Aircraft cabin separation covering cap structure

Abstract

The invention relates to an aircraft cabin separation covering cap structure which comprises a separation baffle, a covering cap bearing structure and a separation body, the separation baffle is used for sealing a cabin opening, and one end of the separation baffle is used for being connected with a cabin body; the covering cap bearing structure comprises a connecting part and a separating part, the connecting part is arranged at the other end of the separating baffle, and the separating part is connected to the middle of the connecting part; the separating body is connected with the separating part; wherein the connection part and the separation part are configured as follows: when the separation body is separated, the connection part and the separation baffle are fixed on the cabin body, and the separation part and the separation body are separated from the connection part, so that a cavity is formed in the middle of the separation covering cap structure, one end of the cavity is open, and the other end of the cavity is closed by the separation baffle. Before the aircraft carries out covering cap separation work, the separation covering cap structure and the cabin body are connected into a whole through the separation baffle, gap heat between the separation covering cap structure and the cabin body does not need to be treated, after the separation body is separated, the connecting part and the separation baffle are still fixed to the cabin body, the integrity of the structure of the cabin body is guaranteed, and operation of equipment in the cabin is guaranteed.

Description

Technical Field

[0001] The present application relates to the field of aircraft, and in particular to an aircraft cabin separation cover structure. Background Art

[0002] During the flight of the aircraft, the cabin covers need to be separated as required, such as the reverse thrust engine covers of the rocket booster stage and the covers of the telemetry detection device. After the covers are separated, the aircraft continues to fly, completing flight maneuvers and performing detection functions.

[0003] When separating the hatch cover in a traditional way, explosive bolts are used to connect the hatch cover to the cabin body. The impact load is large, and the buffer device is difficult to design. In addition, this connection method inevitably leads to a gap between the hatch cover and the cabin body, and thermal protection of the gap needs to be considered. In addition, for the hatch cover in a high-temperature environment, after separation, the hot air flow near the hatch cover is easily transferred to the cabin, affecting the use of the equipment in the cabin, and even worse, causing the equipment in the cabin to malfunction. Summary of the invention

[0004] The present application provides an aircraft cabin separation cover structure, which can solve the problem in the related art that after the cover is separated, the hot air flow near the cover is easily transferred to the cabin, affecting the use of equipment in the cabin.

[0005] In the first aspect, the embodiment of the present application provides an aircraft cabin separation cover structure, which includes: a separation baffle, a cover bearing structure and a separation body, wherein the separation baffle is used to close the hatch, and one end is used to connect with the cabin; the cover bearing structure includes a connecting part and a separating part, wherein the connecting part is arranged at the other end of the separation baffle, and the separating part is connected to the middle of the connecting part; the separating body is connected to the separating part; wherein the connecting part and the separating part are configured as follows: when the separating body is separated, the connecting part and the separation baffle are fixed on the cabin, and the separating part and the separating body are separated from the connecting part, so that a cavity is formed in the middle of the separation cover structure, and one end of the cavity is open and the other end is closed by the separation baffle. In the present application, before the aircraft performs the cover separation work, the separation cover structure and the cabin are connected as a whole through the separation baffle, and there is no need to additionally process the gap heat between the separation cover structure and the cabin. After the separation body is separated, the connecting part and the separation baffle are still fixed on the cabin, ensuring the structural integrity of the cabin, being able to withstand aerodynamic force and aerodynamic heat, and ensuring the operation of the equipment in the cabin.

[0006] In one embodiment, when the separation body is not separated, there is a receiving cavity between the separation part and the separation baffle, and a separation cutting device is arranged inside the receiving cavity. When the separation body is separated, the separation cutting device 6 is selected to separate the connection part and the separation part.

[0007] In one embodiment, when the separation body is not separated, an annular groove is formed between the outer peripheral surface of the separation body and the inner wall of the connecting portion, a buffer device is arranged inside the annular groove, and a gap is arranged between the outer peripheral surface of the separation body and the buffer device. The buffer device can be arranged as an elastic body, which can absorb energy and alleviate the impact caused by the separation and cutting device during cutting.

[0008] In one embodiment, the buffer device, the connecting portion and the separating and cutting device are connected via a limiting member.

[0009] In one embodiment, a cutting groove is provided on the cover bearing structure, a portion of the cutting groove is located on the connecting portion, and another portion is located on the separating portion, and the cutting groove is provided on one side of the separating and cutting device. The provision of the cutting groove facilitates cutting by the separating and cutting device and reduces the cutting path.

