Radar environment control device and aircraft

Abstract

The invention discloses a radar environment control device and an aircraft, relates to the technical field of aerospace, and is used for ensuring normal work and service life of a radar on the basis of cooling the radar. The radar environment control device comprises a shell, a radar, a heat exchanger and a fan, a cavity is formed in the shell, and an air inlet and an air outlet which communicate with the cavity are formed in the shell. The radar is arranged in the cavity. The heat exchanger is arranged in the cavity, and a first heat exchange channel and a second heat exchange channel which are independent of each other are formed in the heat exchanger. An inlet of the first heat exchange channel communicates with the air inlet, an outlet of the first heat exchange channel communicates with the air outlet, and low-temperature gas outside the cavity can flow through the first heat exchange channel through the air inlet and the air outlet. An inlet and an outlet of the second heat exchange channel communicate with the interior of the cavity. The fan is arranged in the cavity and located on the ventilation path of the second heat exchange channel. The radar environment control device is used for detecting and tracking a target.

Description

Technical Field

[0001] The present application relates to the field of aerospace technology, and in particular to a radar environmental control device and an aircraft. Background Art

[0002] Aircraft are usually equipped with radars, which can search and locate targets by transmitting and receiving electromagnetic waves. Radars are usually set inside a radome to avoid contact and collision with objects outside the radome and damage. However, radars release a lot of heat during operation, which is difficult to dissipate inside the radome, thus affecting their normal operation.

[0003] In the related art, in order to cool the radar, an air inlet and an air outlet are opened on the radome. In this way, during the flight of the aircraft, low-temperature gas at high altitude will enter the radome from the air inlet, and then be discharged from the air outlet after cooling the radar.

[0004] However, it is inevitable that clouds rich in water vapor will appear in the high sky, and the water vapor will enter the radar dome along with the gas, which will affect the normal operation of the radar and shorten the service life of the radar. Summary of the invention

[0005] In order to solve the above technical problems, the present application provides a radar environmental control device and an aircraft, which are used to ensure the normal operation and service life of the radar while achieving radar cooling.

[0006] This application is implemented through the following technical solutions.

[0007] The first aspect of the present application provides a radar environmental control device. The radar environmental control device includes a shell, a radar, a heat exchanger and a fan. The shell has a cavity inside, and an air inlet and an air outlet connected to the cavity are formed on the shell. The radar is arranged in the cavity. The heat exchanger is arranged in the cavity, and a first heat exchange channel and a second heat exchange channel that are independent of each other are formed on the heat exchanger; the inlet of the first heat exchange channel is connected to the air inlet, and the outlet of the first heat exchange channel is connected to the air outlet, and the low-temperature gas outside the cavity can flow through the first heat exchange channel through the air inlet and the air outlet; the inlet and outlet of the second heat exchange channel are both connected to the inside of the cavity. The fan is arranged in the cavity and is located on the ventilation path of the second heat exchange channel.

[0008] In the technical solution of the embodiment of the present application, the radar can transmit and receive electromagnetic waves to search and locate the target.

[0009] By setting a heat exchanger and a fan, under the action of the fan, the high-temperature gas inside the cavity can flow through the second heat exchange channel. Since the low-temperature gas outside the cavity can flow through the first heat exchange channel, the heat in the gas in the second heat exchange channel will be transferred to the gas in the first heat exchange channel through the heat exchanger. In this way, the temperature of the gas discharged from the outlet of the second heat exchange channel will be reduced, thereby cooling the gas inside the cavity and thus cooling the radar. Since the gas outside the cavity does not enter the cavity, the moisture outside the cavity will not enter the cavity and will not affect the radar, thereby ensuring the normal operation of the radar and its service life.

[0010] In some embodiments of the present application, an outlet of the second heat exchange channel faces the radar.

[0011] In this way, the low-temperature gas discharged from the outlet of the second heat exchange channel can be directly blown toward the radar, thereby achieving a better cooling effect.

[0012] In some embodiments of the present application, the inlet centerline of the second heat exchange channel intersects with the outlet centerline of the second heat exchange channel.

[0013] In this way, the airflow direction of the gas entering from the inlet of the second heat exchange channel intersects with the airflow direction of the gas discharged from the outlet of the second heat exchange channel, which can facilitate the flow of the gas inside the cavity, thereby making the gas temperature at different positions inside the cavity uniform.

[0014] In some embodiments of the present application, the air inlet is located on the windward side of the shell, and the air outlet is located on the non-windward side of the shell.

[0015] In this way, the pressure difference between the windward side and the non-windward side can be utilized to allow the gas outside the cavity to flow through the first heat exchange channel. This eliminates the need to provide additional power for the gas flow in the first heat exchange channel, thereby reducing costs.

[0016] In some embodiments of the present application, a guide pipe is further included, the outlet of the guide pipe is connected to the inlet of the second heat exchange channel, and the inlet of the guide pipe is connected to the cavity; along the air flow direction in the guide pipe, the cross-section of the guide pipe gradually decreases.

[0017] In this way, the gas in the cavity will enter the second heat exchange channel through the guide pipe. Since the cross-section of the guide pipe gradually decreases along the air flow direction in the guide pipe, the gas flow rate in the guide pipe will gradually increase. In this way, the gas flow rate entering the second heat exchange channel will be enhanced, which can improve the heat exchange efficiency of the first heat exchange channel and the second heat exchange channel.

[0018] In some embodiments of the present application, an airflow adjustment device is further included, which is arranged at the inlet of the first heat exchange channel and is used to adjust the conductivity of the first heat exchange channel.

[0019] In this way, the airflow regulating device can adjust the gas flow entering the first heat exchange channel from the air inlet, and can adjust the heat exchange efficiency of the gas in the first heat exchange channel and the second heat exchange channel to adapt to different cooling requirements.

[0020] In some embodiments of the present application, a first temperature sensor is further included, which is arranged in the cavity and is used to detect the temperature in the cavity. The first temperature sensor is electrically connected to the airflow regulating device, and the airflow regulating device is used to adjust the conductivity of the first heat exchange channel according to the detection result of the first temperature sensor.

[0021] In this way, the first temperature sensor and the airflow regulating device can cooperate with each other, and the airflow regulating device controls the airflow regulating device through the detection result of the first temperature sensor to adjust the airflow flow entering the first heat exchange channel, so that the control is more accurate.

[0022] In some embodiments of the present application, a second temperature sensor and a third temperature sensor are further included. The second temperature sensor is arranged at the inlet of the second heat exchange channel, and is used to detect the temperature of the gas passing through the inlet of the second heat exchange channel; the second temperature sensor is electrically connected to the fan. The third temperature sensor is arranged at the outlet of the second heat exchange channel, and is used to detect the temperature of the gas passing through the outlet of the second heat exchange channel; the third temperature sensor is electrically connected to the fan. The speed of the fan is adjusted according to the temperature difference detected by the second temperature sensor and the third temperature sensor.

[0023] In this way, the temperature difference between the gas at the inlet and outlet of the second heat exchange channel can be determined based on the difference in temperatures detected by the second temperature sensor and the third temperature sensor, thereby determining the heat exchange efficiency of the gas in the second heat exchange channel and the first heat exchange channel, and thereby adjusting the fan to meet different cooling requirements.

[0024] In some embodiments of the present application, an air inlet duct and / or an air outlet duct is also included, the air inlet duct is arranged in the cavity, the air inlet end of the air inlet duct is connected to the air inlet, and the air outlet end of the air inlet duct is connected to the inlet of the first heat exchange channel; and / or, the air outlet duct is arranged in the cavity, the air inlet end of the air outlet duct is connected to the air outlet, and the air outlet end of the air outlet duct is connected to the outlet of the first heat exchange channel.

