High-temperature-resistant BD satellite receiving antenna

Abstract

The invention discloses a high-temperature-resistant BD satellite receiving antenna, the receiving antenna is installed on a missile body, the outer surfaces of the receiving antenna and the missile body are conformal and flush, and the receiving antenna comprises an antenna and a cover body wrapping the antenna; a mounting space for providing an antenna is arranged in the cover body, the outer side temperature of the cover body is adaptive to the working temperature of a missile body, the inner side temperature of the cover body meets the working temperature of the antenna, and the cover body has wave-transparent performance for ensuring normal communication of the antenna; the minimum working temperature of the outer side of the cover body is larger than the working temperature of the missile body, and the maximum temperature of the inner side of the cover body is smaller than the upper limit value of the working temperature of the antenna. The antenna housing of the protective antenna is provided with two functional layers, namely the thermal resistance layer and the thermal insulation layer, the thermal insulation layer is used as a protective layer in direct contact with the outside, the thermal resistance layer slows down heat transfer from the thermal insulation layer to the surface of the antenna, and the heating rate of the antenna structure is reduced; therefore, the antenna can work normally in a narrow space and is resistant to high temperature.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of antenna, and relates to a high-temperature-resistant BD satellite receiving antenna. BACKGROUND

[0002] At present, the Beidou satellite (BD satellite) global navigation system in China has been widely applied in many fields such as scientific research, agriculture and military. However, the signal strength of satellite signals reaching the earth's surface is very weak and is easily disturbed by external interference, especially the receiver terminal will be disturbed by various intentional or unintentional interference. With the wide application of high-speed vehicles, in order to ensure that high-speed vehicles provide stable and effective navigation services, it is required that the Beidou satellite receiving antenna has a low profile and can be conformally installed with the surface of the vehicle, and at the same time, the Beidou satellite receiving antenna should be adapted to the high-temperature environment of the missile under the premise of having normal communication function, and has extremely strong high-temperature resistance. The existing high-temperature-resistant BD satellite receiving antenna adopts an external structure, and the connection and fixation of the external antenna and the missile body need high-strength materials. Such materials generally have a large thermal conductivity, and the missile body will transfer heat to the antenna during flight, resulting in that the surface temperature of the antenna is too high to work, thereby causing that on the one hand, the installation volume is too large, and on the other hand, the normal communication and high-temperature resistance of the receiving antenna cannot be met at the same time. SUMMARY

[0003] In view of this, the present application sets the antenna in the radome, the radome is made of composite material, the radome is embedded in the missile body through the embedded assembly of the whole machine shell, the whole machine shell adopts a metal frame, and a heatproof coating is coated on the metal frame to isolate the missile body and the radome. On the one hand, the antenna fastening connection is solved, and on the other hand, the effect of isolating the surface heat of the missile body from the antenna is ensured. A high-temperature-resistant BD satellite receiving antenna is provided, and the radome for protecting the antenna includes two functional layers of a thermal resistance layer and a thermal insulation layer. The thermal insulation layer serves as a protective layer directly contacting the outside, and is selected as a heat protection material with high-temperature resistance, excellent heat insulation performance and high wave permeability. The thermal resistance layer is located between the antenna and the thermal insulation layer, and a material with low thermal conductivity, small density and good wave permeability is selected to slow down the heat transfer from the thermal insulation layer to the surface of the antenna, reduce the heating rate of the antenna structure, reduce the high-temperature impact of high temperature on the antenna and connector and other parts, and meet the demand that the antenna can work normally and resist high temperature in a small space. The specific scheme is as follows: A high-temperature-resistant BD satellite receiving antenna, the receiving antenna is installed on a missile body, and the outer surface of the receiving antenna is conformal and flush with the outer surface of the missile body. The receiving antenna comprises an antenna and a cover body wrapped outside the antenna, characterized in that the cover body is provided with a mounting space for the antenna, the cover body has an outside temperature adapted to the working temperature of the missile body and an inside temperature meeting the working temperature of the antenna, and the cover body has wave permeability for ensuring normal communication of the antenna. The minimum operating temperature on the outer side of the cover is greater than the operating temperature of the missile body, and the maximum temperature on the inner side of the cover is less than the upper limit of the antenna's operating temperature.

[0004] Preferably, the radome includes an antenna cover and a base plate; The radome has a U-shaped cross-section with the opening facing the base plate. The radome covers the outside of the antenna. Both ends of the radome are connected to the base plate to form a complete radome. The outer casing of the device is provided around the radome. The antenna is mounted on the base plate, and a gap is provided between the antenna and the radome; The outer casing is fitted over the radome and is installed inside the missile body.