[0010] In one embodiment, a pressure relief groove is provided on the inner wall surface of the separation body, and the pressure relief groove is located on one side of the cutting groove;

[0011] The width of the cutting groove d = 5 mm to 15 mm, and the depth of the cutting groove h = (0.1 to 0.3) × d;

[0012] The width of the pressure relief groove D = (1.2-1.5) × d, and the depth of the pressure relief groove H = (1-1.5) × h. When the separation and cutting device is cutting, airflow will be generated. If the pressure relief groove is not provided on the wall surface of the separation body, the airflow will enter between the cover bearing structure and the separation body along the cutting gap. Therefore, a pressure relief groove is provided as a guide passage to guide the airflow.

[0013] In one embodiment, the surface of the connection part is provided with a cover heat protection layer, and a through hole is provided in the middle of the cover heat protection layer for the separation body to pass through, so that the cover heat protection layer can protect the connection part from heat before, during and after the separation of the separation body.

[0014] In one embodiment, a gap is provided between the outer peripheral surface of the separator and the heat-proof layer of the cover. When the separator and the separation part are separated, the heat-proof layer of the cover will not interfere with the separator and will not hinder the smooth separation of the separator.

[0015] In one embodiment, a sealing groove is provided on one end of the separation baffle plate connected to the cover bearing structure, and a sealing ring is provided in the sealing groove.

[0016] In one embodiment, the surface of the separation baffle is coated with a heat-resistant coating.

[0017] The beneficial effects brought by the technical solution provided in the embodiments of the present application include:

[0018] An embodiment of the present application provides an aircraft cabin separation cover structure. Before the aircraft performs cover separation, the separation cover structure and the cabin body are connected as one body through a separation baffle, and there is no need to additionally process the gap heat between the separation cover structure and the cabin body. After the separation body is separated, the connecting part and the separation baffle are still fixed to the cabin body, thereby ensuring the structural integrity of the cabin body, being able to withstand aerodynamic force and aerodynamic heat, and ensuring the operation of the equipment in the cabin. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0020] Figure 1 This is a schematic diagram of the overall structure of the separation body provided in the embodiment of the present application before separation;

[0021] Figure 2 This is a schematic diagram of the overall structure after the separation body provided in the embodiment of the present application is separated;

[0022] Figure 3 Schematic diagram of the cover bearing structure, separation and cutting device and separation body structure provided in the embodiment of the present application.

[0023] In the figure: 1. cover bearing structure; 2. cover heat protection layer; 3. separation body; 4. buffer device; 5. screw plug; 6. separation cutting device; 7. first connecting screw; 8. second connecting screw; 9. separation baffle; 10. cutting groove; 11. pressure relief groove; 12. heat protection coating; 13. sealing groove; 14. first sealing ring; 15. second sealing ring. DETAILED DESCRIPTION

[0024] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0025] An embodiment of the present application provides an aircraft cabin separation cover structure, which can solve the problem in the related art that after the cover is separated, the hot air flow near the cover is easily transferred to the cabin, affecting the use of equipment in the cabin.

[0026] During the flight of the aircraft, the cabin covers need to be separated as required, such as the reverse thrust engine covers of the rocket booster stage and the covers of the telemetry detection device. After the covers are separated, the aircraft continues to fly, completing flight maneuvers and performing detection functions.

[0027] When separating the hatch cover in a traditional way, explosive bolts are used to connect the hatch cover to the cabin body. The impact load is large, and the buffer device is difficult to design. In addition, this connection method inevitably leads to a gap between the hatch cover and the cabin body, and thermal protection of the gap needs to be considered. In addition, for the hatch cover in a high-temperature environment, after separation, the hot air flow near the hatch cover is easily transferred to the cabin, affecting the use of the equipment in the cabin, and even worse, causing the equipment in the cabin to malfunction.

[0028] After the cover is separated, the hot air flow near the cover is easily transferred to the cabin, affecting the use of equipment in the cabin. Figures 1 to 3 The embodiment of the present application provides an aircraft cabin separation cover structure, which includes: a separation baffle 9, a cover bearing structure 1 and a separation body 3, wherein the separation baffle 9 is used to close the hatch, and one end of the separation baffle is used to connect with the cabin body; the cover bearing structure 1 includes a connecting portion and a separating portion, the connecting portion is arranged at the other end of the separation baffle 9, and the separating portion is connected to the middle of the connecting portion; the separation body 3 is connected to the separating portion; wherein the connecting portion and the separating portion are configured as follows: when the separation body 3 is separated, the connecting portion and the separation baffle 9 are fixed on the cabin body, and the separating portion and the separation body 3 are separated from the connecting portion, so that a cavity is formed in the middle of the separation cover structure, and one end of the cavity is open, and the other end is closed by the separation baffle 9.