[0025] By providing at least one of the air inlet duct and the air outlet duct, the heat exchanger can be conveniently arranged at a suitable position in the cavity, which facilitates the spatial layout of components such as the heat exchanger and the radar inside the cavity.

[0026] In some embodiments of the present application, the air inlet end of the air inlet duct surrounds the air inlet, and the end face of the air inlet end of the air inlet duct is fitted and connected to the inner wall surface of the cavity; and / or, the air outlet end of the air outlet duct surrounds the air outlet, and the end face of the air outlet end of the air outlet duct is fitted and connected to the inner wall surface of the cavity.

[0027] In this way, the sealing degree of the connection between the air inlet end of the air inlet duct and the air inlet can be ensured, and the sealing degree of the connection between the air outlet end of the air outlet duct and the air outlet can be ensured, thereby preventing the gas outside the cavity from entering the cavity from the connection between the air inlet duct and the air inlet, and preventing the gas outside the cavity from entering the cavity from the connection between the air outlet duct and the air outlet, thereby ensuring the normal operation of electronic components such as radar inside the cavity and ensuring their service life.

[0028] In some embodiments of the present application, a filter is provided at at least one of the air inlet and the air outlet.

[0029] In this way, it is possible to prevent external debris from entering the cavity through at least one of the air inlet and the air outlet, and to prevent the first heat exchange channel from being blocked, thereby ensuring the normal operation of the heat exchanger.

[0030] In some embodiments of the present application, the filter screen is connected to the shell, and the thickness of the filter screen is greater than the thickness of the shell.

[0031] By increasing the thickness of the filter, the structural strength of the filter is increased. When the filter is connected to at least one of the air inlet and the air outlet, the structural strength of the shell at at least one of the air inlet and the air outlet can be guaranteed, thereby ensuring the service life of the shell.

[0032] In some embodiments of the present application, the housing includes a cover body and a blocking portion, the cover body is formed with an opening, the blocking portion blocks the opening to form a cavity, and the blocking portion is connected to the cover body.

[0033] By configuring the shell to consist of a cover body and a sealing portion, it is possible to facilitate the installation of components such as a radar inside the cavity.

[0034] In some embodiments of the present application, a first sealing member is further included, which is disposed between the cover body and the sealing portion and is disposed along the circumference of the opening to seal the cover body and the sealing portion.

[0035] In this way, the first seal can be used to seal the connection between the cover body and the sealing part, thereby reducing the probability of gas outside the cavity entering the cavity through the connection between the cover body and the sealing part, thereby ensuring an independent environment in the cavity.

[0036] In some embodiments of the present application, the radar environmental control device also includes a connecting piece, which is arranged at the opening and along the circumference of the opening. The connecting piece is at least partially located on one side in the thickness direction of the cover body and is connected to the cover body. The connecting piece is connected to the sealing part.

[0037] In this way, the connecting piece can be connected to the cover body along the thickness direction of the cover body, and then the blocking part is connected to the cover body through the connecting piece. Since the thickness of the cover body is generally thin, this can avoid the blocking part being connected to the wall surface of the cover body extending along its thickness direction, and the connection strength can be guaranteed.

[0038] In some embodiments of the present application, the cover body includes a protective part and a middle cover, the protective part is connected to the blocking part, the opening is at least partially located on the middle cover, and the windward side and the leeward side of the middle cover are respectively connected to the protective part.

[0039] With such arrangement, at least a cavity portion is formed inside the middle cover, and two protective portions located on the windward side and the leeward side of the middle cover can protect the middle cover, thereby ensuring the service life of the cover body.

[0040] In some embodiments of the present application, the middle cover is overlapped on a side surface of the protective part away from the blocking part.

[0041] In this way, the protective parts at both ends of the middle cover can be fixed on the blocking part first, and then the middle cover can be overlapped on the protective part from the side of the protective part away from the blocking part, and then the middle cover can be connected to the blocking part, which can facilitate the installation of the middle cover.

[0042] In some embodiments of the present application, a cavity is provided at the connection position between the middle cover and the protective part; the radar environmental control device also includes a second sealing member, which is arranged between the protective part and the middle cover to seal the protective part and the middle cover.

[0043] In this way, the sealing degree of the connection position between the protective part and the middle cover can be ensured, thereby preventing the gas outside the cavity from entering the cavity and ensuring an independent environment inside the cavity.

[0044] A second aspect of the present application provides an aircraft, including an aircraft body and a radar environment control device, wherein the radar environment control device is the radar environment control device provided in any of the above embodiments, and the radar environment control device is connected to the aircraft body.

[0045] The aircraft in the present application includes the radar environmental control device in any of the above embodiments, so it can achieve the same beneficial effects, which will not be repeated here. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present application. Moreover, the same reference numerals are used throughout the drawings to represent the same components. In the drawings:

[0047] Figure 1A schematic diagram of an external structure of an aircraft provided for some embodiments of the present application;

[0048] Figure 2 A schematic diagram of an external structure of a radar environment control device provided in some embodiments of the present application;

[0049] Figure 3 A schematic diagram of an external structure of a housing provided in some embodiments of the present application;

[0050] Figure 4 A cross-sectional schematic diagram of a blocking portion and a cover body provided in some embodiments of the present application;

[0051] Figure 5 Another cross-sectional schematic diagram of a blocking portion and a cover body provided in some embodiments of the present application;

[0052] Figure 6 Another cross-sectional schematic diagram of the blocking portion and the cover body provided in some embodiments of the present application;

[0053] Figure 7 A cross-sectional schematic diagram of a middle cover, a protective portion and a second sealing member provided for some embodiments of the present application;

[0054] Figure 8 Another cross-sectional schematic diagram of the middle cover, the protective portion and the second sealing member provided for some embodiments of the present application;

[0055] Fig. 9 A schematic diagram of an external structure of a heat exchanger and a fan provided in some embodiments of the present application;

[0056] Fig.10 A cross-sectional schematic diagram of the cooperation between the air inlet duct and the housing provided in some embodiments of the present application;

[0057] Fig.11 A schematic diagram of another external structure of a heat exchanger and a fan provided in some embodiments of the present application;

[0058] Fig.12 Another cross-sectional schematic diagram of the cooperation between the air inlet duct and the housing provided in some embodiments of the present application;

[0059] Fig.13 A cross-sectional schematic diagram of the cooperation between the air outlet duct and the housing provided in some embodiments of the present application;

[0060] Fig.14 Another cross-sectional schematic diagram of the cooperation between the air outlet duct and the housing provided in some embodiments of the present application.

[0061] Description of Reference Numerals

[0062] 01- Aircraft;

[0063] 1- Aircraft body;

[0064] 2-radar environmental control device; 21-shell; a-cavity; b-air inlet; c-air outlet; 211-cover; d-opening; 2111-middle cover; 2112-protective part; 212-blocking part; 22-radar; 23-heat exchanger; 231-first heat exchange channel; 232-second heat exchange channel; 24-fan; 25-first sealing member; 26-connecting member; 261-first connecting plate; 262-second connecting plate; 27-second sealing member; 28-flow guide duct; 29-air flow adjustment device; 30-second temperature sensor; 31-third temperature sensor; 32-electric control box; 33-air inlet duct; 331-first groove; 332-first protrusion; 333-first positioning protrusion; 34-air outlet duct; 341-second groove; 342-second protrusion; 343-second positioning protrusion; 35-filter. DETAILED DESCRIPTION

[0065] The following embodiments of the technical solution of the present application are described in detail in conjunction with the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the present application, and are therefore only used as examples, and cannot be used to limit the scope of protection of the present application.

[0066] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by technicians in the technical field to which this application belongs; the terms used herein are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" in the specification and claims of this application and the above-mentioned figure descriptions and any variations thereof are intended to cover non-exclusive inclusions.

