Thermal insulation sealing structure for butt joint of ceramic matrix composite control surface and cabin

Abstract

The invention discloses a thermal insulation sealing structure for butt joint of a ceramic matrix composite control surface and a cabin body, which comprises a composite material and the cabin body, and the composite material control surface of the composite material is in butt joint connection with the cabin body butt joint surface of the cabin body; a heat insulation sealing layer is arranged between the composite control face and the cabin butt joint face, has elasticity and is in a compressed state. Under the condition that the composite material control surface deforms, a tiny gap generated between the composite material control surface and the cabin butt joint surface is filled through resilience of the heat insulation sealing layer, dynamic sealing of connection of the control surface and the cabin structure is achieved, and the hidden danger of damage caused by thermal deformation of an oversized component is eliminated.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a heat-insulating sealing structure for docking a ceramic-based composite material control surface with a cabin. Background Art

[0002] With the continuous advancement of aerospace technology, the performance requirements for aircraft are increasing. As an important part of the aircraft control system, the docking of control surfaces with the cabin will directly affect the performance and safety of the aircraft.

[0003] Aircrafts fly at high Mach numbers for a long time in the atmosphere and need to withstand extreme aerodynamic thermal environments. The use of traditional metal materials can no longer meet the performance requirements of lightweight structure and adaptability to high thermal environments at the same time. Ceramic-based composites have similar toughness and reliability to metals, better mechanical properties and anti-oxidation properties, and are currently the fastest-growing and most widely used new materials in the field of thermal protection. Therefore, continuous fiber-reinforced ceramic-based composites are used to replace metal materials. At the same time, for ultra-long chord control surface components, they are prone to thermal deformation in extreme aerodynamic thermal environments, resulting in tiny gaps between the control surface and the cabin of the aircraft. Under the action of high-speed airflow, these gaps may cause local overheating and generate large gap heat, leaving hidden dangers of damage. Therefore, in order to make the aircraft composite control surface and the cabin tightly connected, it is necessary to design the connection surface with thermal insulation and sealing integration to avoid the safety hazards caused by gap heat. Summary of the invention

[0004] In view of the above problems in the prior art, the present invention provides a thermal insulation sealing structure for the connection between a ceramic-based composite control surface and a cabin, which solves the problem that tiny gaps are generated between the control surface and the cabin connection surface of existing aircraft in extreme environments, leaving hidden dangers of damage.

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

[0006] Provided is a thermal insulation sealing structure for docking a ceramic-based composite material control surface with a cabin body, comprising a composite material and a cabin body, wherein a composite material control surface of the composite material is butt-connected with a cabin body docking surface of the cabin body; a thermal insulation sealing layer is arranged between the composite material control surface and the cabin body docking surface, and the thermal insulation sealing layer is elastic and in a compressed state.

[0007] In the present invention, when the composite control surface is deformed, the micro gap between the composite control surface and the docking surface of the cabin body is filled by the rebound of the heat insulating sealing layer, thereby realizing dynamic sealing of the connection between the control surface and the cabin body structure and eliminating the hidden danger of damage to the super-large component due to thermal deformation.

[0008] Furthermore, a plurality of connecting shafts are evenly arranged on the composite material control surface, and the connecting shafts are made of the same material as the composite material; and a zero position block is sleeved on the connecting shaft.

[0009] Furthermore, positioning holes that match the position and number of the connecting shafts are opened on the heat-insulating sealing layer, and the connecting shafts pass through the positioning holes and fall into the mounting holes reserved on the docking surface of the cabin, and the zero-position blocks are embedded in the positioning holes.

[0010] Furthermore, the thickness H1 of the zero block is greater than the deformation amount Δx of the composite control surface, and the thickness H1 of the zero block is greater than the rebound amount Δh of the thermal insulation sealing layer.