[0029] In the present application, before the aircraft performs the cover separation work, the separation cover structure and the cabin are connected as a whole through the separation baffle 9. The separation cover structure can be disassembled as needed, which is convenient for operating and maintaining the cabin equipment and the separation cover structure. At the same time, there is no need to additionally deal with the gap heat between the separation cover structure and the cabin. The gap heat refers to the phenomenon that the temperature of the area near the gap rises due to the high-temperature airflow entering the gap between the structure or components. This phenomenon is particularly common in the fields of high-speed aircraft, rocket engines, high-temperature industrial equipment, etc., and has an important impact on the thermal protection and safety of the structure. Gap heat can cause local overheating of the structure, thereby affecting the integrity and performance of the structure. If the gap heat is not effectively controlled, it may cause the thermal protection system to fail, thereby posing a threat to the safety of the aircraft. After the separation body 3 is separated, the connecting part and the separation baffle 9 are still fixed on the cabin to ensure the structural integrity of the cabin, be able to withstand aerodynamic force and aerodynamic heat, and ensure the operation of the cabin equipment.

[0030] See also Figure 1As shown, the separation baffle 9 is connected to the cabin body and serves as the base of the separation cover structure. Other components in the separation cover structure are directly or indirectly connected to the separation baffle 9. In this embodiment, the cover bearing structure 1 is directly connected to the separation baffle 9, and the separation body 3 and the cover heat protection layer 2, buffer device 4, and separation cutting device 6 mentioned below are indirectly connected to the separation baffle 9 through the cover bearing structure 1. In addition, the separation baffle 9 has another function: the separation baffle 9 needs to close the hatch and is detachably connected to the cabin body. When the hatch needs to be opened, the separation baffle 9 is removed.

[0031] The cover bearing structure 1 is fixed on the surface of the separation baffle 9. Preferably, the separation baffle 9 and the cover bearing structure 1 are connected by screws. The cover bearing structure 1 and the separation baffle 9 are made of one of aluminum alloy, alloy steel, titanium alloy, carbon fiber reinforced cyanate-based composite material, carbon fiber reinforced epoxy resin-based composite material, and carbon fiber reinforced bismaleimide resin-based composite material. Preferably, the cover bearing structure 1 and the separation baffle 9 are made of aluminum alloy. A quartz fiber reinforced phenolic resin heat-resistant coating 12 or spray coating is coated on the surface of the separation baffle 9. The coating material types include aluminum oxide ceramic coating, zirconium oxide ceramic coating, and yttrium oxide ceramic coating. Preferably, the heat-resistant coating 12 is yttrium oxide ceramic coating, wherein the yttrium oxide ceramic coating has a high melting point (2430°C), high thermal conductivity (the thermal conductivity can reach 27W / (m□K) at 300K), low thermal expansion coefficient, high dielectric constant, good electrical insulation, good transparency, and paramagnetism.

[0032] A sealing groove 13 is provided at one end of the separation baffle 9 connected to the cover bearing structure 1, and a sealing ring is provided in the sealing groove 13. In this embodiment, two axial sealing grooves 13 are provided on the separation baffle 9, a first sealing ring 14 is provided in one sealing groove 13, and a second sealing ring 15 is provided in the other sealing groove 13. For example, a rubber sealing ring is provided in the sealing groove 13 on the outer side of the separation baffle 9, and a quartz fiber sleeve is provided in the sealing groove 13 on the inner side of the separation baffle 9. The quartz fiber sleeve has the following advantages: High temperature resistance: The quartz fiber sleeve can be used for a long time in a high temperature environment of up to 1050°C due to the inherent heat resistance of its raw materials without deformation or damage. Insulation: The quartz fiber sleeve has excellent insulation performance, which can effectively prevent the passage of current and protect equipment such as wires and cables from damage. Thermal insulation: The sleeve material has good thermal insulation performance, which can reduce heat transfer and protect internal equipment from the influence of high temperature environment. Corrosion resistance: Quartz fiber sleeves have excellent corrosion resistance to a variety of chemicals and can remain stable in harsh chemical environments. Chemical stability: In high temperature and corrosive media, quartz fiber sleeves can maintain their chemical stability and will not decompose or produce harmful substances.