[0067] In the description of the embodiments of the present application, the technical terms "first", "second", "third", etc. are only used to distinguish different objects, and cannot be understood as indicating or implying relative importance or implicitly indicating the number, specific order or primary and secondary relationship of the indicated technical features. In the description of the embodiments of the present application, the meaning of "multiple" is more than two, unless otherwise clearly and specifically defined.

[0068] Reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase in various locations in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0069] In the description of the embodiments of the present application, the term "and / or" is only a description of the association relationship of associated objects, indicating that three relationships may exist. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone. In addition, the character " / " in this article generally indicates that the associated objects before and after are in an "or" relationship.

[0070] In the description of the embodiments of the present application, the orientation or position relationship indicated by technical terms such as "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", and "circumferential" are based on the orientation or position relationship shown in the accompanying drawings. They are only for the convenience of describing the embodiments of the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed, operated or used in a specific orientation. Therefore, they should not be understood as limitations on the embodiments of the present application.

[0071] In the description of the embodiments of the present application, unless otherwise clearly specified and limited, technical terms such as "installed", "connected", "connected", "fixed" and the like 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 an indirect connection through an intermediate medium, and it can be the internal connection of two elements or the interaction relationship between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0072] In the description of the embodiments of the present application, unless otherwise clearly specified and limited, the technical term "contact" should be understood in a broad sense, and may be direct contact or contact through an intermediate medium layer. It may be contact with essentially no interaction force between the two contacting parties, or it may be contact with interaction force between the two contacting parties.

[0073] Below, this application is described in detail.

[0074] As a flying tool, an aircraft is widely used in the field of aerospace technology. For example, an aircraft can be an airplane, on which a radar is generally installed. The radar can track and locate targets by transmitting and receiving electromagnetic waves.

[0075] Based on this, Figure 1 As shown, the present application provides an aircraft 01 on the one hand, the aircraft 01 includes an aircraft body 1 and a radar environmental control device 2, the radar environmental control device 2 is connected to the aircraft body 1, and the radar environmental control device 2 includes a radar 22, so that the aircraft body 1 undertakes the flight mission, and the radar 22 performs detection, tracking and other functions.

[0076] In some examples, such as Figure 1 As shown, the radar environmental control device 2 is connected to the lower abdomen of the aircraft body 1, and the radar 22 rotates in a vertical direction to transmit and receive electromagnetic waves in all directions. In this way, the aircraft body 1 will not block the electromagnetic waves, and the detection accuracy of the radar 22 can be improved.

[0077] In some examples, the radar environment control device 2 further includes a housing 21, the housing 21 is connected to the aircraft body 1, the housing 21 has a cavity a inside, and the radar 22 is disposed in the cavity a. By arranging the radar 22 in the housing 21, the housing 21 can play a protective role to protect the radar 22.

[0078] However, the radar 22 will generate a large amount of heat during operation, especially the antenna, transmitter and other components in the radar 22, which can generate a large amount of heat in a short time. Since the radar 22 is arranged in the cavity a, the heat will be released into the cavity a and is difficult to dissipate. This can easily cause thermal deformation of the structure of some components in the radar 22 (for example, the antenna, transmitter), thereby reducing the performance of the radar 22. When the temperature is too high, it may even cause the radar 22 to burn out at high temperature.

[0079] Therefore, the radar 22 needs to be cooled. In the related technology, a variety of cooling and heat dissipation methods are provided, which are introduced below.

[0080] The first one is to directly open a first ventilation hole and a second ventilation hole on the shell 21, so that during the flight of the aircraft 01, the low-temperature gas at high altitude will enter the cavity a from the first ventilation hole, and then be discharged from the second ventilation hole after cooling the radar 22.

[0081] However, it is inevitable that clouds rich in water vapor will appear in the high altitude, and the water vapor will also enter the cavity a along with the gas, and then adhere to the radar 22, which will affect the normal operation of the radar 22 and shorten the service life of the radar 22.

[0082] The second method uses liquid cooling to remove heat from the cavity a and the radar 22 through heat exchange of liquid in two liquid cooling pipes.

[0083] However, the liquid cooling system used for liquid cooling is complex and bulky, and the weight of the coolant in the liquid cooling pipeline is also heavy, which will increase the modification and production costs of the aircraft 01.

[0084] The third type is that a liquid cooling pipe is arranged on the shell 21, so that the liquid cooling pipe is partially arranged inside the cavity a and partially arranged outside the cavity a. The heat inside the cavity a is taken away by the liquid in the liquid cooling pipe, and then the gas outside the cavity a is used to cool the liquid in the liquid cooling pipe.

[0085] However, in this arrangement, in order to improve the heat dissipation effect, the portion of the liquid cooling pipe located in cavity a needs to be in contact with the gas in cavity a as much as possible, which will occupy the space in cavity a.

[0086] A fourth method is to directly set a fan 24 inside the cavity a to blow air to the radar 22 to reduce the temperature of the radar 22 , and then allow the gas in the cavity a to exchange heat with the gas outside the cavity a through the shell 21 .

[0087] However, due to the influence of the shell 21, in this heat dissipation mode, the heat exchange efficiency between the gas in the cavity a and the gas outside the cavity a is low, so the heat dissipation effect on the radar 22 is poor.

[0088] Based on the above problems, the present application provides a radar environment control device 2 to solve the above problems. The radar environment control device 2 is specifically introduced below.

[0089] In some embodiments, Figure 2 As shown, the radar environmental control device 2 includes a housing 21, a radar 22, a heat exchanger 23 and a fan 24. The housing 21 has a cavity a inside, and the housing 21 is formed with an air inlet b and an air outlet c connected to the cavity a. The radar 22 is arranged in the cavity a. The heat exchanger 23 is arranged in the cavity a, and the heat exchanger 23 is formed with a first heat exchange channel 231 and a second heat exchange channel 232 that are independent of each other; the inlet of the first heat exchange channel 231 is connected to the air inlet b, and the outlet of the first heat exchange channel 231 is connected to the air outlet c, and the low-temperature gas outside the cavity a can flow through the first heat exchange channel 231 through the air inlet b and the air outlet c; the inlet and outlet of the second heat exchange channel 232 are both connected to the inside of the cavity a. The fan 24 is arranged in the cavity a and is located on the ventilation path of the second heat exchange channel 232.

[0090] It can be understood that the shell 21 needs to allow the penetration of electromagnetic waves, so as to ensure that the radar 22 receives the electromagnetic waves, or transmits the electromagnetic waves emitted by the radar 22 to the outside of the cavity a.

[0091] In some examples, the outer surface of the shell 21 on the side away from the aircraft body 1 is an arc-shaped surface. Along the arrangement direction of the windward side and the leeward side of the aircraft body 1, the cross-section of the shell 21 first increases and then decreases. In this way, the shell 21 is semi-shuttle-shaped. During the flight of the aircraft body 1, the impact of the airflow on the shell 21 can be reduced, thereby ensuring the normal flight of the aircraft 01.

[0092] In some examples, the fan 24 is disposed at the inlet of the second heat exchange channel 232 , so that the gas in the cavity a can be better sucked into the second heat exchange channel 232 , thereby ensuring the heat exchange efficiency of the gas in the first heat exchange channel 231 and the second heat exchange channel 232 .

[0093] The fan 24 may be connected to the second heat exchanger 23 , or may be connected to the housing 21 .

[0094] In addition, the number of the fans 24 may be one or more, for example, two, three, four or more. The fans 24 are arranged within the inlet range of the second heat exchange channel 232, and the fans 24 are used to draw air simultaneously to ensure the intensity of heat dissipation.

[0095] In some examples, the heat exchanger 23 may be connected to the inner wall of the housing 21 via a mounting plate.