[0005] Preferably, the outer casing of the device is coated with a heat-resistant coating on the side closest to the missile body; The heat-resistant coating has a higher temperature resistance than the missile body's operating temperature.

[0006] Preferably, the radome includes a thermal resistance layer and a heat insulation layer arranged sequentially along the missile body from the inside to the outside; The heat insulation layer has a U-shaped cross-section with the opening facing the bottom plate, and the two ends of the heat insulation layer are... The base plate is not connected separately. The insulation layer has high temperature resistance, excellent heat insulation performance, and high wave transmittance. The thermal resistance layer is located between the top of the antenna and the heat insulation layer, and is located inside the side of the heat insulation layer facing away from the base plate. The thermal resistance layer has low thermal conductivity, low density and high wave transmission performance. Wherein, the thermal conductivity of the thermal resistance layer is ≤0.2W / (m 2 K), density ≤ 0.8 g / cm³ 2 The wave transmission coefficient is greater than or equal to 0.9; The thermal conductivity of the insulation layer is ≤0.2W / (m²). 2 ·K), wave transmission coefficient ≥0.9, heat resistance temperature ≥850℃.

[0007] Preferably, the thermal resistance layer is a thermal insulation aerogel material.

[0008] Preferably, the heat insulation layer is made of quartz fiber reinforced quartz composite material with excellent heat insulation performance and low thermal conductivity.

[0009] Preferably, the heat-resistant coating is an elastic, erosion-resistant heat-protective coating.

[0010] The beneficial effects that this application can produce include: This application solves the antenna installation problem by miniaturizing the receiving antenna as a whole and embedding it on the missile body, while keeping the outer surface of the receiving antenna conformal and flush with the outer surface of the missile body, thus avoiding affecting the normal operation of the missile. The receiving antenna consists of two parts: the antenna itself and a protective cover. The side of the cover facing the missile body is the radome, used to protect the antenna from damage by the external environment. The side inside the missile body is the base plate, used to fix the antenna in place. The radome is composed of two functional layers: a thermal resistance layer and a heat insulation layer, which are fixedly connected. The heat insulation layer, as the protective layer in direct contact with the outside environment, is made of a material with excellent heat insulation performance and low thermal conductivity. The thermal resistance layer, located between the antenna and the heat insulation layer, is made of a material with low thermal conductivity, low density, and good wave transmission performance to slow down the heat transfer from the heat insulation layer to the antenna surface, effectively blocking the heat conduction path, reducing the heating rate of the antenna structure, and reducing the high-temperature impact on the antenna and connectors. This solves the problem of ensuring that the antenna is within its normal operating temperature range and can communicate normally when the installation space is limited, while also adapting the antenna to the high-temperature working environment of the missile body. This fulfills the requirement that the antenna can work normally and stably in a confined space and high-temperature environment.

[0011] In this application, the radome is designed with a U-shaped cross-section to reduce the contact area between the radome and the antenna base plate. Without affecting the antenna performance, the structural design minimizes the friction area between the radome and the air, and minimizes the transmission path of the effective heat source. The structural design effectively blocks the heat source outside the mounting projectile, meets the antenna surface temperature requirements, and improves the antenna's radiation performance. Attached Figure Description

[0012] Figure 1 This is a cross-sectional view of the structure of a high-temperature resistant BD satellite receiving antenna according to an embodiment of this application; Figure 2 This is a schematic diagram of the installation of a high-temperature resistant BD satellite receiving antenna in an embodiment of this application; List of components and reference numerals: 1. Heat-resistant coating; 2. Antenna radome; 3. Thermal resistance layer; 4. Overall casing; 5. Antenna; 6. Base plate; 7. Receiving antenna; 8. Missile body. Detailed Implementation

[0013] The present application is described in detail below with reference to the embodiments, but the present application is not limited to these embodiments.

[0014] like Figure 1 and Figure 2The diagram shows a high-temperature resistant BD satellite receiving antenna, which is mounted on a missile body 8. The outer surface of the receiving antenna is conformal to and flush with the outer surface of the missile body 8. The receiving antenna includes an antenna 5 and a cover that surrounds the antenna. The cover has a space for the antenna 5 to be installed. The cover has the following characteristics: the outer temperature is adapted to the operating temperature of the missile body 8, the inner temperature meets the operating temperature of the antenna 5, and the cover has wave transmission performance to ensure that the antenna 5 can communicate normally. The minimum operating temperature on the outer side of the cover is greater than the operating temperature of the missile body, and the maximum temperature on the inner side of the cover is less than the upper limit of the operating temperature of the antenna 5.

[0015] It should be noted that: In this application, to achieve miniaturization, the receiving antenna 7 is embedded in the missile body 8, which reduces the overall height compared to the traditional external structure. The housing adopts a hollow structure, which reduces the overall weight of the receiving antenna 7, and also has the characteristics of convenient and flexible installation.

