High-temperature-resistant wave-transparent wing structure and aircraft

Abstract

The invention provides a high temperature resistant wave-transparent wing structure and an aircraft, the high temperature resistant wave-transparent wing structure comprises a wing skeleton, a lower skin, a wingtip structure, an adjusting band plate and an upper skin, the skin can be independently used as the skin, and the skin and an antenna can be integrally formed and then installed on the wing skeleton in a blocking manner. And when the wing skin is independently used as the skin, the antenna is mounted on a spar and a side rib of the wing framework. The high-speed flight platform wingtip structure and the antenna can be integrally formed into a wingtip antenna integrated structure, and the high-speed flight platform wingtip structure and the antenna can also be independently prepared into a wingtip antenna separated structure. A connector, a secondary spar, a wing rib and a bevel edge rib of the wing framework are made of high-temperature-resistant resin-based composite materials, and a main spar, a main wing rib and a rear main spar are made of high-temperature-resistant titanium alloy materials. According to the technical scheme, the technical problems that in the prior art, titanium alloy is adopted as a wing bearing structure material, the wave transmission performance is not achieved, and the early warning detection capacity of a high-speed flight platform is greatly restricted are solved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a high-temperature resistant and wave-transparent wing structure and an aircraft. Background Art

[0002] The sensor aircraft is a new concept unmanned aerial vehicle proposed by the United States. It can stay in the air for a long time and perform reconnaissance missions through the integrated sensors carried on board. The current high-speed flight platform can reach a flight speed of Ma2 to 3.5, requiring the wing structure to have a certain early warning and detection capability while being resistant to high temperatures, load-bearing, and shape-maintaining. However, in order to withstand the high temperature environment (200℃-400℃), high-speed flight platforms mostly use titanium alloy as the wing load-bearing structural material, which does not have wave-transmitting properties. This greatly restricts the early warning and detection capabilities of high-speed flight platforms. Summary of the invention

[0003] The present invention provides a high-temperature resistant and wave-transparent wing structure and an aircraft, which can solve the technical problem in the prior art that titanium alloy is used as the wing load-bearing structural material, has no wave-transparent performance, and greatly restricts the early warning and detection capabilities of high-speed flight platforms.

[0004] According to one aspect of the present invention, a high-temperature resistant and wave-transparent wing structure is provided, which comprises a wing frame, a lower skin, a wingtip structure, an adjustment strip and an upper skin, wherein the upper skin is arranged on the upper part of the wing frame, the lower skin is arranged on the lower part of the wing frame, the adjustment strip is arranged on one side of the wing frame, and the wingtip structure is arranged on the other side of the wing frame; the wing frame comprises a joint, a main wing rib, a first wing spar, a main wing spar, a second wing spar, a rear main wing spar, wing ribs and a bevel rib, the first wing spar, the main wing spar, the second wing spar and the rear main wing One end of the beam is connected to the main wing rib, the other ends of the first wing spar, the main wing spar, the second wing spar and the rear main wing spar are connected to the hypotenuse rib, one end of the wing rib is connected to the hypotenuse rib, and the other end of the wing rib is connected to the rear main wing spar; the joint, the first wing spar, the second wing spar, the wing rib and the hypotenuse rib are made of high-temperature resistant resin-based composite materials, and the main wing spar, the main wing rib and the rear main wing spar are made of high-temperature resistant titanium alloy materials; the antenna is installed between the areas surrounded by the main wing ribs, the first wing spar, the main wing spar, the second wing spar, the rear main wing spar, the wing ribs and the hypotenuse ribs, or the antenna is installed on the hypotenuse ribs.

[0005] Furthermore, the resin-based composite components are all prepared by an autoclave method, the matrix of the composite is prepared by bismaleimide resin, high-temperature resistant polyimide or phthalonitrile resin, and the reinforcement is glass fiber.

[0006] Furthermore, the joint, the main wing rib, the first wing spar, the main wing spar, the second wing spar, the rear main wing spar, the wing rib and the bevel rib are connected by adhesive bonding.

[0007] According to another aspect of the present invention, a high-temperature resistant and wave-transparent wing structure is provided, which includes a wing frame, a lower skin, a wingtip structure, an adjustment strip and an upper skin, wherein the upper skin is arranged on the upper part of the wing frame, the lower skin is arranged on the lower part of the wing frame, the adjustment strip is arranged on one side of the wing frame, and the wingtip structure is arranged on the other side of the wing frame; the wing frame includes a joint, a main wing rib, a first wing spar, a main wing spar, a second wing spar, a rear main wing spar, wing ribs and bevel ribs, and the first wing spar One end of the main wing spar, the second wing spar and the rear main wing spar are connected to the main wing rib, the other ends of the first wing spar, the main wing spar, the second wing spar and the rear main wing spar are connected to the hypotenuse rib, one end of the wing rib is connected to the hypotenuse rib, and the other end of the wing rib is connected to the rear main wing spar; the joints, the first wing spar, the second wing spar, the wing ribs and the hypotenuse ribs are made of high-temperature resistant resin-based composite materials, the main wing spar, the main wing ribs and the rear main wing spar are made of high-temperature resistant titanium alloy materials; the upper skin and the lower skin are integrated with the antenna and installed in blocks on the wing frame.