[0096] In some examples, the extension direction of the first heat exchange channel 231 intersects with the extension direction of the second heat exchange channel 232 , for example, at 90°, which can facilitate the arrangement of the first heat exchange channel 231 and the second heat exchange channel 232 .

[0097] In some examples, the temperature of the core components in the radar 22 is controlled below 75° C. and the temperature of the gas in the cavity a is controlled below 40° C. through heat exchange by the heat exchanger 23 .

[0098] Through the above-mentioned arrangement, under the action of the fan 24, the high-temperature gas inside the cavity a can flow through the second heat exchange channel 232. Since the low-temperature gas outside the cavity a can flow through the first heat exchange channel 231, the heat in the gas in the second heat exchange channel 232 will be transferred to the gas in the first heat exchange channel 231 through the heat exchanger 23. In this way, the temperature of the gas discharged from the outlet of the second heat exchange channel 232 will be reduced, thereby cooling the gas inside the cavity a and thereby cooling the radar 22.

[0099] Compared with the first heat dissipation method in the above-mentioned related technology, since the gas outside cavity a in the present application does not enter the cavity a, but passes through cavity a through the first heat exchange channel 231, the moisture outside cavity a will not enter the gas inside cavity a, and will not affect the radar 22, thereby ensuring the normal operation of the radar 22 and its service life.

[0100] Compared with the second heat dissipation method in the above-mentioned related art, the heat exchange medium in the present application is air, so it is lighter in weight and has a simpler structure.

[0101] Compared with the third heat dissipation method in the above-mentioned related technology, the gas inside cavity a in the present application can circulate between the second heat exchange channel 232 and cavity a, so that the overall cooling of the gas in cavity a can be achieved without occupying too much cavity a space.

[0102] Compared with the fourth heat dissipation method in the above-mentioned related technology, the present application can ensure the heat dissipation effect of the gas in the cavity a.

[0103] In some embodiments, Figure 3 , Figure 4 As shown, the housing 21 includes a cover body 211 and a blocking portion 212 . The cover body 211 is formed with an opening d. The blocking portion 212 blocks the opening d to form a cavity a. The blocking portion 212 is connected to the cover body 211 .

[0104] In some examples, the blocking portion 212 is detachably connected to the cover body 211 , which can facilitate the installation and removal of components such as the radar 22 and the heat exchanger 23 .

[0105] Through the above arrangement, the shell 21 is divided into two parts, namely, a cover body 211 and a sealing part 212. Thus, after the radar 22, the heat exchanger 23 and other components are set in place, the cover body 211 and the sealing part 212 can be connected together to form a cavity a for accommodating the radar 22, the heat exchanger 23 and other components. This can facilitate the installation of the radar 22, the heat exchanger 23 and other components and improve the convenience of installation.

[0106] In some examples, the air inlet b and the air outlet c are disposed on the cover body 211 .

[0107] In some examples, the blocking portion 212 may be a skin on the aircraft body 1 , which is wrapped around the outside of the aircraft body 1 . By blocking the opening d with the skin, the cover 211 can be more tightly combined with the aircraft body 1 .

[0108] In some examples, components such as the radar 22, the heat exchanger 23, and the fan 24 can be connected to the sealing portion 212, and then the sealing portion 212 can be connected to the aircraft body 1, and finally the cover body 211 can be covered on the outside so that the sealing portion 212 blocks the opening d, which makes the installation relatively simple.

[0109] In some examples, the cover body 211 and the sealing portion 212 can be detachably connected, for example, by screw fastening, snap-on connection, etc. This not only facilitates the installation of components such as the radar 22 and the heat exchanger 23, but also facilitates the disassembly of components such as the radar 22 and the heat exchanger 23.

[0110] In some examples, the blocking portion 212 may be located in the opening d to block the opening d.

[0111] In other examples, such as Figure 4 , Figure 5 As shown, the blocking portion 212 may also be covered on the wall surface where the opening d is located to block the opening d, so that the blocking portion 212 can be easily connected to the cover body 211.

[0112] For example, Figure 4 As shown, the wall surface where the opening d is located can be the outer surface of the cover body 211, so that the blocking part 212 is directly covered on the outer surface of the cover body 211 and connected to the cover body 211, which can facilitate the connection between the blocking part 212 and the cover body 211.

[0113] For example, Figure 5 As shown, the wall surface where the opening d is located can also be an edge surface extending along the thickness direction of the cover body 211, and the edge surface surrounds the opening d. In this way, along the arrangement direction of the cover body 211 and the blocking part 212, the connection between the cover body 211 and the blocking part 212 can withstand greater force.

[0114] In this case, in order to facilitate the connection of the blocking portion 212 to the cover body 211, the blocking portion 212 is directly connected to the edge surface, for example, by using screws to sequentially penetrate the blocking portion 212 and the edge surface to achieve connection.

[0115] However, since the thickness of the cover body 211 is generally thin, the above fixing method causes great damage to the wall plate of the cover body 211, and the fixing firmness is also low.

[0116] Based on the above problems, in some embodiments, Figure 6 As shown, the radar environmental control device 2 also includes a connecting member 26, which is arranged at the opening d and arranged along the circumference of the opening d. The connecting member 26 is at least partially located on one side of the cover body 211 in the thickness direction and is connected to the cover body 211. The connecting member 26 is connected to the blocking portion 212.

[0117] The connecting member 26 may extend along the circumference of the opening d for one circle. Alternatively, the connecting member 26 may extend along the circumference of the opening d for one section. Alternatively, the connecting member 26 may include a plurality of connecting sections, which are arranged along the circumference of the opening d for one circle. For example, the plurality of connecting sections may be arranged at intervals or closely adjacent to each other along the circumference of the opening d, and each connecting section is connected to the cover body 211 and the blocking portion 212.

[0118] In addition, the connector 26 may be connected to the cover body 211 by fasteners such as screws.

[0119] In some examples, the connection member 26 may be a metal member with high structural strength.

[0120] In some examples, such as Figure 6As shown, the connecting member 26 includes a first connecting plate 261 and a second connecting plate 262 connected to each other. The first connecting plate 261 is arranged on the inner side or the outer side of the cover body 211 along the thickness direction thereof, and is arranged along the circumference of the opening d, and is connected to the cover body 211. The second connecting plate 262 is arranged between the blocking portion 212 and the edge surface extending along the thickness direction of the cover body 211, and is arranged along the circumference of the opening d, and is connected to the blocking portion 212. In this way, the blocking portion 212 can be connected to the cover body 211 through the second connecting plate 262 and the first connecting plate 261, and the existence of the second connecting plate 262 can facilitate the connection of the blocking portion 212.

[0121] Exemplarily, the first connecting plate 261 is fixed to the cover body 211 by screws. In order to improve the connection strength between the screws and the first connecting plate 261, a threaded connection part is embedded inside the cover body 211 so that the screws extend into the cover body 211 and are threadedly connected with the threaded connection part.

[0122] Exemplarily, the second connecting plate 262 may be overlapped on the edge surface, so as to improve the connection stability among the connecting member 26 , the cover body 211 and the blocking portion 212 .

[0123] Through the above arrangement, the blocking part 212 can be connected to the cover body 211 by setting the connecting member 26 as a transfer component. Since the connecting member 26 is at least partially located on one side of the cover body 211 along its thickness direction, even if a fastener such as a screw passes through the connecting member 26 and the cover body 211, it passes through at least one of the outer wall surface and the inner wall surface of the cover body 211. Since the outer wall surface and the inner wall surface of the cover body 211 have a large area, the presence of fasteners such as screws will not cause significant damage to the cover body 211, and the structural strength of the cover body 211 can be ensured. And since the connecting member 26 is connected to the blocking part 212, this connection method can still ensure the force strength at the connection between the blocking part 212 and the cover body 211 along the arrangement direction of the blocking part 212 and the cover body 211.