[0011] Furthermore, the compression amount ΔH of the heat-insulating sealing layer is greater than the rebound amount Δh of the heat-insulating sealing layer;

[0012] The compression amount of the heat-insulating sealing layer ΔH=H2-H3, H2 is the thickness of the heat-insulating sealing layer in a free state, and H3 is the thickness of the heat-insulating sealing layer in a compressed state.

[0013] Furthermore, the heat insulating sealing layer is made of flexible material.

[0014] Furthermore, the thermal insulation sealing layer includes a thermal insulation felt, the thermal insulation felt includes aerogel, and the aerogel is wrapped with a thermal insulation cloth.

[0015] The present invention discloses a heat-insulating sealing structure for butting a ceramic-based composite control surface with a cabin, which has the following beneficial effects:

[0016] 1. The present invention provides a heat-insulating sealing layer on the interface between the composite control surface of the composite material and the cabin body, so that when the composite control surface is deformed, the heat-insulating sealing layer can rebound to fill the tiny gap between the composite control surface and the cabin body interface, thereby achieving dynamic sealing of the connection between the control surface and the cabin body structure, blocking the generation of gap heat, and eliminating the hidden danger of damage to super-large components due to thermal deformation.

[0017] 2. The connection shaft and the zero position block in the present invention can cooperate to position the heat insulating sealing layer, so that the heat insulating sealing layer blocks the generation of gap heat, eliminating the hidden danger of damage to super-large components due to thermal deformation. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 The present invention is a schematic structural diagram of a heat-insulating sealing structure for docking a ceramic-based composite material control surface with a cabin.

[0019] Figure 2 The exploded structure schematic diagram of a heat-insulating sealing structure for docking a ceramic-based composite control surface with a cabin body according to the present invention.

[0020] Figure 3 It is a schematic diagram of the structure of the composite material of the present invention.

[0021] Figure 4 For the present invention Figure 3 Schematic diagram of the structure viewed from above.

[0022] Figure 5 It is a schematic diagram of the explosion structure before docking of the present invention.

[0023] Figure 6 It is a schematic diagram of the explosion structure during docking of the present invention.

[0024] Figure 7 It is a schematic diagram of the structure after docking of the present invention.

[0025] Among them, 1. composite material; 2. cabin; 3. composite control surface; 4. cabin docking surface; 5. thermal insulation sealing layer; 6. connecting shaft; 7. zero position block; 8. positioning hole. DETAILED DESCRIPTION

[0026] The specific embodiments of the present invention are described to facilitate those skilled in the art to understand the present invention. However, it should be clear that the present invention is not limited to the scope of the specific embodiments. For those of ordinary skill in the art, as long as various changes are within the spirit and scope of the present invention as defined and determined by the attached claims, these changes are obvious, and all inventions and creations utilizing the concept of the present invention are protected.

[0027] refer to Figure 1-Figure 7 , which is a structural schematic diagram of a thermal insulation sealing structure for docking a ceramic-based composite control surface with a cabin body in this embodiment. Its purpose is to solve the problem that in existing aircraft, tiny gaps are generated between the control surface and the cabin body docking surface under extreme environments, leaving hidden dangers of damage. The specific structure in this embodiment will be explained in detail below.

[0028] A heat-insulating sealing structure for butting a ceramic-based composite control surface with a cabin, comprising a composite material 1 and a cabin 2, wherein a composite control surface 3 of the composite material 1 is butt-connected with a cabin butt surface 4 of the cabin 2;

[0029] A heat-insulating sealing layer 5 is provided between the composite control surface 3 and the cabin docking surface 4. The heat-insulating sealing layer 5 is elastic and in a compressed state.