[0016] In one embodiment of this application, since the operating temperature of the antenna 5 does not exceed 180°C, while the highest temperature on the outer surface of the missile body is 850°C for more than 400 seconds, the minimum temperature on the outer side of the cover in this application is greater than 850°C, and the maximum temperature on the inner side of the cover is less than 180°C. The cover itself has wave transmission performance, thereby achieving the following: on the one hand, the cover meets the requirement that the antenna is within the normal operating temperature range in the narrow space of the cover, and the transmission coefficient of the cover meets the communication wave transmission requirements of the antenna 5, so as to ensure that the antenna can communicate normally inside the cover; on the other hand, the outer side of the cover has high temperature resistance requirements to ensure that the antenna performance is stable and reliable in high temperature environments.

[0017] Furthermore, the cover includes an antenna cover 2 and a base plate 6; The antenna cover 2 has a U-shaped cross-section with the opening facing the base plate 6. The antenna cover 2 covers the antenna 5. The two ends of the antenna cover 2 are respectively connected to the base plate 6, forming a complete cover with the base plate 6. The outer casing 4 is provided around the antenna cover 2. The antenna 5 is mounted on the base plate 6, and the antenna 5 is spaced apart from the antenna cover 2; The outer casing 4 is fitted over the radome 2 and is installed inside the missile body.

[0018] It should be noted that: In one embodiment of this application, the outer casing 4 is made of titanium alloy, which satisfies both installation strength and low thermal conductivity, with a thermal conductivity of 0.2 W / (m²). 2 ·K); In order to ensure that the outer surface of the receiving antenna 7 is conformal and flush with the outer surface of the missile body 8 when the receiving antenna 7 is installed inside the missile body 8, in one embodiment of the application, an open mounting cavity is provided on the missile body 8, and the overall shape and size of the receiving antenna 7 are matched with the mounting cavity. To ensure that the connection between the antenna cover 2 and the base plate 6 is flat when the antenna cover 2 is fastened to the base plate 6, the end of the antenna cover 2 is flush with the periphery of the base plate 6. In order to ensure that the surface of the radome 2 is consistent with the arc direction of the missile body 8 when it is installed in the mounting cavity of the missile body 8, the shape of the top of the radome 2 (i.e. the side that is flush with the surface of the missile body 8 / the side that faces away from the base plate 6) is adapted to the shape of the missile body 8. To facilitate the installation between the radome 2 and the missile body 8, a housing 4 is provided between the radome 2 and the missile body 8. To achieve a natural transition at the installation point of the radome 2 and the missile body 8, the housing 4 is designed as a hollow rectangular columnar structure. A mounting groove is provided on the periphery of the top of the radome 2, and the thickness of the mounting groove matches the wall thickness of the housing 4. After the housing 4 is fitted over the radome 2 (i.e., at the mounting groove), the periphery of the housing 4, the radome 2, and the base plate 6 are flush. To achieve heat insulation at the installation point of the radome 2 and the missile body 8, the overall height of the housing 4 is less than the height of the mounting groove, and a connecting part extends outward along the cross-sectional direction at the end of the housing 4 facing away from the base plate 6. The top of the connecting part is coated with a heat-resistant coating 1, which on the one hand achieves the flushness of the surface at the connection point of the radome 2 and the missile body 8, and on the other hand, achieves heat insulation between the radome 2 and the missile body 8 through the housing 4 and the heat-resistant coating 1.

[0019] Furthermore, the outer casing 4 is coated with a heat-resistant coating 1 on the side near the missile body 8; The heat-resistant coating 1 has a high temperature resistance greater than the operating temperature of the missile body 8. That is, in one embodiment of this application, the heat-resistant coating 1 has a high temperature resistance of at least 850°C.

[0020] Furthermore, the radome 2 includes a thermal resistance layer 3 and a heat insulation layer arranged sequentially from the inside to the outside along the missile body 8; The heat insulation layer has a U-shaped cross-section with the opening facing the bottom plate 6, and the two sides of the heat insulation layer... The ends are respectively connected to the base plate 6, and the heat insulation layer has high temperature resistance, excellent heat insulation performance and high wave transmittance; The thermal resistance layer 3 is located between the top of the antenna 5 and the heat insulation layer, and is located inside the side of the heat insulation layer facing away from the base plate 6. The thermal resistance layer 3 has low thermal conductivity, low density and high wave transmission performance. The thermal conductivity of the thermal resistance layer 3 is ≤0.2W / (m).2 K), density ≤ 0.8 g / cm³ 2 The wave transmission coefficient is greater than or equal to 0.9; The thermal conductivity of the insulation layer is ≤0.2W / (m²). 2 ·K), wave transmission coefficient greater than ≥0.9, heat resistance temperature ≥850℃.

