Ablation-resistant and high-temperature-resistant composite material protective cover

Abstract

This invention provides an ablation-resistant and high-temperature-resistant composite material protective shield for aircraft in the field of aerodynamic thermal protection technology. The shield includes an ablation-resistant end, an ablation-resistant heat-insulating coating, a fixing and separation mechanism, and a load-bearing structure. The ablation-resistant end, the ablation-resistant heat-insulating coating, the fixing and separation mechanism, and the load-bearing structure are all fixedly mounted on the protective shield. By using a load-bearing structure made of carbon fiber reinforced resin-based composite material, the weight of the protective shield is significantly reduced under the same mechanical structural requirements, thus reducing the negative weight of the aircraft structure. The ablation-resistant end, made of quartz fiber reinforced resin-based composite material, is located at the front end of the protective shield and can withstand the erosion of high-temperature hot airflow. The lightweight, silicone-based ablation-resistant heat-insulating coating exhibits good toughness under ablation and erosion-resistant conditions, enabling it to withstand short-term, high-temperature hot airflow erosion.

Description

Technical Field

[0001] This invention relates to the field of aerodynamic thermal protection technology for aircraft, specifically to a composite material protective cover that is resistant to ablation and high temperature. Background Technology

[0002] Aircraft fly in the atmosphere, and protective shields are used to protect them from harmful environmental factors such as aerodynamics, aerothermal activity, and acoustic resonance, and to maintain the streamlined aerodynamic shape of the aircraft. They are an important component of aircraft. Protective shields need to withstand the loads of transportation, launch, and flight, and must meet certain structural and thermal performance requirements. In addition, protective shields must be reliably fixed to the aircraft, not affect the normal operation of the aircraft, and be able to separate from the aircraft quickly. At present, protective shields for such aircraft, both domestically and internationally, are mostly made of metal materials such as titanium alloys and aluminum alloys, but they have the following disadvantages: (1) The metal shield has a large mass, which increases the negative weight of the aircraft structure; (2) The heavy metal shield increases the difficulty of separation of the fixed separation mechanism, such as the large number of fixed points and the large separation energy; (3) The high thermal conductivity of metal materials makes heat insulation treatment complicated; (4) The poor environmental resistance of metal materials results in a short service life; (5) The shape of the shield is mostly a complex curved surface, which makes processing difficult and manufacturing costs high.

[0003] This invention overcomes the shortcomings of metal protective shields. The main structure is made of high-temperature resistant carbon fiber reinforced resin composite material, which has high specific strength and specific modulus, and can withstand temperatures up to 200℃. Under the same structural performance conditions, the composite material protective shield is 60% lighter than the titanium alloy protective shield. The front end of the shield is made of quartz reinforced resin composite material, which can withstand the impact of high-temperature hot airflow. The outer layer uses a silicon-based heat-insulating coating, ensuring the main structure's short-term ablation resistance and high-temperature resistance requirements. Based on these reasons, the ablation-resistant and high-temperature resistant composite material protective shield has a good aerodynamic shape, can withstand the impact of high-temperature hot airflow, is lightweight and high-strength, and has better corrosion resistance and environmental resistance than metal materials. The development of ablation-resistant and high-temperature resistant composite material protective shields will become a new direction for aircraft aerodynamic thermal protection technology. Therefore, this invention is simple in design but highly practical, solves the above problems, and has better practical application results. Summary of the Invention

[0004] In view of the deficiencies in the prior art, the purpose of this invention is to provide a composite material protective cover that is resistant to ablation and high temperature.

[0005] The present invention provides a composite material protective cover that is resistant to ablation and high temperature, comprising an ablation-resistant end, an ablation-resistant heat insulation coating, a fixing and separation mechanism, and a load-bearing structure;

[0006] The ablation-resistant end is fixedly mounted on the protective cover, the ablation-resistant heat insulation coating is fixedly mounted on the protective cover, the fixing and separation mechanism is fixedly mounted on the protective cover, and the load-bearing structure is fixedly mounted on the protective cover.

[0007] In some embodiments, the ablation-resistant end is fixedly disposed at the front end of the protective cover.

[0008] In some embodiments, the ablation-resistant end comprises an ablation-resistant end of a quartz fiber reinforced resin matrix composite material, and the high-temperature tensile strength of the ablation-resistant end is not less than 60 MPa.

[0009] In some embodiments, the ablation-resistant heat-insulating coating is applied to the inner and outer surfaces of the protective cover.

[0010] In some embodiments, the ablation-resistant heat insulation coating comprises a silicone-based lightweight ablation-resistant heat insulation coating, and the tensile strength of the ablation-resistant heat insulation coating is not less than 2 MPa.

[0011] In some embodiments, the fixing and separation mechanism is glued inside the protective cover, and the fixing and separation mechanism is connected to the aircraft.

[0012] In some embodiments, the fixing separation mechanism includes an upper base and a lower base, which are embedded inside the support structure via the upper base and the lower base.

[0013] In some embodiments, one end of the load-bearing structure is connected to the ablation-resistant end.

[0014] In some embodiments, the load-bearing structure includes a load-bearing structure of carbon fiber reinforced resin matrix composite material, and the heat resistance of the load-bearing structure is not less than 200°C, and the high-temperature tensile strength of the load-bearing structure is greater than 300 MPa.

[0015] Compared with the prior art, the present invention has the following beneficial effects:

[0016] 1. This invention, by setting up a load-bearing structure, which is made of carbon fiber reinforced resin matrix composite material, ensures the structural load-bearing performance of the protective cover under storage, transportation, and separation conditions. The density of carbon fiber reinforced resin matrix composite material is 1 / 3 to 1 / 2 of that of traditional metal materials. Under the same mechanical structural requirements, the mass of the protective cover is significantly reduced, which can reduce the negative weight of the aircraft structure. Moreover, the molding process is simple and convenient, and the cost is low.