[0030] In this embodiment, the composite material 1 is an ultra-large chord length control surface component made of ceramic-based composite materials. A thermal insulation sealing layer 5 is provided between the composite control surface 3 of the composite material 1 and the cabin docking surface 4 of the cabin 2. When the composite material 1 and the cabin 2 are docked, the thermal insulation sealing layer 5 is in a compressed state due to the extrusion force applied by the composite control surface 3 to the cabin docking surface 4 along the span direction. In the long-term high Mach number flight environment, the composite material 1 is prone to certain thermal deformation due to extreme aerodynamic heat. At this time, the extrusion force applied by the composite control surface 3 along the span direction to the thermal insulation sealing layer 5 is reduced, and the thermal insulation sealing layer 5 will actively rebound to fill the fine gap between the composite control surface 3 and the cabin docking surface 4, so as to realize dynamic sealing between the composite control surface 3 and the cabin docking surface 4, block the generation of gap heat, eliminate the hidden danger of damage to the ultra-large component due to thermal deformation, and thus can improve the heat protection margin to 2000°C working condition.

[0031] Specifically, a plurality of connecting shafts 6 are evenly arranged on the composite material control surface 3 , and the connecting shafts 6 are made of the same material as the composite material 1 ; and a zero position block 7 is sleeved on the connecting shafts 6 .

[0032] The heat-insulating sealing layer 5 is provided with positioning holes 8 that match the position and number of the connecting shaft 6 . The connecting shaft 6 passes through the positioning holes 8 and falls into the mounting holes reserved on the cabin docking surface 4 , and the zero block 7 is embedded in the positioning holes 8 .

[0033] The thickness H1 of the zero block 7 is greater than the deformation amount Δx of the composite control surface 3 , and the thickness H1 of the zero block 7 is greater than the rebound amount Δh of the heat insulation sealing layer 5 .

[0034] In this embodiment, the connecting shaft 6 is made of the same material as the composite material 1, and the zero block 7 is sleeved on the connecting shaft 6. At the same time, the zero block 7 is fixed to the composite control surface 3 by a composite pin, so that the upper surface of the zero block 7 is kept flush with the composite control surface 3, and the lower surface of the zero block 7 is larger than the area of ​​the reserved mounting hole on the cabin docking surface 4, and the lower surface of the zero block 7 is flush with the cabin docking surface 4.

[0035] When docking the composite material 1 and the cabin hull 2, the positioning hole 8 on the thermal insulation sealing layer 5 is passed through the connecting shaft 6 and sleeved on the zeroing block 7, and the thickness H1 of the zeroing block 7 is greater than the deformation Δx of the composite control surface 3, and the thickness H1 of the zeroing block 7 is greater than the rebound amount Δh of the thermal insulation sealing layer 5. At this time, the zeroing block 7 plays a bearing role, ensuring that the thermal insulation sealing layer 5 can effectively rebound and fill the tiny gap between the composite control surface 3 and the cabin hull docking surface 4, and the zeroing block 7 and the connecting shaft 6 cooperate to position the thermal insulation sealing layer 5.

[0036] Specifically, the compression amount ΔH of the heat-insulating sealing layer 5 is greater than the rebound amount Δh of the heat-insulating sealing layer 5;

[0037] The compression amount of the heat-insulating sealing layer 5 is ΔH=H2-H3, H2 is the thickness of the heat-insulating sealing layer 5 in a free state, and H3 is the thickness of the heat-insulating sealing layer 5 in a compressed state.

[0038] In this embodiment, when the composite material 1 and the cabin body 2 are docked, the composite control surface 3 and the cabin body docking surface 4 squeeze the thermal insulation sealing layer 5. At this time, the thermal insulation sealing layer 5 is in a compressed state, and the thickness of the thermal insulation sealing layer 5 in the compressed state is H3. The compression amount ΔH=H2-H3, H2 is the thickness of the thermal insulation sealing layer 5 in the free state, and the compression amount ΔH of the thermal insulation sealing layer 5 is greater than the rebound amount Δh of the thermal insulation sealing layer 5, which can ensure that the thermal insulation sealing layer 5 can be effectively rebounded. After rebounding, the fine gap between the composite control surface 3 and the cabin body docking surface 4 can be filled, so as to realize dynamic sealing between the composite control surface 3 and the cabin body docking surface 4, block the generation of gap heat, and eliminate the hidden danger of damage to super-large components due to thermal deformation problems.