[0008] Furthermore, the resin-based composite components are all prepared by an autoclave method, the matrix of the composite is prepared by bismaleimide resin, high-temperature resistant polyimide or phthalonitrile resin, and the reinforcement is glass fiber.

[0009] According to another aspect of the present invention, a high-temperature resistant and wave-transparent wing structure is provided, which comprises a wing frame, a lower skin, a wingtip structure, an adjustment strip and an upper skin, wherein the upper skin is arranged on the upper part of the wing frame, the lower skin is arranged on the lower part of the wing frame, the adjustment strip is arranged on one side of the wing frame, and the wingtip structure is arranged on the other side of the wing frame; the wing frame comprises a joint, a main wing rib, a first wing spar, a main wing spar, a second wing spar, a rear main wing spar, wing ribs and bevel ribs, one end of the first wing spar, the main wing spar, the second wing spar and the rear main wing spar is connected to the main wing rib, and the first wing spar is connected to the main wing rib. The main wing spar, the second wing spar and the other end of the rear main wing spar are connected to the hypotenuse rib, one end of the wing rib is connected to the hypotenuse rib, and the other end of the wing rib is connected to the rear main wing spar; the joint, the first wing spar, the second wing spar, the wing rib and the hypotenuse rib are made of high-temperature resistant resin-based composite materials, and the main wing spar, the main wing rib and the rear main wing spar are made of high-temperature resistant titanium alloy materials; the wingtip structure and the antenna are integrated into a wingtip antenna integrated structure, the wingtip structure includes a wingtip lap, a ceramic panel and an aerogel interlayer, the wingtip antenna integrated structure is connected to the wing frame frame through the wingtip lap, and the antenna is integrated with the ceramic panel and the aerogel interlayer.

[0010] Furthermore, the ceramic panel may be made of materials such as quartz, silicon oxide, silicon carbide or aluminum oxide, and the ceramic panel and the nano-silicon oxide aerogel interlayer are connected and combined through ceramicized high-temperature resistant fibers to form a heat-proof and wave-transmitting material.

[0011] According to another aspect of the present invention, a high-temperature resistant and wave-transparent wing structure is provided, which comprises a wing frame, a lower skin, a wingtip structure, an adjustment strip and an upper skin, wherein the upper skin is arranged on the upper part of the wing frame, the lower skin is arranged on the lower part of the wing frame, the adjustment strip is arranged on one side of the wing frame, and the wingtip structure is arranged on the other side of the wing frame; the wing frame comprises a joint, a main wing rib, a first wing spar, a main wing spar, a second wing spar, a rear main wing spar, wing ribs and hypotenuse ribs, one end of the first wing spar, the main wing spar, the second wing spar and the rear main wing spar is connected to the main wing rib, and the other end of the first wing spar, the main wing spar, the second wing spar and the rear main wing spar is connected to the hypotenuse rib The wing tip and the antenna are connected, one end of the rib is connected to the hypotenuse rib, and the other end of the rib is connected to the rear main spar; the joint, the first spar, the second spar, the rib and the hypotenuse rib are made of high-temperature resistant resin-based composite materials, and the main spar, the main rib and the rear main spar are made of high-temperature resistant titanium alloy materials; the wing tip structure and the antenna are independently prepared to form a separate structure of the wing tip antenna, the wing tip structure includes a wing tip lap, a ceramic panel, a honeycomb filler and a polyimide thermal insulation pad, the wing tip antenna integrated structure is connected to the wing frame frame through the wing tip lap, and the ceramic panel and the honeycomb filler are integrated; the antenna is installed on the wing frame frame, and a polyimide thermal insulation pad is added between the two to prevent the wing frame from conducting heat to the antenna.

[0012] Further, the material of the honeycomb filler includes glass fiber or fiber foam.

[0013] According to yet another aspect of the present invention, there is provided an aircraft, the aircraft comprising the high temperature resistant and wave-transparent wing structure as described above.

[0014] By applying the technical solution of the present invention, a high-temperature resistant and wave-transparent wing structure is provided. The wave-transparent wing structure can play a synergistic role of high-temperature resistance, load-bearing, shape-maintaining and wave-transparent in a high-speed flight platform, realizes the integrated design of structure and function, and can realize the integrated integration of various types of antennas, greatly improving the survival and reconnaissance capabilities of the flight platform, and has good application prospects in engineering. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The included drawings are used to provide a further understanding of the embodiments of the present invention, which constitute a part of the specification, are used to illustrate the embodiments of the present invention, and together with the text description, explain the principles of the present invention. Obviously, the drawings in the following description are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0016] Attached Figure 1 The invention is a high-speed flight platform, comprising a wing frame (1), a lower skin (2), a wing tip structure (3), an adjustment strip (4) and an upper skin (5).

[0017] Attached Figure 2 The invention relates to a wing frame of a high-speed flight platform, comprising a wing joint (11), a main wing rib (12), a front secondary wing spar (13), a main wing spar (14), a rear secondary wing spar (15), a rear main wing spar (16), a wing rib (17), and a side rib (18).

[0018] Attached Figure 3 The invention relates to a wing tip of a high-speed flight platform, comprising a wing tip antenna integrated structure (31) and a wing tip antenna separated structure (32).