[0124] In some embodiments, Figures 4 to 6 As shown, the radar environmental control device 2 further includes a first sealing member 25 , which is disposed between the cover body 211 and the blocking portion 212 and along the circumferential direction of the opening d to seal the cover body 211 and the blocking portion 212 .

[0125] In some examples, the first sealing member 25 may extend around the circumference of the opening d, so as to ensure the tightness of the seal to the greatest extent.

[0126] In some other examples, the first sealing member 25 includes a plurality of first sealing segments, and the plurality of first sealing segments are spaced apart or closely disposed along the circumference of the opening d.

[0127] In some examples, the first sealing member 25 may include a toothed sealing strip, which is disposed along the circumference of the opening d.

[0128] In some examples, the first sealing member 25 may be fixed to the sealing portion 212 or the cover body 211 , so that the first sealing member 25 may be stably disposed between the sealing portion 212 and the cover body 211 .

[0129] In some examples, when the cover body 211 and the blocking portion 212 are connected together by the connecting member 26 , a first sealing member 25 may be provided between the blocking portion 212 and the connecting member 26 and between the cover body 211 and the connecting member 26 .

[0130] Exemplarily, the connector 26 includes a first connector plate 261 and a second connector plate 262, and the first connector plate 261 is located on the outside of the cover body 211 along its thickness direction, so that the first seal 25 only needs to be arranged between the second connector plate 262 and the sealing portion 212 to meet the sealing requirements.

[0131] Through the above-mentioned arrangement, the first seal 25 can be used to seal the connection between the cover body 211 and the sealing part 212, thereby reducing the probability of gas outside the cavity a entering the cavity a from the connection between the cover body 211 and the sealing part 212, ensuring an independent environment inside the cavity a, and thus ensuring the normal operation of components such as the radar 22 and the heat exchanger 23 inside the cavity a.

[0132] The cover body 211 may be an integral structure, or the cover body 211 may be composed of multiple sections. The structure of the cover body 211 is described below.

[0133] In some embodiments, Figure 3 As shown, the cover body 211 includes a middle cover 2111 and a protective portion 2112, the protective portion 2112 is connected to the blocking portion 212, the opening d is at least partially located on the middle cover 2111, and the windward side and the leeward side of the middle cover 2111 are respectively connected to the protective portion 2112.

[0134] It can be understood that when the shell 21 is installed on the aircraft body 1, the windward side of the middle cover 2111 is the windward side of the aircraft body 1, located on the front side of the aircraft body 1, and the leeward side is opposite to the windward side, located on the rear side of the aircraft body 1.

[0135] In some examples, the structural strength of the protective portion 2112 can be set higher, so that the middle cover 2111 can be better protected.

[0136] Exemplarily, the material of the protective part 2112 includes aluminum alloy. The protective part 2112 made of aluminum alloy has high structural strength and light weight. It can reduce the overall weight of the radar environmental control device 2 and reduce flight costs on the basis of effectively protecting the middle cover 2111. In addition, since the two protective parts 2112 are respectively located on the windward side and the leeward side of the middle cover 2111, when the protective part 2112 is struck by lightning, the protective part 2112 made of aluminum alloy can conduct current to the aircraft body 1, so that the radar 22 and other components inside the cavity a can be protected from lightning. Of course, during the flight, the existence of the protective part 2112 can also protect the middle cover 2111 from being hit by birds.

[0137] In some examples, the material of the middle cover 2111 needs to meet the wave transmission requirement. For example, the material of the middle cover 2111 may include fiberglass.

[0138] Exemplarily, the interior of the middle cover 2111 is a honeycomb structure, which can not only reduce the weight of the middle cover 2111 and the flight burden of the aircraft body 1, but also improve the wave transmission ability of the middle cover 2111, so that the radar 22 can better receive and transmit electromagnetic waves.

[0139] In some examples, the protective portion 2112 is also a cover-shaped structure, and the two protective portions 2112 and the middle cover 2111 are spliced ​​together to form the cover body 211, and the opening d is located on the same side of the two protective portions 2112 and the middle cover 2111, and the two protective portions 2112 and the middle cover 2111 both have a portion with the opening d, that is, the portions of the opening d on the three are spliced ​​into the opening d.

[0140] With such a configuration, at least part of the cavity a is formed inside the middle cover 2111, and components such as the radar 22 are at least partially located inside the middle cover 2111, so that the middle cover 2111 can play an important role in accommodating. Since the windward side and the leeward side of the middle cover 2111 are provided with protective parts 2112 respectively, the two protective parts 2112 can protect the middle cover 2111, and prevent debris or birds on the windward side or the leeward side of the middle cover 2111 from directly hitting the middle cover 2111, thereby ensuring the service life of the cover body 211.

[0141] On this basis, in some embodiments, such as Figure 7 , Figure 8 As shown, the middle cover 2111 overlaps the side surface of the protective portion 2112 away from the blocking portion 212 .

[0142] In some examples, when the protection portion 2112 is a cover-shaped structure, the middle cover 2111 is overlapped at the edge of the protection portion 2112 close to the middle cover 2111 .

[0143] In some examples, around the arrangement direction of the protective portion 2112 and the middle cover 2111, the overlapping surface between the middle cover 2111 and the protective portion 2112 extends from one edge of the middle cover 2111 to the other side, which can improve the stability of the overlapping.

[0144] In some examples, a step surface concave toward the blocking portion 212 is formed on the side of the protective portion 2112 facing away from the blocking portion 212, and the middle cover 2111 overlaps the step surface so that the side surface of the middle cover 2111 facing away from the blocking portion 212 and the side surface of the protective portion 2112 facing away from the blocking portion 212 are located on the same surface. In this way, the outer wall surface of the cover body 211 away from the blocking portion 212 can be made smoother, thereby reducing flight resistance.

[0145] Through the above arrangement, when assembling the radar environment control device 2 under the aircraft body 1, the blocking part 212 can be connected to the bottom of the aircraft body 1 first, and then the protection parts 2112 located at both ends of the middle cover 2111 can be fixed on the blocking part 212, and then the radar 22, heat exchanger 23 and other components are connected to the blocking part 212, and the radar 22, heat exchanger 23 and other components are located between the two blocking parts 212, and then the middle cover 2111 is overlapped on the protection part 2112 from the side of the protection part 2112 away from the blocking part 212, so that the middle cover 2111 and the blocking part 212 are connected to form at least part of the cavity a. In this way, it is convenient to install the radar environment control device 2 on the aircraft body 1, and the convenience of installation is improved.

[0146] In some embodiments, as shown in FIG. Figure 7 , Figure 8 As shown, there is a cavity a at the connection position between the middle cover 2111 and the protection part 2112. The radar environment control device 2 further includes a second sealing member 27, which is disposed between the protection part 2112 and the middle cover 2111 to seal the protection part 2112 and the middle cover 2111.

[0147] It should be explained that the presence of cavity a at the connection position between the middle cover 2111 and the protective part 2112 means that both the middle cover 2111 and the protective part 2112 have an opening d, so that after the sealing part 212 blocks the opening d to form the cavity a, the middle cover 2111 and the protective part 2112 both participate in forming the cavity a. Therefore, when the protective part 2112 is connected to the middle cover 2111, there may be a gap connecting the inside and outside of the cavity a at the connection position, so the second sealing member 27 can be used for sealing.

[0148] In some examples, when the middle cover 2111 overlaps the protective portion 2112 , the second sealing member 27 is located between two opposite overlapping surfaces of the middle cover 2111 and the protective portion 2112 .

