Skin structure, cooling regulation system and cooling regulation method

Abstract

The present invention relates to the field of cooling technology, and provides a skin structure, a cooling regulation system, and a cooling regulation method. The above-mentioned skin structure includes: an annular heat exchanger, a first pipeline, and a second pipeline. The annular heat exchanger is used to be mounted on the outside of the aircraft; the first end of the first pipeline is used to communicate with the heat source of the aircraft, and the second end of the first pipeline is connected to the annular heat exchanger; the first end of the second pipeline is connected to the annular heat exchanger, and the second end of the second pipeline is used to communicate with the heat source; wherein the heat source, the first pipeline, the annular heat exchanger, and the second pipeline form a circulation loop, and the annular heat exchanger is used to exchange heat with the liquid in the heat source. The above-mentioned skin structure, by mounting the annular heat exchanger on the outside of the aircraft, designs the annular heat exchanger as the skin of the aircraft through an integrated design, thereby reducing the space occupied inside the aircraft. At the same time, the annular heat exchanger does not need to be equipped with special refrigeration equipment to cool the cooling medium, thereby reducing the energy consumption of the aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of cooling equipment, and in particular to a skin structure, a cooling adjustment system and a cooling adjustment method. Background Art

[0002] The cooling system is an important functional guarantee system that dissipates the heat of a moving platform such as an aircraft or an airplane into the environment. Traditional cooling systems introduce external cooling media into the cooling system through pipes, and then cool the heat source through a cooler. However, the existing cooling system pipes and coolers take up a large space, making it difficult to miniaturize the aircraft or airplane. Summary of the Invention

[0003] The present invention provides a skin structure, a cooling adjustment system and a cooling adjustment method, which are used to solve the defect in the prior art that the cooling system occupies a large space.

[0004] The present invention provides a skin structure, comprising: an annular heat exchanger for being mounted on the outside of an aircraft; a first pipeline, wherein the first end of the first pipeline is used to communicate with the heat source of the aircraft, and the second end of the first pipeline is connected to the annular heat exchanger; a second pipeline, wherein the first end of the second pipeline is connected to the annular heat exchanger, and the second end of the second pipeline is used to communicate with the heat source; wherein the heat source, the first pipeline, the annular heat exchanger and the second pipeline form a circulation loop, and the annular heat exchanger is used to exchange heat with the liquid in the heat source.

[0005] According to a skin structure provided by the present invention, the annular heat exchanger includes: a header, which is used to be mounted on the outside of the aircraft, part of the header is connected to the first pipeline, and the remaining part of the header is connected to the second pipeline; an annular pipe, which is mounted on the outside of the header, the annular pipe includes an inner wall and an outer wall, a first flow channel is formed between the inner wall and the outer wall, and a cavity is provided between the annular pipe and the header, and the cavity is filled with a cooling medium; a plurality of groups of heat exchange tubes are arranged in the cavity and are arranged in a ring along the circumferential surface of the header, and the header is connected to the annular pipe through the heat exchange tubes.

[0006] According to a skin structure provided by the present invention, the annular heat exchanger further includes: a plurality of elastic fins, and two adjacent heat exchange tubes in each group of the heat exchange tubes are connected by the elastic fins to divide the cavity into a plurality of second flow channels.

[0007] According to a skin structure provided by the present invention, the annular heat exchanger also includes: multiple driving mechanisms, which are arranged in the second flow channel, each of the driving mechanisms is respectively arranged between two oppositely arranged elastic fins, and the driving mechanisms on both sides of the multiple elastic fins located on the same straight line are staggered, wherein the driving mechanism is used to drive the elastic fins to produce an offset relative to the heat exchange tube to adjust the flow direction of the cooling medium in the second flow channel, and thereby adjust the heat transfer area between the cooling medium and the heat exchange tube and the convective heat transfer coefficient between the cooling medium and the heat exchange tube.