[0019] Attached Figure 4a ) is the integrated structural details of the wing tip antenna, including the wing frame frame (311), the wing tip lap edge (312), the antenna (313), the ceramic panel (314), and the aerogel interlayer (315); Figure 4b ) are separate structural details of the wing tip antenna, including a wing frame frame (321), a wing tip lap edge (322), an antenna (323), a ceramic panel (324), an aerogel interlayer (325), and a polyimide thermal insulation pad (326). DETAILED DESCRIPTION

[0020] It should be noted that, in the absence of conflict, the embodiments in this application and the features in the embodiments can be combined with each other. The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is by no means intended to limit the present invention and its application or use. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0021] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0022] Unless otherwise specifically stated, the relative arrangement of the parts and steps described in these embodiments, numerical expressions and numerical values ​​do not limit the scope of the present invention. At the same time, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to the actual proportional relationship. The technology, method and equipment known to ordinary technicians in the relevant field may not be discussed in detail, but in appropriate cases, the technology, method and equipment should be regarded as a part of the authorization specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0023] like Figures 1 to 4b As shown, according to a first embodiment of the present invention, a high-temperature resistant and wave-transparent wing structure is provided, which includes a wing frame 1, a lower skin 2, a wingtip structure 3, an adjustment strip plate 4 and an upper skin 5, wherein the upper skin 5 is arranged at the upper part of the wing frame 1, the lower skin 2 is arranged at the lower part of the wing frame 1, the adjustment strip plate 4 is arranged at one side of the wing frame 1, and the wingtip structure 3 is arranged at the other side of the wing frame 1; the wing frame 1 includes a joint 11, a main wing rib 12, a first wing spar 13, a main wing spar 14, a second wing spar 15, a rear main wing spar 16, a rib 17 and a bevel rib 18, and one end of the first wing spar 13, the main wing spar 14, the second wing spar 15 and the rear main wing spar 16 It is connected to the main wing rib 12, the other ends of the first wing spar 13, the main wing spar 14, the second wing spar 15 and the rear main wing spar 16 are connected to the hypotenuse rib 18, one end of the rib 17 is connected to the hypotenuse rib 18, and the other end of the rib 17 is connected to the rear main wing spar 16; the joint 11, the first wing spar 13, the second wing spar 15, the wing rib 17 and the hypotenuse rib 18 are made of high-temperature resistant resin-based composite materials, and the main wing spar 14, the main wing rib 12 and the rear main wing spar 16 are made of high-temperature resistant titanium alloy materials; the antenna is installed between the area enclosed by the main wing rib 12, the first wing spar 13, the main wing spar 14, the second wing spar 15, the rear main wing spar 16, the wing rib 17 and the hypotenuse rib 18, or the antenna is installed on the hypotenuse rib 18.

[0024] By applying this configuration, a high temperature resistant and wave-transparent wing structure is provided, wherein the lower skin 2, the wing tip structure 3, the adjustment strip 4 and the upper skin 5 are connected to the wing frame 1 to maintain the aerodynamic shape of the platform; the joint 11, the first wing spar 13, the second wing spar 15, the rib 17 and the bevel rib 18 are made of high temperature resistant resin-based composite materials, and the main wing spar 14, the main wing rib 12 and the rear main wing spar 16 are made of high temperature resistant titanium alloy materials. This design can ensure that the strength and stiffness of the main load-bearing joint and the main wing spar and wing rib frame structure meet the use requirements, and at the same time, other frame structures using resin-based composite materials ensure that the wing has good wave-transparent performance. The antenna can be installed between the areas enclosed by the main wing rib 12, the first wing spar 13, the main wing spar 14, the second wing spar 15, the rear main wing spar 16, the rib 17 and the bevel rib 18 according to the test field angle requirements, or the antenna is installed on the bevel rib 18. The antenna is installed between the areas enclosed by the main wing rib 12, the first wing spar 13, the main wing spar 14, the second wing spar 15, the rear main wing spar 16, the wing rib 17 and the bevel rib 18, or the antenna is installed on the bevel rib 18. Through the above design, the wing structure can meet the requirements of high temperature resistance of 200℃ to 400℃ and high strength bearing. According to analysis, the wing tip deformation of the wing structure is not greater than 5% of the half span of the wing surface. Therefore, compared with the prior art, the high temperature resistant and wave-transparent wing structure provided by the present invention can play a synergistic role in high temperature resistance, bearing, shape maintenance and wave transmission in high-speed flight platforms, realizes the integrated design of structure and function, and can realize the integrated integration of various types of antennas, greatly improving the survival and reconnaissance capabilities of the flight platform, and has good application prospects in engineering.

[0025] Furthermore, in the first embodiment, in order to ensure good wave transmission performance, the resin-based composite components are all prepared by autoclave method, the matrix of the composite is prepared by bismaleimide resin, high temperature resistant polyimide or phthalonitrile resin, and the reinforcement is glass fiber. The joint 11, the main rib 12, the first spar 13, the main spar 14, the second spar 15, the rear main spar 16, the rib 17 and the bevel rib 18 are connected by adhesive bonding.