[0039] Specifically, the heat insulating sealing layer 5 is a flexible material and includes a heat insulating felt, which includes aerogel, and the aerogel is wrapped with a heat insulating cloth.

[0040] In this embodiment, a flexible material is used as the heat insulating sealing layer 5, and it has elasticity, so that when the composite control surface 3 of the composite material 1 is thermally deformed, it can rebound based on the elasticity of the material itself, fill the fine gap between the composite control surface 3 and the cabin docking surface 4, and realize dynamic sealing between the composite control surface 3 and the cabin docking surface 4, blocking the generation of gap heat, and eliminating the potential damage to the super-large component due to thermal deformation.

[0041] Preferably, the aerogel may be alumina aerogel, and the thermal insulation cloth may be quartz fiber cloth. The alumina aerogel is wrapped layer by layer with quartz fiber cloth to form thermal insulation felt as the thermal insulation sealing layer 5 .

[0042] Although the specific implementation of the invention is described in detail in conjunction with the drawings, it should not be understood as limiting the scope of protection of this patent. Within the scope described in the claims, various modifications and variations that can be made by those skilled in the art without creative work still fall within the scope of protection of this patent.

Claims

1. A thermal insulation sealing structure for connecting a ceramic matrix composite control surface with a cabin, characterized in that: It comprises a composite material (1) and a cabin (2), wherein a composite control surface (3) of the composite material (1) is butt-jointed with a cabin butt joint surface (4) of the cabin (2); A heat-insulating sealing layer (5) is provided between the composite material control surface (3) and the cabin body docking surface (4); the heat-insulating sealing layer (5) is elastic and in a compressed state.

2. The heat-insulating sealing structure for connecting a ceramic-based composite control surface with a cabin according to claim 1, characterized in that: A plurality of connecting shafts (6) are evenly arranged on the composite material control surface (3); the connecting shafts (6) are made of the same material as the composite material (1); and a zero position block (7) is sleeved on the connecting shaft (6).

3. The heat-insulating sealing structure for connecting a ceramic-based composite control surface with a cabin according to claim 2, characterized in that: The heat-insulating sealing layer (5) is provided with positioning holes (8) that match the position and number of the connecting shaft (6); the connecting shaft (6) passes through the positioning holes (8) and falls into the mounting holes reserved on the cabin docking surface (4); and the zero-position block (7) is embedded in the positioning holes (8).

4. The heat-insulating sealing structure for connecting a ceramic-based composite control surface with a cabin according to claim 3, characterized in that: The thickness H1 of the zero position block (7) is greater than the deformation amount Δx of the composite material control surface (3), and the thickness H1 of the zero position block (7) is greater than the rebound amount Δh of the thermal insulation sealing layer (5).

5. The heat-insulating sealing structure for connecting a ceramic-based composite control surface with a cabin according to claim 4, characterized in that: The compression amount ΔH of the heat-insulating sealing layer (5) is greater than the rebound amount Δh of the heat-insulating sealing layer (5); The compression amount of the heat insulating sealing layer (5) is ΔH=H2-H3, where H2 is the thickness of the heat insulating sealing layer (5) in a free state, and H3 is the thickness of the heat insulating sealing layer (5) in a compressed state.

6. The heat-insulating sealing structure for connecting a ceramic-based composite control surface with a cabin according to any one of claims 1 to 5, characterized in that: The heat-insulating sealing layer (5) is made of flexible material.

7. The heat-insulating sealing structure for butting a ceramic-based composite control surface with a cabin according to claim 6 The structure is characterized by: The heat-insulating sealing layer (5) comprises a heat-insulating felt, and the heat-insulating felt comprises aerogel, The aerogel is wrapped with heat-insulating cloth.

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