[0008] According to a skin structure provided by the present invention, the annular heat exchanger further includes: a plurality of fixing plates arranged in the cavity, the fixing plates and the heat exchange tubes being spaced apart, and the two ends of the driving mechanism being respectively connected to the fixing plates and the elastic fins.

[0009] According to a skin structure provided by the present invention, the header includes: a first header and a second header, the first header and the second header are arranged opposite to each other, the first header and the second header are semicircular ring headers, wherein the first header is connected to the first pipeline, and the second header is connected to the second pipeline.

[0010] The present invention also provides a cooling and regulating system, comprising a heat source and the skin structure as described above, wherein the heat source is connected to the skin structure.

[0011] The cooling and regulating system provided according to the present invention further includes: a heat source sensing unit, which is arranged in the heat source, and the heat source sensing unit is used to detect the measured temperature of the liquid flowing back to the heat source through the second pipeline; a controller, which is communicatively connected to the heat source sensing unit, and the controller is used to control the driving mechanism to drive the elastic fin to produce an offset relative to the heat exchange tube according to the measured temperature and the set temperature.

[0012] The cooling and regulating system provided according to the present invention further includes: an environmental sensing unit, which is arranged on the surface of the annular pipe, and the environmental sensing unit is used to detect the incoming flow velocity and incoming flow temperature outside the skin structure; the heat source sensing unit is also used to detect the thermal load inside the heat source, and the controller is provided with a characteristic database, and the controller is used to obtain the target value of the offset of the elastic fin according to the incoming flow velocity, the incoming flow temperature and the thermal load in combination with the characteristic database, and control the driving mechanism to drive the actual offset of the elastic fin to reach the target value, wherein the characteristic database is a data set composed of relationship curves corresponding to the offset and the incoming flow velocity and incoming flow temperature under different thermal loads.

[0013] The present invention also provides a method for cooling regulation using the cooling regulation system as described above, comprising: obtaining the measured temperature of the liquid flowing through the second pipe and returning to the heat source; when the measured temperature is greater than the set temperature, controlling the driving mechanism to increase the offset of the elastic fin; when the measured temperature is less than the set temperature, controlling the driving mechanism to decrease the offset of the elastic fin.

[0014] The skin structure provided by the present invention, by arranging an annular heat exchanger on the outside of the aircraft, and designing the annular heat exchanger as the skin of the aircraft through an integrated design, reduces the space occupied inside the aircraft, reduces the volume of the aircraft, and realizes miniaturization of the aircraft; at the same time, the annular heat exchanger relies on seawater flushing to cool down, and there is no need to set up special refrigeration equipment to cool the cooling medium, thereby reducing the energy consumption and cost of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions in the present invention or the prior art, a brief introduction is given below to the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0016] Figure 1 It is a structural schematic diagram of the skin structure provided by the present invention;

[0017] Figure 2 yes Figure 1 A local enlarged view of the position A shown in FIG;

[0018] Figure 3 is a schematic diagram of the flow field in the second flow channel under natural conditions;

[0019] Figure 4 is a schematic diagram of the flow field in the second flow channel under the driving state;

[0020] Figure 5 It is a structural schematic diagram of the cooling and regulating system provided by the present invention;

[0021] Figure 6 This is a graph showing the relationship between the deflection of the elastic fin and the incoming flow velocity and temperature under a specific heat load;

[0022] Figure 7 This is a graph showing the relationship between the offset of the elastic fin and the incoming flow velocity and temperature under different heat loads;

[0023] Figure 8 This is one of the flow charts of the cooling adjustment method provided by the present invention;

[0024] Figure 9This is the second flow chart of the cooling adjustment method provided by the present invention;

[0025] Reference numerals:

[0026] 10: Annular heat exchanger; 20: Heat source; 30: First pipeline; 40: Second pipeline; 50: Heat source sensing unit; 61: Data acquisition module; 62: Central processing unit; 63: Characteristic database; 71: Detection data transmission network; 72: Control data transmission network; 101: First header; 102: Second header; 103: Annular pipeline; 104: Heat exchange tube; 105: Elastic fin; 106: Driving mechanism; 107: Fixed plate; 108: Second flow channel; 109: Environmental sensing unit; 200: Aircraft. DETAILED DESCRIPTION

[0027] To make the objectives, technical solutions, and advantages of the present invention more clear, the technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the embodiments described are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts shall fall within the scope of protection of the present invention.