[0026] According to the second embodiment of the present invention, a high temperature resistant and wave-transparent wing structure is provided. Different from the first embodiment, in this embodiment, the skin and the antenna are integrally formed and then separately installed on the wing frame. Specifically, the high temperature resistant and wave-transparent wing structure includes a wing frame 1, a lower skin 2, a wingtip structure 3, an adjustment strip 4 and an upper skin 5. The upper skin 5 is arranged on the upper part of the wing frame 1, the lower skin 2 is arranged on the lower part of the wing frame 1, the adjustment strip 4 is arranged on one side of the wing frame 1, and the wingtip structure 3 is arranged on the other side of the wing frame 1; the wing frame 1 includes a joint 11, a main wing rib 12, a first wing spar 13, a main wing spar 14, a second wing spar 15, a rear main wing spar 16, a rib 17 and a bevel rib 18, the first wing spar 13, the main wing spar 14, the second wing spar 15 and the rear One end of the main spar 16 is connected to the main wing rib 12, the other ends of the first spar 13, the main spar 14, the second spar 15 and the rear main spar 16 are connected to the hypotenuse rib 18, one end of the rib 17 is connected to the hypotenuse rib 18, and the other end of the rib 17 is connected to the rear main spar 16; the joint 11, the first spar 13, the second spar 15, the rib 17 and the hypotenuse rib 18 are made of high-temperature resistant resin-based composite materials, and the main spar 14, the main rib 12 and the rear main spar 16 are made of high-temperature resistant titanium alloy materials; the upper skin 5 and the lower skin 2 are integrated with the antenna and installed in blocks on the wing frame 1.

[0027] By using this configuration, a high temperature resistant and wave-transparent wing structure is provided. The lower skin 2, the wing tip structure 3, the adjustment strip 4 and the upper skin 5 are connected to the wing frame 1 to maintain the aerodynamic shape of the platform; the joint 11, the first wing spar 13, the second wing spar 15, the wing rib 17 and the bevel rib 18 are made of high temperature resistant resin-based composite materials, and the main wing spar 14, the main wing rib 12 and the rear main wing spar 16 are made of high temperature resistant titanium alloy materials. This design can ensure that the strength and stiffness of the main load-bearing joint and the main wing spar and wing rib frame structure meet the use requirements. At the same time, other frame structures using resin-based composite materials ensure that the wing has good wave-transparent performance. The upper skin 5 and the lower skin 2 are integrally formed with the antenna and installed in blocks on the wing frame 1. Through the above design, the wing structure can meet the requirements of high temperature resistance of 200℃ to 400℃ and high strength bearing. According to analysis, the wing tip deformation of the wing structure is not greater than 5% of the half span of the wing surface. Therefore, compared with the prior art, the high-temperature resistant and wave-transparent wing structure provided by the present invention can play a synergistic role in high-temperature resistance, load-bearing, shape-maintaining and wave-transparent performance in high-speed flight platforms, realizes the integrated design of structure and function, and can realize the integrated integration of various types of antennas, greatly improving the survival and reconnaissance capabilities of the flight platform, and has good application prospects in engineering.

[0028] In the second embodiment, in order to ensure good wave transmission performance, the resin-based composite components are all prepared by autoclave method, the matrix of the composite is made of bismaleimide resin, high temperature resistant polyimide or phthalonitrile resin, and the reinforcement is glass fiber.

[0029] According to the third embodiment of the present invention, a high temperature resistant and wave-transparent wing structure is provided. Different from the first and second embodiments, in this embodiment, the wing tip structure (3) can be integrated with the antenna to form a wing tip antenna integrated structure (31). Specifically, the high temperature resistant and wave-transparent wing structure includes a wing frame 1, a lower skin 2, a wing tip structure 3, an adjustment strip plate 4 and an upper skin 5, wherein the upper skin 5 is arranged on the upper part of the wing frame 1, the lower skin 2 is arranged on the lower part of the wing frame 1, the adjustment strip plate 4 is arranged on one side of the wing frame 1, and the wing tip structure 3 is arranged on the other side of the wing frame 1; the wing frame 1 includes a joint 11, a main wing rib 12, a first wing spar 13, a main wing spar 14, a second wing spar 15, a rear main wing spar 16, a wing rib 17 and a bevel rib 18, one end of the first wing spar 13, the main wing spar 14, the second wing spar 15 and the rear main wing spar 16 is connected to the main wing rib 12, and the other end of the first wing spar 13, the main wing spar 14, the second wing spar 15 and the rear main wing spar 16 is connected to the main wing rib 12. One end is connected to the hypotenuse rib 18, one end of the rib 17 is connected to the hypotenuse rib 18, and the other end of the rib 17 is connected to the rear main spar 16; the joint 11, the first spar 13, the second spar 15, the rib 17 and the hypotenuse rib 18 are made of high-temperature resistant resin-based composite materials, and the main spar 14, the main rib 12 and the rear main spar 16 are made of high-temperature resistant titanium alloy materials; the wingtip structure 3 and the antenna are integrated into a wingtip antenna integrated structure 31, the wingtip structure 3 includes a wingtip lap 312, a ceramic panel 314 and an aerogel interlayer 315, the wingtip antenna integrated structure is connected to the wing skeleton frame 311 (i.e., the hypotenuse rib 18) through the wingtip lap 312, and the antenna 313 is integrated with the ceramic panel 314 and the aerogel interlayer 315.