[0149] Through the above arrangement, the second sealing member 27 can be used to seal the connection position between the protective part 2112 and the middle cover 2111, so as to ensure the sealing degree at the connection position between the protective part 2112 and the middle cover 2111, thereby preventing the gas outside the cavity a from entering the cavity a from the connection position, so as to ensure the independent environment inside the cavity a and ensure the normal operation of the radar 22 and other components inside the cavity a.

[0150] The heat dissipation effect mainly depends on the arrangement of components such as the heat exchanger 23 inside the cavity a. The heat exchanger 23 inside the shell 21 is introduced below.

[0151] In some embodiments, Figure 2 As shown, the outlet of the second heat exchange passage 232 faces the radar 22 .

[0152] In some examples, guide vanes are provided on the heat exchanger 23 , and the outlet of the second heat exchange channel 232 is directed toward the radar 22 by means of the guide vanes.

[0153] Of course, the guide plate may not be provided, and the outlet of the second heat exchange channel 232 may be directly facing the radar 22.

[0154] In this way, the low-temperature gas discharged from the outlet of the second heat exchange channel 232 can be blown directly toward the radar 22. During the blowing process, the low-temperature gas can take away the heat on the radar 22. That is to say, during the cooling process, not only the gas in the cavity a is directly cooled, but also the radar 22 is directly cooled, so that a better cooling effect can be achieved.

[0155] In some embodiments, Figure 2 , Fig. 9 As shown, the inlet center line A of the second heat exchange channel 232 intersects with the outlet center line B of the second heat exchange channel 232 .

[0156] The inlet of the second heat exchange channel 232 and the outlet of the second heat exchange channel 232 may be located at opposite sides of the heat exchanger 23. Alternatively, the inlet of the second heat exchange channel 232 and the outlet of the second heat exchange channel 232 may also be located at the same side of the heat exchanger 23.

[0157] In some examples, the angle formed by the intersection of the inlet centerline A of the second heat exchange channel 232 and the outlet centerline B of the second heat exchange channel 232 may be 50°, 60°, 70°, 90°, 100°, etc.

[0158] Through the above-mentioned arrangement, the airflow direction of the gas entering from the inlet of the second heat exchange channel 232 intersects with the airflow direction of the gas discharged from the outlet of the second heat exchange channel 232, so that the airflows in two directions can form a circulating airflow inside the cavity a, which can drive the gas inside the cavity a to flow, thereby making the gas temperature at different positions inside the cavity a uniform, thereby achieving a better cooling effect.

[0159] In some embodiments, Figure 2 As shown, the air inlet b is located on the windward side of the shell 21 , and the air outlet c is located on the non-windward side of the shell 21 .

[0160] It can be understood that the windward side of the shell 21 refers to the front side of the shell 21 when the aircraft body 1 is flying. The non-windward side of the shell 21 refers to any other side of the shell 21 except the windward side of the shell 21.

[0161] In some examples, the air outlet c is located on the leeward side of the shell 21, the leeward side of the shell 21 is opposite to the windward side, and the first heat exchange channel 231 extends along the arrangement direction of the windward side and the leeward side of the shell 21. In this way, during the flight of the aircraft body 1, the flow direction of the gas is consistent with the arrangement direction of the air inlet b, the first heat exchange channel 231, and the air outlet c, which can facilitate the gas to flow through the air inlet b, the first heat exchange channel 231 and the air outlet c, thereby reducing airflow losses and improving heat dissipation efficiency.

[0162] Exemplarily, when the shell 21 includes a cover body 211 and a sealing portion 212, and the cover body 211 includes a middle cover 2111 and a protective portion 2112, the air inlet b is located on the protective portion 2112 on the windward side of the middle cover 2111, and the air outlet c is located on the protective portion 2112 on the leeward side of the middle cover 2111.

[0163] Through the above arrangement, the pressure difference between the windward side and the non-windward side can be utilized to allow the gas outside the cavity a to flow through the first heat exchange channel 231. This does not require additional power for the gas flow in the first heat exchange channel 231, thereby reducing costs.

[0164] Of course, in other embodiments, a fan assembly may also be provided on the air flow channel of the first heat exchange channel 231 , so as to utilize the fan assembly to drive external air to flow through the first heat exchange channel 231 to achieve heat exchange.

[0165] In some embodiments, Fig. 9 As shown, the radar environment control device 2 further includes a guide pipe 28, the outlet of the guide pipe 28 is connected to the inlet of the second heat exchange channel 232, and the inlet of the guide pipe 28 is connected to the cavity a. Along the airflow direction in the guide pipe 28, the cross section of the guide pipe 28 gradually decreases.

[0166] In some examples, the fan 24 is disposed at the inlet of the guide duct 28 , so that the gas inside the cavity a can be better sucked into the guide channel 28 , facilitating the gas flow in the guide channel 28 and the second heat exchange channel 232 .

[0167] Through the above-mentioned arrangement, the gas inside the cavity a will enter the second heat exchange channel 232 through the guide pipe 28. Since the cross-section of the guide pipe 28 gradually decreases along the air flow direction in the guide pipe 28, the gas flow rate in the guide pipe 28 will gradually increase with the flow of the gas. In this way, the air flow rate entering the second heat exchange channel 232 will be enhanced, which can improve the heat exchange efficiency of the first heat exchange channel 231 and the second heat exchange channel 232.

[0168] In some embodiments, Fig.10 As shown, the radar environmental control device 2 further includes an airflow regulating device 29 , which is disposed at the inlet of the first heat exchange channel 231 and is used to regulate the conduction degree of the first heat exchange channel 231 .

[0169] In some examples, the airflow regulating device 29 includes a valve and a power component, and the power component is used to control the movement of the valve to adjust the opening of the inlet of the first heat exchange channel 231, thereby adjusting the gas flow rate passing through the inlet of the first heat exchange channel 231 to control the amount of gas entering the first heat exchange channel 231 per unit time.

[0170] Through the above-mentioned setting, the airflow regulating device 29 can adjust the gas flow rate entering the first heat exchange channel 231 from the air inlet b. In this way, when the heat exchange efficiency between the first heat exchange channel 231 and the second heat exchange channel 232 is too high, the conductivity of the first heat exchange channel 231 can be reduced, and the gas flow rate in the first heat exchange channel 231 can be reduced to reduce the heat exchange efficiency of the gas in the first heat exchange channel 231 and the second heat exchange channel 232, thereby reducing the cooling effect on the gas in the cavity a and components such as the radar 22.

[0171] When the heat exchange efficiency between the first heat exchange channel 231 and the second heat exchange channel 232 is too low, the conductivity of the first heat exchange channel 231 is increased, and the gas flow in the first heat exchange channel 231 is increased to improve the heat exchange efficiency of the gas in the first heat exchange channel 231 and the second heat exchange channel 232, and improve the cooling effect, so as to adapt to different cooling requirements.

[0172] On this basis, in some embodiments, the radar environmental control device 2 also includes a first temperature sensor, which is arranged in cavity a and is used to detect the temperature in cavity a. The first temperature sensor is electrically connected to the airflow regulating device 29, and the airflow regulating device 29 is used to adjust the conductivity of the first heat exchange channel 231 according to the detection result of the first temperature sensor.

[0173] In some examples, the airflow adjustment device 29 is electrically connected to the first temperature sensor through a controller.

[0174] In some examples, when the actual temperature detected by the first temperature sensor is greater than the first threshold, the airflow regulating device 29 increases the degree of conduction of the first heat exchange channel 231 to improve the heat exchange efficiency and the heat dissipation effect. When the actual temperature detected by the first temperature sensor is less than the first threshold, the airflow regulating device 29 reduces the degree of conduction of the first heat exchange channel 231 to reduce the heat exchange efficiency and the heat dissipation effect.

[0175] Through the above-mentioned setting, the first temperature sensor and the airflow regulating device 29 can cooperate with each other. The airflow regulating device 29 controls the action of the airflow regulating device 29 according to the detection result of the first temperature sensor to adjust the gas flow entering the first heat exchange channel 231, thereby adjusting the cooling effect. Such control is more intelligent and accurate.