[0017] 2. This invention features an ablation-resistant end located at the front of the protective cover. The ablation-resistant end is a localized area subjected to high-temperature ablation and erosion. The ablation-resistant end is made of quartz fiber reinforced resin matrix composite material, which can withstand the erosion of high-temperature hot airflow; it has good environmental resistance and a long service life.

[0018] 3. This invention provides an anti-ablation heat insulation coating. The anti-ablation heat insulation coating is a silicone-based lightweight heat insulation coating that meets the heat insulation requirements of non-load-bearing high-temperature environments and low decomposition. The anti-ablation heat insulation coating has good toughness in ablation-resistant and erosion-resistant environments and can withstand short-term, high-heat airflow erosion. In addition, it has good spray adhesion performance and can adapt to the requirements of aerodynamic thermal environment. Attached Figure Description

[0019] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0020] Figure 1 This is a schematic diagram of the structure of the composite material protective cover that is resistant to ablation and high temperature according to the present invention.

[0021] Figure label:

[0022] Detailed Implementation

[0023] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0024] like Figure 1 The diagram shows the structure of the ablation-resistant and high-temperature-resistant composite material protective cover of the present invention. It includes an ablation-resistant end 11, an ablation-resistant heat-insulating coating 12, a fixing and separation mechanism 13, and a supporting structure 14. The ablation-resistant end 11 is fixedly mounted on the protective cover 1, the ablation-resistant heat-insulating coating 12 is fixedly mounted on the protective cover 1, the fixing and separation mechanism 13 is fixedly mounted on the protective cover 1, and the supporting structure 14 is fixedly mounted on the protective cover 1. The protective cover 1 can resist the erosion of high-temperature hot air and ensures smooth separation of the cover from the aircraft.

[0025] An ablation-resistant end 11 is fixedly installed at the front end of the protective cover 1. The ablation-resistant end 11 is a localized high-temperature ablation and erosion area, capable of withstanding the erosion of high-temperature hot airflow. The ablation-resistant end 11 comprises an ablation-resistant end made of quartz fiber reinforced resin-based composite material, and its high-temperature tensile strength is not less than 60 MPa. An ablation-resistant heat-insulating coating 12 is applied to the inner and outer surfaces of the protective cover 1. The ablation-resistant heat-insulating coating 12 meets the heat insulation requirements of non-load-bearing high-temperature environments and low decomposition. Under ablation-resistant and erosion-resistant conditions, it exhibits good toughness and can withstand short-term, high-temperature airflow erosion. The ablation-resistant heat-insulating coating 12 comprises a silicone-based lightweight ablation-resistant heat-insulating coating, and its tensile strength is not less than 2 MPa.

[0026] The fixed separation mechanism 13 is glued inside the protective cover 1 and connected to the aircraft, enabling effective separation. The fixed separation mechanism 13 is made of metal. It includes an upper base 131 and a lower base 132, which are embedded within the support structure 14. One end of the support structure 14 is connected to an ablation-resistant end cap 11. The support structure 14 is the main load-bearing structure of the protective cover 1, ensuring its structural load-bearing performance during storage, transportation, and separation. The support structure 14 is made of carbon fiber reinforced resin matrix composite material, with a heat resistance of not less than 200℃ and a high-temperature tensile strength greater than 300 MPa.

[0027] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0028] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A composite material protective cover that is resistant to ablation and high temperature, characterized in that, It includes an ablation-resistant end (11), an ablation-resistant heat insulation coating (12), a fixed separation mechanism (13), and a load-bearing structure (14). The ablation-resistant end (11) is fixedly installed on the protective cover (1), the ablation-resistant heat insulation coating (12) is fixedly installed on the protective cover (1), the fixed separation mechanism (13) is fixedly installed on the protective cover (1), and the bearing structure (14) is fixedly installed on the protective cover (1). The ablation-resistant heat insulation coating (12) is applied to the inner and outer surfaces of the protective cover (1); The ablation-resistant heat insulation coating (12) includes a silicone-based lightweight ablation-resistant heat insulation coating, and the tensile strength of the ablation-resistant heat insulation coating (12) is not less than 2 MPa; The fixed separation mechanism (13) includes an upper base (131) and a lower base (132), and the fixed separation mechanism (13) is embedded in the bearing structure (14) through the upper base (131) and the lower base (132).

2. The ablation-resistant and high-temperature-resistant composite material protective cover according to claim 1, characterized in that, The ablation-resistant end (11) is fixedly installed at the front end of the protective cover (1).

3. The ablation-resistant and high-temperature-resistant composite material protective cover according to claim 2, characterized in that, The ablation-resistant end (11) includes an ablation-resistant end made of quartz fiber reinforced resin matrix composite material, and the high-temperature tensile strength of the ablation-resistant end (11) is not less than 60 MPa.

4. The ablation-resistant and high-temperature-resistant composite material protective cover according to claim 1, characterized in that, The fixed separation mechanism (13) is glued inside the protective cover (1) and is connected to the aircraft.

5. The ablation-resistant and high-temperature-resistant composite material protective cover according to claim 1, characterized in that, One end of the load-bearing structure (14) is connected to the ablation-resistant end (11).

6. The ablation-resistant and high-temperature-resistant composite material protective cover according to claim 5, characterized in that, The load-bearing structure (14) includes a load-bearing structure of carbon fiber reinforced resin matrix composite material, and the heat resistance of the load-bearing structure (14) is not less than 200℃, and the high temperature tensile strength of the load-bearing structure (14) is greater than 300MPa.

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