[0033] In this embodiment, the cover bearing structure 1 is divided into a connecting portion and a separating portion, and before separation, the connecting portion and the separating portion are integrally formed. The separating portion is connected to the separating body 3 by a first connecting screw 7 .

[0034] On the basis of the above embodiments, in this embodiment, a heat-proof layer 2 for the mouth cover is provided on the surface of the connection part, and the heat-proof layer 2 for the mouth cover is connected as a whole by a screw plug 5, so that the heat-proof layer 2 for the mouth cover can protect the connection part from heat before, during and after the separation of the separation body 3. Preferably, the material of the heat-proof layer 2 for the mouth cover is a quartz fiber reinforced phenolic resin-based composite material, wherein the quartz fiber reinforced phenolic resin-based composite material is composed of quartz fiber and a phenolic resin matrix. Quartz fiber, as a reinforcing phase, has excellent properties such as high strength, high modulus, high temperature resistance and corrosion resistance; phenolic resin, as a matrix phase, has good adhesion, heat resistance and chemical stability. The thickness of the heat-proof layer 2 for the mouth cover is 5 mm to 30 mm. A through hole for the separation body 3 to pass through is provided in the middle of the heat-proof layer 2 for the separation body 3 to pass through. When the separation body 3 is separated, the separation body 3 and the separation part pass through the through hole.

[0035] On the basis of the above-mentioned embodiment, in this embodiment, when the separation body 3 is separated, the separation cutting device 6 is selected to separate the connection part and the separation part. Therefore, in order to accommodate the separation cutting device 6, the middle of the separation baffle 9 is set to be concave, and the middle of the cover bearing structure 1 is set to be concave, so that in the separation cover structure, when the separation body 3 is not separated, there is a accommodating cavity between the separation part and the separation baffle 9, and the accommodating cavity is a closed cavity; when the separation body 3 and the separation part are separated, a cavity is formed in the middle of the separation cover structure, and the cavity is also located at the accommodating cavity, one end of the cavity is closed by the separation baffle 9, and the other end has an opening.

[0036] Furthermore, a separation and cutting device 6 is provided inside the accommodating chamber. When cutting, the separation and cutting device 6 generates high-temperature and high-pressure gas to separate the connecting part and the separating part. When separating, the separating body 3 is separated together with the separating part. Therefore, it is necessary to connect the connecting part and the separation and cutting device 6 through a limiting member. The limiting member is a second connecting screw 8. One end of the second connecting screw 8 passes through the connecting part and the separation and cutting device 6 and is placed inside the accommodating chamber.

[0037] In order to facilitate the cutting by the separation cutting device 6 and reduce the cutting path, a cutting groove 10 is provided on the cover bearing structure 1. The cutting groove 10 is provided on one side of the separation cutting device 6, and a part of the cutting groove 10 is provided on the connecting part and another part is provided on the separation part. In this embodiment, preferably, the width of the cutting groove 10 is set to d=5mm-15mm, and the depth of the cutting groove 10 is set to h=(0.1-0.3)×d.

[0038] On the basis of the above embodiment, in this embodiment, a pressure relief groove 11 is provided on the inner wall surface of the separation body 3, and the pressure relief groove 11 is arranged on one side of the cutting groove 10. The width D of the pressure relief groove 11 is set to (1.2-1.5)×d, and the depth H of the pressure relief groove 11 is set to (1-1.5)×h.

[0039] Specifically, when the separation and cutting device 6 is cutting, airflow will be generated. If the pressure relief groove 11 is not provided on the wall of the separation body 3, the airflow will enter between the cover bearing structure 1 and the separation body 3 along the cutting gap. Therefore, a pressure relief groove 11 is provided as a guide passage to guide the airflow. Therefore, the positions of the cutting groove 10 and the pressure relief groove 11 need to correspond.

[0040] On the basis of the above embodiments, in this embodiment, when the separation body 3 is not separated, an annular groove is formed between the outer peripheral surface of the separation body 3, the inner wall of the cover heat protection layer 2 and the inner wall of the connecting part, and the annular groove is arranged around the separation body 3.

[0041] Since the separation and cutting device 6 generates energy when cutting, and the energy will impact the cover bearing structure 1, a buffer device 4 is provided inside the annular groove. The buffer device 4 can be provided as an elastic body, which can absorb energy and alleviate the impact caused by the separation and cutting device 6 when cutting. In addition, one end of the second connecting screw 8 is also connected to the buffer device 4, so as to connect the buffer device 4, the separation and cutting device 6 and the connecting part in the cover bearing structure 1 as a whole.