[0021] In the application, the heat insulation layer and the thermal resistance layer 3 are bonded together with high-temperature adhesive.

[0022] In one embodiment of this application, the high-temperature adhesive used to bond the heat insulation layer and the thermal resistance layer 3 is specifically GZJ03 silicone rubber.

[0023] Furthermore, the thermal resistance layer 3 is a thermal insulation aerogel material.

[0024] In one embodiment of this application, the thermal insulation aerogel material is specifically SR283-04 composite material, purchased from the Second Academy of China Aerospace Science and Industry Corporation.

[0025] Furthermore, the insulation layer is made of quartz fiber reinforced quartz composite material with excellent thermal insulation performance and low thermal conductivity, and its thermal conductivity is 0.2 W / (m). 2 ·K).

[0026] Furthermore, the heat-resistant coating 1 is made of TCGR-01 elastic erosion-resistant heat protection coating, which was purchased from Shandong Industrial Ceramics Research and Design Institute.

[0027] The above description is merely a few embodiments of this application and is not intended to limit this application in any way. Although this application discloses preferred embodiments as described above, it is not intended to limit this application. Any changes or modifications made by those skilled in the art without departing from the scope of the technical solution of this application using the disclosed technical content are equivalent to equivalent implementation cases and fall within the scope of the technical solution.

Claims

1. A high-temperature resistant BD satellite receiving antenna, wherein the receiving antenna (7) is mounted on a missile body (8), and the outer surface of the receiving antenna (7) is conformal and flush with the outer surface of the missile body (8), the receiving antenna comprising an antenna (5) and a cover enclosing the antenna, characterized in that, The enclosure is provided with an installation space for the antenna (5). The enclosure has the following features: the outer temperature is adapted to the working temperature of the missile body (8), the inner temperature meets the working temperature of the antenna (5), and the enclosure has the wave transmission performance to ensure that the antenna (5) can communicate normally. The minimum operating temperature on the outer side of the cover is greater than the operating temperature of the missile body, and the maximum temperature on the inner side of the cover is less than the upper limit of the operating temperature of the antenna (5).

2. The high-temperature resistant BD satellite receiving antenna according to claim 1, characterized in that, The enclosure includes an antenna cover (2) and a base plate (6); The radome (2) has a U-shaped structure with the opening facing the base plate (6) in cross section. The radome (2) covers the antenna (5). The two ends of the radome (2) are respectively connected to the base plate (6) to form a complete radome with the base plate (6). The radome (2) is provided with a complete housing (4) around its periphery. The antenna (5) is mounted on the base plate (6), and the antenna (5) is spaced apart from the antenna cover (2); The outer casing (4) is fitted over the radome (2) and is installed inside the missile body.

3. The high-temperature resistant BD satellite receiving antenna according to claim 2, characterized in that, The outer casing (4) of the machine is coated with a heat-resistant coating (1) on the side near the missile body (8). The heat-resistant coating (1) has a higher temperature resistance than the working temperature of the missile body (8).

4. A high-temperature resistant BD satellite receiving antenna according to claim 2, characterized in that, The radome (2) includes a thermal resistance layer (3) and a heat insulation layer arranged sequentially from the inside to the outside along the missile body (8); The heat insulation layer has a U-shaped cross-section with the opening facing the bottom plate (6). The two ends are respectively connected to the base plate (6), and the heat insulation layer has high temperature resistance, excellent heat insulation performance and high wave transmission; The thermal resistance layer (3) is located between the top of the antenna (5) and the heat insulation layer, and is located inside the side of the heat insulation layer facing away from the base plate (6). The thermal resistance layer (3) has low thermal conductivity, low density and high wave transmission performance. The thermal conductivity of the thermal resistance layer (3) is ≤0.2W / (m). 2 K), density ≤ 0.8 g / cm³ 2 The wave transmission coefficient is ≥0.9; The thermal conductivity of the insulation layer is ≤0.2W / (m²). 2 ·K), wave transmission coefficient greater than ≥0.9, heat resistance temperature ≥850℃.

5. A high-temperature resistant BD satellite receiving antenna according to claim 4, characterized in that, The thermal resistance layer (3) is a thermal insulation aerogel material.

6. A high-temperature resistant BD satellite receiving antenna according to claim 4, characterized in that, The heat insulation layer is made of quartz fiber reinforced quartz composite material.

7. A high-temperature resistant BD satellite receiving antenna according to claim 4, characterized in that, The heat-resistant coating (1) is an elastic erosion-resistant heat protection coating.

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