[0028] The features of the terms "first" and "second" in the description and claims of the present invention may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, the meaning of "plurality" is two or more.

[0029] The following combination Figures 1-9 The skin structure, cooling regulation system and cooling regulation method of the present invention are described.

[0030] like Figure 1 As shown, in an embodiment of the present invention, the skin structure includes an annular heat exchanger 10, a first pipeline 30, and a second pipeline 40. The annular heat exchanger 10 is configured to be mounted on the exterior of an aircraft 200. The first end of the first pipeline 30 is configured to communicate with the heat source 20 of the aircraft 200, and the second end of the first pipeline 30 is configured to communicate with the annular heat exchanger 10. The first end of the second pipeline 40 is configured to communicate with the annular heat exchanger 10, and the second end of the second pipeline 40 is configured to communicate with the heat source 20. The heat source 20, the first pipeline 30, the annular heat exchanger 10, and the second pipeline 40 form a circulation loop, and the annular heat exchanger 10 is configured to exchange heat with the liquid in the heat source 20.

[0031] Specifically, in this embodiment, the annular heat exchanger 10 is sheathed on the exterior of the aircraft 200, conforming to the aircraft 200 and thus referred to as a skin structure. The higher-temperature liquid within the heat source 20 enters the annular heat exchanger 10 through a first pipe 30, where it undergoes heat exchange with the coolant within the annular heat exchanger 10. The cooled liquid then enters the heat source 20 through a second pipe 40. The heated liquid then enters the annular heat exchanger 10 again through the first pipe 30 for heat exchange. The circulation loop formed by the heat source 20, the first pipe 30, the annular heat exchanger 10, and the second pipe 40 continuously cools the higher-temperature liquid within the heat source 20, thereby ensuring the heat dissipation requirements of the aircraft. Furthermore, since the annular heat exchanger 10 is sheathed on the exterior of the aircraft 200, the coolant within the annular heat exchanger 10 can exchange heat with the seawater under the flushing of seawater, continuously cooling the coolant within the annular heat exchanger 10 without requiring additional refrigeration equipment, thereby reducing the energy consumption of the aircraft 200.

[0032] The skin structure provided by the embodiment of the present invention, by installing an annular heat exchanger on the outside of the aircraft, and designing the annular heat exchanger as the skin of the aircraft through an integrated design, reduces the space occupied inside the aircraft, reduces the volume of the aircraft, and realizes miniaturization of the aircraft; at the same time, the annular heat exchanger relies on seawater flushing to cool down, and there is no need to set up special refrigeration equipment to cool the cooling medium, thereby reducing the energy consumption and cost of the aircraft.

[0033] like Figure 1 As shown, in an embodiment of the present invention, an annular heat exchanger 10 includes a header, an annular pipe 103, and multiple groups of heat exchange tubes 104. The header is designed to be mounted externally of a vehicle 200. Part of the header is connected to the first pipe 30, and the remaining portion is connected to the second pipe 40. The annular pipe 103 is mounted externally of the header and includes an inner wall and an outer wall, with a first flow channel formed between the inner and outer walls. A cavity is defined between the annular pipe 103 and the header, and the cavity is filled with a cooling medium. Multiple groups of heat exchange tubes 104 are arranged in an annular manner within the cavity. The multiple heat exchange tubes in each group 104 are arranged along the length of the vehicle 200. The header is connected to the annular pipe 103 via the heat exchange tubes 104.