[0042] Furthermore, since the separation body 3 needs to be separated, in order to make the separation process smoother, a gap is provided between the outer peripheral surface of the separation body 3 and the buffer device 4, and a gap is provided between the outer peripheral surface of the separation body 3 and the mouth cover heat protection layer 2, and the gap size L=0.1mm~5mm. Therefore, when the separation body 3 and the separation part are separated, the buffer device 4 and the mouth cover heat protection layer 2 will not interfere with the separation body 3, and will not hinder the smooth separation of the separation body 3.

[0043] In summary, in the present application, before the aircraft performs cover separation work, the separation cover structure is connected to the cabin section as a whole, and there is no need to additionally deal with the heat in the gap between the separation cover structure and the cabin body; after the separation body 3 is separated, the separation cover structure part is retained on the cabin body, and still has the functions of heat insulation, waterproofing, and load-bearing; the buffer device 4 on the separation cover structure can absorb the impact load energy generated during separation to ensure the normal operation of the equipment in the cabin; the separation cover structure has a detachable function, which is easy to operate and convenient for the maintenance of equipment such as equipment in the cabin.

[0044] In the description of the present application, it should be noted that the terms "upper", "lower", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application. Unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances.

[0045] It should be noted that, in this application, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0046] The above description is only a specific implementation of the present application, so that those skilled in the art can understand or implement the present application. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to the embodiments shown herein, but will conform to the widest range consistent with the principles and novel features applied for herein.

Claims

1. An aircraft cabin separation cover structure, characterized in that: It includes: A separation baffle (9), the separation baffle (9) being used to close the hatch and having one end connected to the cabin body; A mouth cover bearing structure (1), the mouth cover bearing structure (1) comprising a connecting portion and a separating portion, the connecting portion being arranged at the other end of the separating baffle (9), and the separating portion being connected to the middle of the connecting portion; A separation body (3), wherein the separation body (3) is connected to the separation portion; The connection part and the separation part are configured as follows: when the separation body (3) is separated, the connection part and the separation baffle (9) are fixed on the cabin body, and the separation part and the separation body (3) are separated from the connection part, so that a cavity is formed in the middle of the separation cover structure, one end of the cavity is open, and the other end is closed by the separation baffle (9).

2. The aircraft cabin separation cover structure according to claim 1, characterized in that: When the separation body (3) is not separated, there is a receiving cavity between the separation portion and the separation baffle (9), and a separation cutting device (6) is arranged inside the receiving cavity.

3. The aircraft cabin separation cover structure according to claim 2, characterized in that: When the separation body (3) is not separated, an annular groove is formed between the outer peripheral surface of the separation body (3) and the inner wall of the connecting portion, a buffer device (4) is arranged inside the annular groove, and a gap is arranged between the outer peripheral surface of the separation body (3) and the buffer device (4).

4. The aircraft cabin separation cover structure according to claim 3, characterized in that: The buffer device (4), the connecting portion and the separation and cutting device (6) are connected via a limiting member.

5. The aircraft cabin separation cover structure according to claim 2, characterized in that: The cover bearing structure (1) is provided with a cutting groove (10), a part of the cutting groove (10) is located on the connecting part and another part is located on the separating part, and the cutting groove (10) is arranged on one side of the separating and cutting device (6).

6. The aircraft cabin separation cover structure according to claim 5, characterized in that: A pressure relief groove (11) is provided on the inner wall surface of the separation body (3), and the pressure relief groove (11) is located on one side of the cutting groove (10); The width d of the cutting groove (10) is 5 mm to 15 mm, and the depth h of the cutting groove (10) is (0.1 to 0.3)×d; The width D of the pressure relief groove (11) is (1.2-1.5)×d, and the depth H of the pressure relief groove (11) is (1-1.5)×h.

7. The aircraft cabin separation cover structure according to claim 1, characterized in that: The surface of the connection portion is provided with a cover heat protection layer (2), and a through hole for the separation body (3) to pass through is opened in the middle of the cover heat protection layer (2).

8. The aircraft cabin separation cover structure according to claim 7, characterized in that: A gap is provided between the outer peripheral surface of the separation body (3) and the heat-proof layer (2) of the mouth cover.

9. The aircraft cabin separation cover structure according to claim 1, characterized in that: A sealing groove (13) is provided on one end of the separation baffle (9) connected to the cover bearing structure (1), and a sealing ring is provided in the sealing groove (13).

10. The aircraft cabin separation cover structure according to claim 1, characterized in that: The surface of the separation baffle (9) is coated with a heat-resistant coating (12).

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