[0030] By using this configuration, a high temperature resistant and wave-transparent wing structure is provided. The lower skin 2, the wing tip structure 3, the adjustment strip 4 and the upper skin 5 are connected to the wing frame 1 to maintain the aerodynamic shape of the platform. The joint 11, the first wing spar 13, the second wing spar 15, the rib 17 and the bevel rib 18 are made of high temperature resistant resin-based composite materials, and the main wing spar 14, the main wing rib 12 and the rear main wing spar 16 are made of high temperature resistant titanium alloy materials. This design can ensure that the strength and rigidity of the main load-bearing joint and the main wing spar and wing rib frame structure meet the use requirements. At the same time, other frame structures using resin-based composite materials ensure that the wing has good wave-transparent performance. The wing tip structure 3 and the antenna are integrated into a wing tip antenna integrated structure 31. The wing tip structure 3 includes a wing tip lap 312, a ceramic panel 314 and an aerogel interlayer 315. The wing tip antenna integrated structure is connected to the wing frame frame 311 through the wing tip lap 312. The antenna 313 is integrated with the ceramic panel 314 and the aerogel interlayer 315. Through the above design, the wing structure can meet the requirements of high temperature resistance of 200℃~400℃ and high strength load bearing. After analysis, the wing tip deformation of the wing structure is no more than 5% of the half span of the wing surface. Therefore, compared with the prior art, the high temperature resistant and wave-transparent wing structure provided by the present invention can play a synergistic role in high temperature resistance, load bearing, shape maintenance and wave transmission in high-speed flight platforms, realize the integrated design of structure and function, realize the integrated integration of various types of antennas, greatly improve the survival and reconnaissance capabilities of the flight platform, and have good application prospects in engineering.

[0031] Furthermore, in the third embodiment, the ceramic panel 314 may be made of materials such as quartz, silicon oxide, silicon carbide or aluminum oxide, and the ceramic panel 314 and the nano-silicon oxide aerogel interlayer 315 are connected and combined through ceramic high-temperature resistant fibers to form a heat-proof and wave-transmitting material.

[0032] According to a fourth embodiment of the present invention, a high temperature resistant and wave-transparent wing structure is provided. Different from the first, second and third embodiments, in this embodiment, the wing tip structure and the antenna are independently prepared to form a wing tip antenna separate structure (32). Specifically, the high temperature resistant and wave-transmitting wing structure includes a wing frame 1, a lower skin 2, a wingtip structure 3, an adjustment strip 4 and an upper skin 5, wherein the upper skin 5 is arranged on the upper part of the wing frame 1, the lower skin 2 is arranged on the lower part of the wing frame 1, the adjustment strip 4 is arranged on one side of the wing frame 1, and the wingtip structure 3 is arranged on the other side of the wing frame 1; the wing frame 1 includes a joint 11, a main wing rib 12, a first wing spar 13, a main wing spar 14, a second wing spar 15, a rear main wing spar 16, a rib 17 and a hypotenuse rib 18, one end of the first wing spar 13, the main wing spar 14, the second wing spar 15 and the rear main wing spar 16 are connected to the main wing rib 12, the other end of the first wing spar 13, the main wing spar 14, the second wing spar 15 and the rear main wing spar 16 are connected to the hypotenuse rib 18, one end of the rib 17 is connected to the hypotenuse rib 18, and the rib 17 is connected to the hypotenuse rib 18. The other end is connected to the rear main wing spar 16; the joint 11, the first wing spar 13, the second wing spar 15, the rib 17 and the bevel rib 18 are made of high-temperature resistant resin-based composite materials, and the main wing spar 14, the main wing rib 12 and the rear main wing spar 16 are made of high-temperature resistant titanium alloy materials; the wingtip structure 3 and the antenna are independently prepared to form a wingtip antenna separate structure 32, the wingtip structure 3 includes a wingtip lap 322, a ceramic panel 324, a honeycomb filler 325 and a polyimide insulation pad 326, the wingtip antenna integrated structure is connected to the wing skeleton frame 321 (i.e., the bevel rib 18) through the wingtip lap 312, and the ceramic panel 324 and the honeycomb filler 325 are integrated; the antenna 323 is installed on the wing skeleton frame 321, and a polyimide insulation pad 326 is added between the two to prevent the wing skeleton frame 321 from conducting heat to the antenna 323.