[0176] Of course, the airflow adjustment device 29 can also be controlled based on experience to adjust the degree of conduction of the first heat exchange channel 231. For example, in different seasons, the degree of conduction of the first heat exchange channel 231 can be increased or decreased at certain intervals.

[0177] In some embodiments, Fig.11 As shown, the radar environment control device 2 also includes a second temperature sensor 30 and a third temperature sensor 31. The second temperature sensor 30 is arranged at the inlet of the second heat exchange channel 232, and is used to detect the temperature of the gas passing through the inlet of the second heat exchange channel 232; the second temperature sensor 30 is electrically connected to the fan 24. The third temperature sensor 31 is arranged at the outlet of the second heat exchange channel 232, and is used to detect the temperature of the gas passing through the outlet of the second heat exchange channel 232; the third temperature sensor 31 is electrically connected to the fan 24. The speed of the fan 24 is adjusted according to the temperature difference detected by the second temperature sensor 30 and the third temperature sensor 31.

[0178] It can be understood that the gas temperature at the inlet of the second heat exchange channel 232 is higher than the gas temperature at the outlet of the second heat exchange channel 232 .

[0179] In some examples, the radar environmental control device 2 also includes an electrical control box 32, and the fan 24, the second temperature sensor 30, and the third temperature sensor 31 are all electrically connected to the electrical control box 32. The electrical control box 32 is used to obtain the temperature values ​​obtained by the first temperature sensor and the second temperature sensor 30, thereby controlling the fan 24.

[0180] In some examples, when the actual difference between the temperatures detected by the second temperature sensor 30 and the third temperature sensor 31 is greater than the second threshold, the speed of the fan 24 is reduced to reduce the heat exchange efficiency and reduce the heat dissipation effect. When the actual difference between the temperatures detected by the second temperature sensor 30 and the third temperature sensor 31 is less than the second threshold, the speed of the fan 24 is increased to improve the heat exchange efficiency and improve the heat dissipation effect.

[0181] Through the above settings, the temperature difference between the gas at the inlet and outlet of the second heat exchange channel 232 can be determined based on the temperature difference detected by the second temperature sensor 30 and the third temperature sensor 31, thereby determining the heat exchange efficiency of the gas in the second heat exchange channel 232 and the first heat exchange channel 231. When the actual temperature difference detected by the second temperature sensor 30 and the third temperature sensor 31 is too large, the speed of the fan 24 is reduced to reduce the heat exchange efficiency and the heat dissipation effect. When the actual temperature difference detected by the second temperature sensor 30 and the third temperature sensor 31 is too small, the speed of the fan 24 is increased to improve the heat exchange efficiency and the heat dissipation effect. This is suitable for different cooling requirements.

[0182] In some embodiments, Figure 2 , Fig.10 As shown, the radar environment control device 2 further includes an air inlet duct 33 and / or an air outlet duct 34, the air inlet duct 33 is arranged in the cavity a, the air inlet end of the air inlet duct 33 is connected to the air inlet b, and the air outlet end of the air inlet duct 33 is connected to the inlet of the first heat exchange channel 231. And / or, the air outlet duct 34 is arranged in the cavity a, the air inlet end of the air outlet duct 34 is connected to the air outlet c, and the air outlet end of the air outlet duct 34 is connected to the outlet of the first heat exchange channel 231.

[0183] In some examples, the airflow adjustment device 29 may be disposed in the air inlet duct 33 to adjust the inlet opening of the first heat exchange channel 231 .

[0184] By setting at least one of the air inlet duct 33 and the air outlet duct 34, the heat exchanger 23 can be conveniently set at a suitable position in the cavity a, which facilitates the spatial layout of the heat exchanger 23, radar 22 and other components inside the cavity a, thereby improving the convenience of the layout.

[0185] In some embodiments, Fig.10 As shown, the air inlet end of the air inlet duct 33 surrounds the air inlet port b, and the end surface of the air inlet end of the air inlet duct 33 is closely connected to the inner wall surface of the cavity a.

[0186] In some examples, such as Fig.12As shown, a first groove 331 and a first protrusion 332 are provided between the end face of the air inlet end of the air inlet duct 33 and the inner wall surface of the cavity a, and the first groove 331 and the first protrusion 332 are both arranged around the air inlet b, one of the first groove 331 and the first protrusion 332 is located at the end face of the air inlet end of the air inlet duct 33, and the other of the first groove 331 and the first protrusion 332 is located on the inner wall surface of the cavity a, and the first protrusion 332 is inserted into the first groove 331. In this way, the air inlet end of the air inlet duct 33 can be connected to the housing 21 conveniently, thereby improving the convenience of installation.

[0187] In some examples, the air inlet end of the air inlet duct 33 is connected with a first positioning protrusion 333, which is arranged along the circumference of the air inlet b and abuts against the inner side of the air inlet b. In this way, when installing the air inlet duct 33, the air inlet end of the air inlet duct 33 and the center of the air inlet b can be located first, and then connected, which can improve the convenience and accuracy of installation.

[0188] Exemplarily, when a filter 35 is connected to the air inlet b, the first positioning protrusion 333 can be made to abut against the inner wall of the filter 35 .

[0189] Of course, the first positioning protrusion 333 may also abut against the inner wall of the air inlet b.

[0190] Through the above-mentioned arrangement, the sealing degree of the connection between the air inlet end of the air inlet duct 33 and the air inlet port b can be ensured, thereby preventing the gas outside the cavity a from entering the cavity a from the connection between the air inlet duct 33 and the air inlet port b, thereby preventing external water vapor from entering the cavity a, so as to ensure the normal operation of electronic components such as the radar 22 inside the cavity a and ensure their service life.

[0191] In other embodiments, Fig.13 As shown, the air outlet end of the air outlet duct 34 surrounds the air outlet c, and the end surface of the air outlet end of the air outlet duct 34 is closely connected to the inner wall surface of the cavity a.

[0192] In some examples, such as Fig.14 As shown, a second groove 341 and a second protrusion 342 are provided between the end surface of the outlet end of the air outlet duct 34 and the inner wall surface of the cavity a, and the second groove 341 and the second protrusion 342 are both arranged around the air outlet c, one of the second groove 341 and the second protrusion 342 is located at the end surface of the outlet end of the air outlet duct 34, and the other of the second groove 341 and the second protrusion 342 is located on the inner wall surface of the cavity a, and the second protrusion 342 is inserted into the second groove 341. In this way, the outlet end of the air outlet duct 34 can be connected to the housing 21 conveniently, thereby improving the convenience of installation.

[0193] In some examples, the outlet end of the air outlet duct 34 is connected with a second positioning protrusion 343, which is arranged along the circumference of the air outlet c and abuts against the inner side of the air outlet c. In this way, when installing the air outlet duct 34, the center of the air outlet end of the air outlet duct 34 and the air inlet b can be located first, and then connected, which can improve the convenience and accuracy of installation.

[0194] Exemplarily, when a filter 35 is connected to the air outlet c, the second positioning protrusion 343 can be made to abut against the inner wall of the filter 35 .

[0195] Of course, the second positioning protrusion 343 may also abut against the inner wall of the air outlet c.

[0196] Through the above-mentioned arrangement, the sealing degree of the connection between the air outlet end of the air outlet duct 34 and the air outlet c can be ensured, thereby preventing the gas outside the cavity a from entering the cavity a from the connection between the air outlet duct 34 and the air outlet c, thereby preventing external water vapor from entering the cavity a, so as to ensure the normal operation of electronic components such as the radar 22 inside the cavity a and ensure their service life.

