integrated rudder structure according to any one of claims 1 to 8, characterized in that: The metal rudder surface (1) is provided with a plurality of weight-reducing holes (11).

Images