Carrier rocket tail section thermal protection structure and carrier rocket tail section

Abstract

The utility model discloses a thermal protection structure for a tail section of a carrier rocket and the tail section of the carrier rocket, which belong to thermal protection structures for tail sections of carrier rockets and comprise an ablation-resistant layer, a rubber-based coating and a metal structure layer, the ablation-resistant layer is used for resisting instantaneous ultrahigh heat flow when the carrier rocket is launched; the rubber-based coating is used for reducing heat conduction and maintaining the temperature of the inner wall of the structure; the metal structure layer is used for maintaining a structure form; the rubber-based coating is fixedly arranged on the surface of the metal structure layer, and the ablation-resistant layer is fixedly arranged on the other surface of the rubber-based coating. The thermal protection structure for the tail section of the carrier rocket has higher high-temperature ablation resistance, lower thermal conductivity and lower density, and ensures that the temperature of the inner wall of the structure is controlled within 120 DEG C in the pre-fire flight process of the carrier rocket.

Description

Technical Field

[0001] The utility model relates to the technical field of thermal protection of a carrier rocket's tail section structure, in particular to a carrier rocket's tail section thermal protection structure and a carrier rocket's tail section. Background Art

[0002] The thermal protection scheme is an important component of the launch vehicle before launch. It can ensure that the inner wall of the structure is at normal temperature conditions under complex thermal environment conditions, thereby ensuring that the mechanical properties of the structure do not decay at high temperatures and the equipment works normally at normal temperatures.

[0003] In daily practice, the inventors found that the existing technical solutions have the following problems:

[0004] Traditional launch vehicle thermal protection solutions mainly adopt the form of installing cork on the outside of the structure, spraying coatings, etc. This thermal protection solution is suitable for low heat flux and poor ablation conditions. The radiation jet environment of the bundled launch vehicle pre-fire engine is characterized by high heat flux and severe ablation. When facing the radiation jet environment of the bundled launch vehicle pre-fire engine, the traditional launch vehicle thermal protection solution is difficult to ensure the structural temperature, or the thickness of the thermal protection solution is too large, resulting in the problem of overweight of the thermal protection solution, which cannot meet the design requirements of the launch vehicle pre-fire.

[0005] In view of this, it is necessary to provide a new technical solution to solve the above problems. Utility Model Content

[0006] In order to solve the above technical problems, the present application provides a thermal protection structure for the tail section of a launch vehicle, which can achieve thermal protection under low weight conditions and ensure the structural temperature.

[0007] A thermal protection structure for the tail section of a carrier rocket comprises: an ablation-resistant layer, a rubber-based coating and a metal structural layer; the ablation-resistant layer is used to resist the instantaneous ultra-high heat flux during the launch of the carrier rocket; the rubber-based coating is used to reduce heat conduction and maintain the temperature of the inner wall of the structure; the metal structural layer is used to maintain the structural form; the metal structural layer, the rubber-based coating and the ablation-resistant layer are arranged in sequence; the rubber-based coating is fixedly arranged on the surface of the metal structural layer, and the ablation-resistant layer is fixedly arranged on the other surface of the rubber-based coating.

[0008] Preferably, the ablation-resistant layer has a withstand temperature of 1500°C, a density of 800kg / m3, a thermal conductivity of 0.35W / (m·K), and a specific heat capacity of 1500J / (kg·K).

[0009] Preferably, the ablation-resistant layer has a thickness of 2 mm.

[0010] Preferably, the rubber-based coating has a temperature resistance of 800°C, a density of 650kg / m3, a thermal conductivity of 0.13W / (m·K), and a specific heat capacity of 1300J / (kg·K).

[0011] Preferably, the thickness of the rubber-based coating is 6 mm.

[0012] Preferably, the density of the metal structural layer is 2700 kg / m3, the thermal conductivity is 153 W / (m·K), and the specific heat capacity is 960 J / (kg·K).

[0013] Preferably, the thickness of the metal structure layer is 6 mm.

[0014] Preferably, the metal structural layer is an aluminum alloy structural layer.

[0015] A carrier rocket tail section comprises the carrier rocket tail section thermal protection structure.

[0016] Compared with the prior art, this application has at least the following beneficial effects:

[0017] The thermal protection structure of the tail section of a launch vehicle of the utility model has high resistance to high-temperature ablation, low thermal conductivity and low density, so that the net weight increase of the thermal protection structure accounts for 5% of the total weight of the tail section structure. At the same time, it ensures that the temperature of the inner wall of the structure is controlled within 120°C during the flight before the launch. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Hereinafter, some specific embodiments of the present invention will be described in detail in an exemplary and non-restrictive manner with reference to the accompanying drawings. The same reference numerals in the accompanying drawings indicate the same or similar components or parts. It should be understood by those skilled in the art that these drawings are not necessarily drawn to scale.

[0019] In the attached figure:

[0020] Figure 1 The utility model is a schematic structural diagram of the thermal protection structure of the tail section of a launch vehicle.