[0034] Specifically, in this embodiment, the header is an annular pipe, partially connected to the first pipe 30 and partially connected to the second pipe 40. Multiple rows of heat exchange tubes 104 are arranged along the outer surface of the header along its circumference. Each heat exchange tube 104 is connected to the header and the annular pipe 103 at both ends. The higher-temperature liquid within the heat source 20 enters the heat exchange tubes 104 through the first pipe 30, exchanges heat with the cooling medium outside the heat exchange tubes 104, and then, after cooling, enters the annular pipe 103. Then, it passes through the heat exchange tubes 104 into the second pipe 40, and finally enters the heat source 20.

[0035] Optionally, in an embodiment of the present invention, the header may be a complete annular pipe with two partitions provided in the annular pipe to separate the first flow channel into two flow channels, wherein one flow channel is connected to the first pipeline 30 and the other flow channel is connected to the second pipeline 40.

[0036] Optionally, in another embodiment of the present invention, the header includes: a first header 101 and a second header 102, the first header 101 and the second header 102 are arranged opposite to each other, and the first header 101 and the second header 102 are both semicircular ring headers, wherein the first header 101 is connected to the first pipeline 30, and the second header 102 is connected to the second pipeline 40.

[0037] Furthermore, if Figure 1 and Figure 2 As shown, in an embodiment of the present invention, the annular heat exchanger 10 further includes a plurality of elastic fins 105 , and two adjacent heat exchange tubes 104 in each group of heat exchange tubes 104 are connected by the elastic fins 105 to separate the cavity into a plurality of second flow channels 108 .

[0038] Specifically, the multiple heat exchange tubes 104 within each group of heat exchange tubes 104 are arranged along the length of the vehicle 200. Adjacent heat exchange tubes 104 are connected by elastic fins 105, thereby dividing the cavity between the header and the annular duct 103 into multiple second flow channels 108. Each second flow channel 108 is filled with a cooling medium, which exchanges heat with the liquid within the heat exchange tubes 104 to cool the liquid. Furthermore, in an embodiment of the present invention, the elastic fins 105 are thermally conductive, allowing heat from the liquid within the heat exchange tubes 104 to be transferred to the elastic fins 105 through the heat exchange tubes 104, where it is then absorbed by the cooling medium, thereby assisting the heat exchange tubes 104 in further cooling the liquid.

[0039] like Figure 3 and Figure 4 As shown, in an embodiment of the present invention, the annular heat exchanger further includes a plurality of driving mechanisms 106, each driving mechanism 106 is respectively arranged between two oppositely arranged elastic fins 105, and the driving mechanisms 106 on both sides of the plurality of elastic fins 105 located on the same straight line are staggered, wherein the driving mechanism is used to drive the elastic fins 105 to produce an offset relative to the heat exchange tube 104, so as to adjust the flow direction of the cooling medium in the second flow channel 108, and thereby adjust the heat transfer area between the cooling medium and the heat exchange tube 104 and the convective heat transfer coefficient between the cooling medium and the heat exchange tube 104.

[0040] Specifically, the elastic fin 105 is elastic and can be deformed under the action of the driving mechanism 106, that is, it is offset relative to the heat exchange tube 104. When the elastic fin 105 is deformed, the flow direction of the cooling medium in the second flow channel 108 will change. Specifically, Figure 4 As shown, when the elastic fins 105 are bent, the heat transfer area between the cooling medium and the heat exchange tube 104 is increased. At the same time, the disturbance of the cooling medium in the second flow channel 108 is enhanced, increasing the vortex turbulence intensity, thereby improving the heat transfer capacity of the heat exchange tube 104. Furthermore, the more the elastic fins 105 are bent, that is, the greater the offset, the larger the heat transfer area between the cooling medium and the heat exchange tube 104. At the same time, the greater the vortex turbulence intensity of the cooling medium, the greater the heat transfer coefficient between the cooling medium and the heat exchange tube 104, and the greater the heat transfer capacity of the heat exchange tube 104. In other words, by adjusting the offset of the elastic fins 105, the heat transfer capacity of the heat exchange tube 104 can be adjusted, thereby further improving the cooling effect of the skin structure.