[0033] By applying this configuration, a high-temperature resistant and wave-transparent wing structure is provided, in which the lower skin 2, the wingtip structure 3, the adjustment strap 4 and the upper skin 5 are connected to the wing frame 1 to maintain the aerodynamic shape of the platform; the joint 11, the first wing spar 13, the second wing spar 15, the wing rib 17 and the bevel rib 18 are made of high-temperature resistant resin-based composite materials, and the main wing spar 14, the main wing rib 12 and the rear main wing spar 16 are made of high-temperature resistant titanium alloy materials. This design can ensure that the strength and stiffness of the main load-bearing joints and the main wing spar and wing rib frame structure meet the use requirements. At the same time, other frame structures using resin-based composite materials ensure that the wing has good wave-transparent performance. The wing tip structure 3 and the antenna are independently prepared to form a wing tip antenna separate structure 32. The wing tip structure 3 includes a wing tip lap 322, a ceramic panel 324, a honeycomb filler 325 and a polyimide thermal insulation pad 326. The wing tip antenna integrated structure is connected to the wing frame frame 321 through the wing tip lap 312. The ceramic panel 324 and the honeycomb filler 325 are integrated. The antenna 323 is installed on the wing frame frame 321, and a polyimide thermal insulation pad 326 is added between the two to prevent the wing frame frame 321 from conducting heat to the antenna 323. Through the above design, the wing structure can meet the requirements of high temperature resistance of 200℃ to 400℃ and high strength bearing. According to analysis, the wing tip deformation of the wing structure is not more than 5% of the half span of the wing surface. Therefore, compared with the prior art, the high-temperature resistant and wave-transparent wing structure provided by the present invention can play a synergistic role in high-temperature resistance, load-bearing, shape-maintaining and wave-transparent performance in high-speed flight platforms, realizes the integrated design of structure and function, and can realize the integrated integration of various types of antennas, greatly improving the survival and reconnaissance capabilities of the flight platform, and has good application prospects in engineering.

[0034] Further, in the fourth embodiment, the material of the honeycomb filler 325 includes glass fiber or fiber foam.

[0035] According to yet another aspect of the present invention, there is provided an aircraft, the aircraft comprising the high temperature resistant and wave-transparent wing structure as described above.

[0036] By applying this configuration, an aircraft is provided. Since the wave-transmitting wing structure provided by the present invention can play a synergistic role in high temperature resistance, load bearing, shape maintenance, and wave transmission in a high-speed flight platform, a fusion design of structure and function is realized, and multiple types of antennas can be integrated, which greatly improves the survival and reconnaissance capabilities of the flight platform and has good application prospects in engineering. Therefore, the use of the wave-transmitting wing structure in an aircraft can greatly improve the working performance of the aircraft.

[0037] In order to further understand the present invention, the following Figures 1 to 4b The high temperature resistant and wave-transparent wing structure provided by the present invention is described in detail.

[0038] like Figures 1 to 4bAs shown, the present invention provides a high-temperature resistant and wave-transparent wing structure, which can play a synergistic role in high-temperature resistance, load-bearing, shape maintenance and wave transmission in a high-speed flight platform, thereby realizing a fusion design of structure and function.

[0039] like Figure 1 As shown, a high temperature resistant and wave-transmitting wing structure comprises a wing frame (1), a lower skin (2), a wing tip structure (3), an adjustment strap plate (4) and an upper skin (5). The skin (2), (5), the wing tip structure (3), the adjustment strap plate (4) are screwed to the wing frame (1) through a support plate nut to maintain the aerodynamic shape of the platform. The skin (2), (5) can be used as a skin alone, or can be integrated with the antenna and installed in blocks on the wing frame (1). When the wing skin (2), (5) is used as a skin alone, the antenna is installed on the wing beam and side rib of the wing frame (1).

[0040] like Figure 2 As shown, the joints (11), secondary spars (13), (15), ribs (17) and bevel ribs (18) of the wing frame (1) are made of high-temperature resistant resin-based composite materials, and the main spars (14), main ribs (12) and rear main spars (16) are made of high-temperature resistant titanium alloy materials. This design can ensure that the strength and stiffness of the main load-bearing joints and the main spars and rib frame structures meet the use requirements. At the same time, other frame structures using resin-based composite materials ensure that the wing has good wave transmission performance. The main spars (14) and the rear main spars (16) adopt a variable width design according to the structural stress characteristics. The antenna can be installed between the spars and ribs (12) to (18) according to the test field angle requirements, or it can be installed on the bevel rib (18). The resin-based composite components are all prepared by the autoclave method, and the components are bonded to ensure good wave transmission performance. The matrix of the composite material can be made of bismaleimide resin, high temperature resistant polyimide, or phthalonitrile resin, and the reinforcement is made of glass fiber. Through the above design, the wing structure can meet the requirements of high temperature resistance of 200℃ to 400℃ and high strength bearing. According to analysis, the wing tip deformation of the wing structure is no more than 5% of the half span of the wing surface.

[0041] like Figure 3 As shown, the wingtip structure (3) of the high-speed flight platform can be integrated with the antenna to form an integrated wingtip antenna structure (31), or can be independently prepared from the antenna to form a separate wingtip antenna structure (32).

[0042] like Figure 4a), the high-speed flight platform wing tip structure (3) can be integrated with the antenna to form a wing tip antenna integrated structure (31). The wing tip antenna integrated structure is connected to the wing skeleton frame (311) through the wing tip lap (312). The antenna (313) is integrated with the ceramic panel (314) and the aerogel interlayer (315). The ceramic panel can be made of materials such as quartz, silicon oxide, silicon carbide or aluminum oxide, and is connected and combined with the nano-silicon oxide aerogel insulation core layer through ceramicized high temperature resistant fibers to form a heat-proof and wave-transmitting material.