[0021] The above drawings include the following reference numerals:

[0022] 100, ablation-resistant layer; 200, rubber-based coating; 300, metal structural layer. DETAILED DESCRIPTION

[0023] In order to make the purpose, technical solution and advantages of the present application clearer, the technical solution of the present application will be clearly and completely described below in combination with the specific embodiments of the present application and the corresponding drawings. 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 making creative work are within the scope of protection of the present application.

[0024] like Figure 1 As shown, a thermal protection structure of the tail section of a carrier rocket includes: an ablation-resistant layer 100, a rubber-based coating 200 and a metal structure layer 300; the ablation-resistant layer 100 is used to resist the instantaneous ultra-high heat flux during the launch of the carrier rocket; the rubber-based coating 200 is used to reduce heat conduction and maintain the temperature of the inner wall of the structure; the metal structure layer 300 is used to maintain the structural form; the metal structure layer 300, the rubber-based coating 200 and the ablation-resistant layer 100 are arranged in sequence; the rubber-based coating 200 is fixedly arranged on the surface of the metal structure layer 300, and the ablation-resistant layer 100 is fixedly arranged on the other surface of the rubber-based coating 200.

[0025] Preferably, the ablation-resistant layer 100 has a withstand temperature of 1500° C., a density of 800 kg / m 3 , a thermal conductivity of 0.35 W / (m·K), and a specific heat capacity of 1500 J / (kg·K).

[0026] Preferably, the thickness of the ablation-resistant layer 100 is 2 mm.

[0027] Preferably, the rubber-based coating 200 has a temperature resistance of 800° C., a density of 650 kg / m 3 , a thermal conductivity of 0.13 W / (m·K), and a specific heat capacity of 1300 J / (kg·K).

[0028] Preferably, the thickness of the rubber-based coating 200 is 6 mm.

[0029] Preferably, the metal structure layer 300 has a density of 2700 kg / m3, a thermal conductivity of 153 W / (m·K), and a specific heat capacity of 960 J / (kg·K).

[0030] Preferably, the thickness of the metal structure layer 300 is 6 mm.

[0031] Preferably, the metal structural layer 300 is an aluminum alloy structural layer.

[0032] The jet environment of the strapped-on carrier before-fire engine is characterized by large heat flux, long time, severe ablation, and there are instantaneous ultra-high heat flux and ablation problems caused by engine ignition during flight. Relying on the thermal protection structure of the tail section of the carrier rocket, it can be ensured that during the pre-fire flight process, the temperature of the inner wall of the structure is controlled within 120°C, and the net weight increase of the thermal protection structure accounts for 5% of the total weight of the tail section structure.

[0033] 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.

[0034] 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.

[0035] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein.

[0036] The above description is only the preferred embodiment of the utility model, and is not intended to limit the utility model. For those skilled in the art, the utility model can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the utility model shall be included in the protection scope of the utility model.

Claims

1. A thermal protection structure for the tail section of a launch vehicle, characterized in that: include: An ablation-resistant layer, a rubber-based coating and a metal structural layer; the ablation-resistant layer is used to resist the instantaneous ultra-high heat flux during the launch of the carrier rocket; The rubber-based coating is used to reduce heat conduction and maintain the temperature of the inner wall of the structure; the metal structural layer is used to maintain the structural form; the metal structural layer, the rubber-based coating and the ablation-resistant layer are arranged in sequence; the rubber-based coating is fixedly arranged on the surface of the metal structural layer, and the ablation-resistant layer is fixedly arranged on the other surface of the rubber-based coating.

2. The thermal protection structure of the tail section of a launch vehicle according to claim 1, characterized in that: The ablation-resistant layer has a withstand temperature of 1500° C., a density of 800 kg / m 3 , a thermal conductivity of 0.35 W / (m·K), and a specific heat capacity of 1500 J / (kg·K).

3. The thermal protection structure of the tail section of a launch vehicle according to claim 2, characterized in that: The thickness of the ablation-resistant layer is 2 mm.

4. The thermal protection structure of the tail section of a launch vehicle according to claim 1, characterized in that: The rubber-based coating has a temperature resistance of 800° C., a density of 650 kg / m 3 , a thermal conductivity of 0.13 W / (m·K), and a specific heat capacity of 1300 J / (kg·K).

5. The thermal protection structure of the tail section of a launch vehicle according to claim 4, characterized in that: The thickness of the rubber-based coating is 6 mm.

6. The thermal protection structure of the tail section of a launch vehicle according to claim 1, characterized in that: The metal structural layer has a density of 2700 kg / m3, a thermal conductivity of 153 W / (m·K), and a specific heat capacity of 960 J / (kg·K).

7. The thermal protection structure of the tail section of a launch vehicle according to claim 6, characterized in that: The thickness of the metal structure layer is 6 mm.

8. The thermal protection structure of the tail section of a launch vehicle according to claim 6 or 7, characterized in that: The metal structural layer is an aluminum alloy structural layer.

9. A launch vehicle tail section, characterized in that: It includes the thermal protection structure of the tail section of a launch vehicle as described in any one of claims 1 to 8.

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