[0041] Furthermore, in an embodiment of the present invention, the driving mechanisms 106 on both sides of the multiple elastic fins 105 located on the same straight line are staggered to ensure that there is only one driving mechanism 106 on both sides of each elastic fin 105, so that the elastic fins 105 can deform freely and produce a larger offset.

[0042] Optionally, in an embodiment of the present invention, the driving mechanism 106 may be a telescopic member, and the offset of the elastic fin 105 may be adjusted by controlling the telescopic member to extend or retract.

[0043] The skin structure provided in an embodiment of the present invention, by providing a driving mechanism and elastic fins, can adjust the offset of the elastic fins according to the temperature of the liquid flowing back to the heat source, and further adjust the heat transfer area and convective heat transfer coefficient between the cooling medium and the heat exchange tube to improve the heat exchange capacity of the heat exchange tube.

[0044] Furthermore, if Figure 1 As shown, in an embodiment of the present invention, the annular heat exchanger 10 further includes a plurality of fixing plates 107. The plurality of fixing plates 107 are disposed in the cavity, and the fixing plates 107 are spaced apart from the heat exchange tubes 104. The two ends of the driving mechanism 106 are respectively connected to the fixing plates 107 and the elastic fins 105.

[0045] Specifically, in this embodiment, multiple fixed plates 107 are arranged in a ring along the circumference of the header, with a group of heat exchange tubes 104 disposed between two adjacent fixed plates 107. One end of the drive mechanism 106 is connected to the fixed plates 107, and the other end is connected to the elastic fins 105. In this embodiment, the fixed plates 107 are rigid. When the drive mechanism 106 is extended or retracted, the elastic fins 105 are deformed while the fixed plates 107 remain unchanged. This causes the flow direction of the cooling medium to bend and distort within the second flow channel 108, increasing the turbulent eddy flow intensity of the cooling medium and thereby increasing the heat transfer area and convective heat transfer coefficient between the heat exchange tubes 104 and the cooling medium.

[0046] An embodiment of the present invention also provides a cooling and regulating system, including a heat source 20 and a skin structure, wherein the annular heat exchanger 10 of the skin structure is mounted on the outside of the aircraft 200, and the two ends of the first pipeline 30 of the skin structure are respectively connected to the annular heat exchanger and the heat source 20, and the two ends of the second pipeline 40 of the skin structure are respectively connected to the annular heat exchanger and the heat source 20.

[0047] Specifically, in this embodiment, the annular heat exchanger 10 is sheathed on the exterior of the aircraft 200, conforming to the aircraft 200 and thus referred to as a skin structure. The higher-temperature liquid within the heat source 20 enters the annular heat exchanger 10 through a first pipe 30, where it undergoes heat exchange with the coolant within the annular heat exchanger 10. The cooled liquid then enters the heat source 20 through a second pipe 40. The heated liquid then enters the annular heat exchanger 10 again through the first pipe 30 for heat exchange. The circulation loop formed by the heat source 20, the first pipe 30, the annular heat exchanger 10, and the second pipe 40 continuously cools the higher-temperature liquid within the heat source 20, thereby ensuring the heat dissipation requirements of the aircraft. Furthermore, since the annular heat exchanger 10 is sheathed on the exterior of the aircraft 200, the coolant within the annular heat exchanger 10 can exchange heat with the seawater under the flushing of seawater, continuously cooling the coolant within the annular heat exchanger 10 without requiring additional refrigeration equipment, thereby reducing the energy consumption of the aircraft 200.

[0048] The cooling and regulating system provided by the embodiment of the present invention arranges a skin structure and lays an annular heat exchanger on the outer surface of the aircraft. The annular heat exchanger is designed as the skin of the aircraft through an integrated design, thereby reducing the space occupied inside the aircraft, reducing the volume of the aircraft, and miniaturizing the aircraft. At the same time, the annular heat exchanger relies on seawater flushing to cool down, and there is no need to set up special refrigeration equipment to cool the cooling medium, thereby reducing the energy consumption and cost of the aircraft.