[0043] like Figure 4b ), the high-speed flight platform wing tip structure (3) and the antenna are independently prepared to form a wing tip antenna separate structure (32). The wing tip antenna integrated structure is connected to the wing frame frame (321) through the wing tip overlap (322). The ceramic panel (324) and the glass fiber honeycomb filler (325) are integrated; the antenna (323) is installed on the wing frame frame (321), and a polyimide insulation pad (326) is added between the two to prevent the wing frame frame (321) from conducting heat to the antenna (323). At the same time, the glass fiber honeycomb filler (325) can also be replaced by lightweight and high temperature resistant materials such as fiber foam. The wing tip main structure is located at the leading edge of the wing and can withstand temperatures of more than 450°C.

[0044] In summary, the present invention proposes a high-temperature resistant and wave-transparent wing structure, which can play a synergistic role in high-temperature resistance, load-bearing, shape-maintaining and wave-transparent performance in high-speed flight platforms, realizes the integrated design of structure and function, and can realize the integrated integration of various types of antennas, greatly improving the survival and reconnaissance capabilities of the flight platform, and can be widely used in the wave-transparent wing structures of high-speed aircraft and flight platforms.

[0045] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0046] In addition, it should be noted that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of the present invention.

[0047] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A high temperature resistant wave-transmitting wing structure, characterized in that: The high temperature resistant and wave-transmitting wing structure comprises a wing frame (1), a lower skin (2), a wing tip structure (3), an adjustment strap plate (4) and an upper skin (5), wherein the upper skin (5) is arranged on the upper part of the wing frame (1), the lower skin (2) is arranged on the lower part of the wing frame (1), the adjustment strap plate (4) is arranged on one side of the wing frame (1), and the wing tip structure (3) is arranged on the other side of the wing frame (1); The wing frame (1) comprises a joint (11), a main wing rib (12), a first wing spar (13), a main wing spar (14), a second wing spar (15), a rear main wing spar (16), a wing rib (17) and a bevel rib (18), wherein one end of the first wing spar (13), the main wing spar (14), the second wing spar (15) and the rear main wing spar (16) are connected to the main wing rib (12), and the first wing spar (13), the main wing spar (14), the second wing spar (15) and the rear main wing spar (16) are connected to the main wing rib (12), and the first wing spar (13), the main wing spar (14), the second wing spar (15) and the rear main wing spar (16) are connected to the main wing rib (12). The other end of the main spar (16) is connected to the hypotenuse rib (18), one end of the wing rib (17) is connected to the hypotenuse rib (18), and the other end of the wing rib (17) is connected to the rear main spar (16); the joint (11), the first spar (13), the second spar (15), the wing rib (17) and the hypotenuse rib (18) are made of high-temperature resistant resin-based composite materials, and the main spar (14), the main wing rib (12) and the rear main spar (16) are made of high-temperature resistant titanium alloy materials; The antenna is installed between the area enclosed by the main wing rib (12), the first wing spar (13), the main wing spar (14), the second wing spar (15), the rear main wing spar (16), the wing rib (17) and the bevel rib (18), or the antenna is installed on the bevel rib (18).

2. The high temperature resistant and wave-transparent wing structure according to claim 1, characterized in that: The resin-based composite components are all prepared by an autoclave method. The matrix of the composite is prepared by bismaleimide resin, high-temperature resistant polyimide or phthalonitrile resin, and the reinforcement is glass fiber.

3. The high temperature resistant and wave-transmitting wing structure according to claim 2, characterized in that: The joint (11), the main wing rib (12), the first wing spar (13), the main wing spar (14), the second wing spar (15), the rear main wing spar (16), the wing rib (17) and the bevel rib (18) are connected by adhesive bonding.

4. A high temperature resistant wave-transmitting wing structure, characterized in that: The high temperature resistant and wave-transmitting wing structure comprises a wing frame (1), a lower skin (2), a wing tip structure (3), an adjustment strap plate (4) and an upper skin (5), wherein the upper skin (5) is arranged on the upper part of the wing frame (1), the lower skin (2) is arranged on the lower part of the wing frame (1), the adjustment strap plate (4) is arranged on one side of the wing frame (1), and the wing tip structure (3) is arranged on the other side of the wing frame (1); The wing frame (1) comprises a joint (11), a main wing rib (12), a first wing spar (13), a main wing spar (14), a second wing spar (15), a rear main wing spar (16), a wing rib (17) and a bevel rib (18), wherein one end of the first wing spar (13), the main wing spar (14), the second wing spar (15) and the rear main wing spar (16) are connected to the main wing rib (12), and the first wing spar (13), the main wing spar (14), the second wing spar (15) and the rear main wing spar (16) are connected to the main wing rib (12), and the first wing spar (13), the main wing spar (14), the second wing spar (15) and the rear main wing spar (16) are connected to the main wing rib (12). The other end of the main spar (16) is connected to the hypotenuse rib (18), one end of the wing rib (17) is connected to the hypotenuse rib (18), and the other end of the wing rib (17) is connected to the rear main spar (16); the joint (11), the first spar (13), the second spar (15), the wing rib (17) and the hypotenuse rib (18) are made of high-temperature resistant resin-based composite materials, and the main spar (14), the main wing rib (12) and the rear main spar (16) are made of high-temperature resistant titanium alloy materials; The upper skin (5) and the lower skin (2) are integrally formed with the antenna and are installed in blocks on the wing frame (1).