[0197] In other embodiments, Fig.10 , Fig.13 As shown, the air inlet end of the air inlet duct 33 surrounds the air inlet b, and the end surface of the air inlet end of the air inlet duct 33 is connected to the inner wall of the cavity a. The air outlet end of the air outlet duct 34 surrounds the air outlet c, and the end surface of the air outlet end of the air outlet duct 34 is connected to the inner wall of the cavity a.

[0198] In this way, the sealing degree of the connection between the air inlet end of the air inlet duct 33 and the air inlet b can be ensured; and / or, the sealing degree of the connection between the air outlet end of the air outlet duct 34 and the air outlet c can be ensured, thereby preventing the gas outside the cavity a from entering the cavity a from the connection between the air inlet duct 33 and the air inlet b, preventing the gas outside the cavity a from entering the cavity a from the connection between the air outlet duct 34 and the air outlet c, and preventing water vapor from entering the cavity a, thereby ensuring the normal operation of electronic components such as the radar 22 inside the cavity a and ensuring their service life.

[0199] In some embodiments, Fig.10 , Fig.13 As shown, a filter 35 is provided at at least one of the air inlet b and the air outlet c.

[0200] In some examples, the filter 35 includes a frame and a filter. The filter is disposed in the frame. The frame is connected to the housing 21. The frame provides support for the filter, and the filter filters debris.

[0201] By setting up the filter 35, the filter 35 can filter the debris in the gas entering the first heat exchange channel 231, and can reduce the probability of external debris entering the cavity a from at least one of the air inlet b and the air outlet c, thereby reducing the probability of the first heat exchange channel 231 being blocked, thereby ensuring the normal operation of the heat exchanger 23.

[0202] On this basis, in some embodiments, the filter net 35 is connected to the shell 21 , and the thickness of the filter net 35 is greater than the thickness of the shell 21 .

[0203] It can be understood that the thickness of the filter 35 at the air inlet b refers to the thickness of the filter 35 along the center line of the air inlet b. Similarly, the thickness of the filter 35 at the air outlet c refers to the thickness of the filter 35 along the center line of the air outlet c.

[0204] Through the above arrangement, the thickness of the filter 35 is greater than the thickness of the shell 21. Thus, even if there are filter holes on the filter 35, the thickness of the filter 35 can still be increased to compensate for the structural strength reduced by the filter holes, thereby ensuring the structural strength of the filter 35 and ensuring the structural strength of the shell 21 at at least one of the air inlet b and the air outlet c after the filter 35 is connected to at least one of the air inlet b and the air outlet c, thereby extending the service life of the shell 21.

[0205] The above are only preferred embodiments of the present application, and are not intended to limit the patent scope of the present application. Any equivalent structure or equivalent process transformation made using the contents of the present application specification and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present application.

Claims

1. A radar environment control device, characterized in that: include: A shell having a cavity inside, and an air inlet and an air outlet connected to the cavity are formed on the shell; A radar is disposed in the cavity; A heat exchanger is arranged in the cavity, and a first heat exchange channel and a second heat exchange channel that are independent of each other are formed on the heat exchanger; the inlet of the first heat exchange channel is communicated with the air inlet, and the outlet of the first heat exchange channel is communicated with the air outlet, so that the low-temperature gas outside the cavity can flow through the first heat exchange channel through the air inlet and the air outlet; the inlet and outlet of the second heat exchange channel are both communicated with the inside of the cavity; The fan is arranged in the cavity and located on the ventilation path of the second heat exchange channel.

2. The radar environment control device according to claim 1, characterized in that: An outlet of the second heat exchange channel faces the radar.

3. The radar environment control device according to claim 1, characterized in that: The inlet centerline of the second heat exchange channel intersects with the outlet centerline of the second heat exchange channel.

4. The aircraft according to claim 1, characterized in that: The air inlet is located on the windward side of the shell, and the air outlet is located on the non-windward side of the shell.

5. The radar environment control device according to claim 1, characterized in that: It also includes a guide pipe, the outlet of the guide pipe is connected to the inlet of the second heat exchange channel, and the inlet of the guide pipe is connected to the cavity; along the airflow direction in the guide pipe, the cross-section of the guide pipe gradually decreases.

6. The radar environment control device according to claim 1, characterized in that: Also includes: An airflow regulating device is arranged at the inlet of the first heat exchange channel and is used to adjust the conductance of the first heat exchange channel.

7. The radar environment control device according to claim 6, characterized in that: Also includes: A first temperature sensor is disposed in the cavity and is used to detect the temperature in the cavity. The first temperature sensor is electrically connected to the airflow regulating device, and the airflow regulating device is used to adjust the conduction degree of the first heat exchange channel according to the detection result of the first temperature sensor.

8. The radar environment control device according to claim 1, characterized in that: Also includes: a second temperature sensor, disposed at the inlet of the second heat exchange channel, for detecting the temperature of the gas passing through the inlet of the second heat exchange channel; the second temperature sensor is electrically connected to the fan; a third temperature sensor, disposed at the outlet of the second heat exchange channel, for detecting the temperature of the gas passing through the outlet of the second heat exchange channel; the third temperature sensor is electrically connected to the fan; The rotation speed of the fan is adjusted according to the temperature difference detected by the second temperature sensor and the third temperature sensor.

9. The radar environment control device according to claim 1, characterized in that: Also includes: an air inlet duct disposed in the cavity, the air inlet end of the air inlet duct being connected to the air inlet, and the air outlet end of the air inlet duct being connected to the inlet of the first heat exchange channel; and / or, An air outlet duct is arranged in the cavity, an air inlet end of the air outlet duct is connected to the air outlet, and an air outlet end of the air outlet duct is connected to the outlet of the first heat exchange channel.

10. The radar environment control device according to claim 9, characterized in that: The air inlet end of the air inlet duct surrounds the air inlet port, and the end surface of the air inlet end of the air inlet duct is in contact with the inner wall surface of the cavity; and / or, The air outlet end of the air outlet duct surrounds the air outlet, and the end surface of the air outlet end of the air outlet duct is in close contact with the inner wall surface of the cavity.

11. The radar environment control device according to claim 1, characterized in that: A filter is provided at at least one of the air inlet and the air outlet.

12. The radar environment control device according to claim 11, characterized in that: The filter screen is connected to the shell, and the thickness of the filter screen is greater than the thickness of the shell.

13. The radar environment control device according to any one of claims 1 to 12, characterized in that: The housing comprises: A cover body formed with an opening; The blocking portion blocks the opening to form the cavity, and the blocking portion is connected to the cover body.

14. The radar environment control device according to claim 13, characterized in that: Also includes: The first sealing member is arranged between the cover body and the blocking portion and is arranged along the circumference of the opening to seal the cover body and the blocking portion.

15. The radar environment control device according to claim 13, characterized in that: The radar environment control device also includes: A connecting piece is arranged at the opening and along the circumference of the opening. The connecting piece is at least partially located on one side of the cover body in the thickness direction and is connected to the cover body. The connecting piece is connected to the blocking portion.

16. The radar environment control device according to claim 13, characterized in that: The cover body comprises: A protection part connected to the blocking part; The middle cover, the opening is at least partially located on the middle cover, and the windward side and the leeward side of the middle cover are respectively connected to the protective part.

17. The radar environment control device according to claim 16, characterized in that: The middle cover is overlapped on a side surface of the protection portion away from the blocking portion.

18. The radar environment control device according to claim 16, characterized in that: The cavity is provided at the connection position between the middle cover and the protective part; the radar environmental control device also includes: The second sealing member is disposed between the protection portion and the middle cover to seal the protection portion and the middle cover.

19. An aircraft, characterized in that: include: Aircraft body; The radar environment control device is the radar environment control device according to any one of claims 1 to 18, and the radar environment control device is connected to the aircraft body.

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