5. The high temperature resistant and wave-transmitting wing structure according to claim 4, characterized in that: The resin-based composite components are all prepared by an autoclave method. The matrix of the composite is prepared by bismaleimide resin, high-temperature resistant polyimide or phthalonitrile resin, and the reinforcement is glass fiber.

6. A high temperature resistant wave-transmitting wing structure, characterized in that: The high temperature resistant and wave-transmitting wing structure comprises a wing frame (1), a lower skin (2), a wing tip structure (3), an adjustment strap plate (4) and an upper skin (5), wherein the upper skin (5) is arranged on the upper part of the wing frame (1), the lower skin (2) is arranged on the lower part of the wing frame (1), the adjustment strap plate (4) is arranged on one side of the wing frame (1), and the wing tip structure (3) is arranged on the other side of the wing frame (1); The wing frame (1) comprises a joint (11), a main wing rib (12), a first wing spar (13), a main wing spar (14), a second wing spar (15), a rear main wing spar (16), a wing rib (17) and a bevel rib (18), wherein one end of the first wing spar (13), the main wing spar (14), the second wing spar (15) and the rear main wing spar (16) are connected to the main wing rib (12), and the first wing spar (13), the main wing spar (14), the second wing spar (15) and the rear main wing spar (16) are connected to the main wing rib (12), and the first wing spar (13), the main wing spar (14), the second wing spar (15) and the rear main wing spar (16) are connected to the main wing rib (12). The other end of the main spar (16) is connected to the hypotenuse rib (18), one end of the wing rib (17) is connected to the hypotenuse rib (18), and the other end of the wing rib (17) is connected to the rear main spar (16); the joint (11), the first spar (13), the second spar (15), the wing rib (17) and the hypotenuse rib (18) are made of high-temperature resistant resin-based composite materials, and the main spar (14), the main wing rib (12) and the rear main spar (16) are made of high-temperature resistant titanium alloy materials; The wing tip structure (3) and the antenna are integrally formed into a wing tip antenna integrated structure (31); the wing tip structure (3) comprises a wing tip lap (312), a ceramic panel (314) and an aerogel interlayer (315); the wing tip antenna integrated structure is connected to a wing frame frame (311) via the wing tip lap (312); and the antenna (313) is integrally prepared with the ceramic panel (314) and the aerogel interlayer (315).

7. The high temperature resistant and wave-transmitting wing structure according to claim 6, characterized in that: The ceramic panel (314) may be made of materials such as quartz, silicon oxide, silicon carbide or aluminum oxide. The ceramic panel (314) and the nano-silicon oxide aerogel interlayer (315) are connected and combined via ceramicized high temperature resistant fibers to form a heat-proof and wave-transmitting material.

8. A high temperature resistant wave-transmitting wing structure, characterized in that: The high temperature resistant and wave-transmitting wing structure comprises a wing frame (1), a lower skin (2), a wing tip structure (3), an adjustment strap plate (4) and an upper skin (5), wherein the upper skin (5) is arranged on the upper part of the wing frame (1), the lower skin (2) is arranged on the lower part of the wing frame (1), the adjustment strap plate (4) is arranged on one side of the wing frame (1), and the wing tip structure (3) is arranged on the other side of the wing frame (1); The wing frame (1) comprises a joint (11), a main wing rib (12), a first wing spar (13), a main wing spar (14), a second wing spar (15), a rear main wing spar (16), a wing rib (17) and a bevel rib (18), wherein one end of the first wing spar (13), the main wing spar (14), the second wing spar (15) and the rear main wing spar (16) are connected to the main wing rib (12), and the first wing spar (13), the main wing spar (14), the second wing spar (15) and the rear main wing spar (16) are connected to the main wing rib (12), and the first wing spar (13), the main wing spar (14), the second wing spar (15) and the rear main wing spar (16) are connected to the main wing rib (12). The other end of the main spar (16) is connected to the hypotenuse rib (18), one end of the wing rib (17) is connected to the hypotenuse rib (18), and the other end of the wing rib (17) is connected to the rear main spar (16); the joint (11), the first spar (13), the second spar (15), the wing rib (17) and the hypotenuse rib (18) are made of high-temperature resistant resin-based composite materials, and the main spar (14), the main wing rib (12) and the rear main spar (16) are made of high-temperature resistant titanium alloy materials; The wingtip structure (3) and the antenna are independently prepared to form a wingtip antenna separate structure (32); the wingtip structure (3) comprises a wingtip lap (322), a ceramic panel (324), a honeycomb filler (325) and a polyimide thermal insulation pad (326); the wingtip antenna integrated structure is connected to the wing skeleton frame (321) via the wingtip lap (312); the ceramic panel (324) and the honeycomb filler (325) are prepared in an integrated manner; the antenna (323) is mounted on the wing skeleton frame (321), and the polyimide thermal insulation pad (326) is added between the two to prevent the wing skeleton frame (321) from conducting heat to the antenna (323).

9. The high temperature resistant and wave-transparent wing structure according to claim 8, characterized in that: The material of the honeycomb filler (325) includes glass fiber or fiber foam.

10. An aircraft, characterized in that: The aircraft comprises the high temperature resistant and wave-transparent wing structure according to any one of claims 1 to 9.

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