[0049] like Figure 5As shown, in an embodiment of the present invention, the cooling and regulating system further includes a heat source sensing unit 50 and a controller. The heat source sensing unit 50 is disposed within the heat source 20 and is configured to detect the actual temperature of the liquid flowing back into the heat source 20 via the second pipeline 40. The controller is communicatively connected to the heat source sensing unit 50 and is configured to control the drive mechanism 106 to drive the elastic fins 105 to offset relative to the heat exchange tubes 104 based on the actual temperature detected by the heat source sensing unit 50 and a set temperature.

[0050] Specifically, in this embodiment, the controller includes a data acquisition module 61 and a central processing unit 62. The heat source sensing unit 50 detects the measured temperature of the liquid flowing through the second pipeline 40 and returning to the heat source 20, and sends the detected measured temperature to the data acquisition module 61 via the detection data transmission network 71. The data acquisition module 61 sends the detected measured temperature to the central processing unit 62 via the control data transmission network 72. The central processing unit 62 outputs a control instruction to the drive mechanism 106 based on the detected measured temperature and the preset set temperature. The drive mechanism 106 drives the offset of the elastic fin 105 to change, so as to adjust the heat transfer area and convective heat transfer coefficient between the cooling medium and the heat exchange tube 104, and further adjust the heat exchange capacity of the heat exchange tube 104, so as to adjust the temperature of the liquid in the heat exchange tube 104, and further adjust the measured temperature of the liquid flowing back to the heat source 20, so that the measured temperature is equal to the set temperature.

[0051] Furthermore, in an embodiment of the present invention, the heat source sensing unit 50 can also be used to detect the heat load within the heat source 20. Furthermore, the heat source sensing unit 50 is equipped with multiple thermometers. One thermometer is located at the connection point between the second pipe 40 and the heat source 20 to detect the actual temperature of the return water, and another thermometer is located within the heat source 20 to detect the actual temperature of the outlet water within the heat source 20. The heat source sensing unit 50 also has a calculation function, which can calculate the heat load of the heat source 20 based on the measured temperature of the return water and the measured temperature of the outlet water.

[0052] The cooling regulation system provided by the embodiment of the present invention, by setting a heat source sensing unit, a controller and a skin structure, can control the driving mechanism to drive the elastic fins to deform according to the actual measured temperature of the liquid returning to the heat source and the preset set temperature, so as to adjust the heat exchange capacity of the heat exchange tube, and then adjust the actual temperature of the return water so that the actual temperature of the return water reaches the set temperature, thereby realizing adaptive adjustment of the cooling capacity of the cooling system and the operating conditions of the aircraft.

[0053] Furthermore, in an embodiment of the present invention, the cooling and regulating system further includes an environmental sensing unit 109. The environmental sensing unit 109 is disposed on the surface of the annular duct 103 and is configured to detect the incoming flow velocity and temperature from outside the skin structure. The controller is configured to include a characteristic database. The controller is configured to determine a target offset value for the elastic fin 105 based on the heat load detected by the heat source sensing unit 50, the incoming flow velocity and temperature detected by the environmental sensing unit 109, and the characteristic database, and to control the drive mechanism 106 to drive the actual offset of the elastic fin 105 to the target value.

[0054] Specifically, the environment sensing unit 109 is used to detect the incoming flow velocity and incoming flow temperature outside the skin structure. Figure 6 The figure shows the relationship between the incoming flow velocity, the incoming flow temperature and the offset of the elastic fin 105 when the heat load of the heat source 20 is constant. Specifically, the greater the incoming flow velocity and the higher the incoming flow temperature, the greater the offset, so that the measured return water temperature is equal to the set return water temperature. Figure 7 As shown in FIG, when the heat load is different, the adjustment amount of the offset is also different. Further, in the embodiment of the present invention, a characteristic database 63 is provided in the controller, and the characteristic database 63 is based on Figure 7 The relationship diagram shown in the figure is a data set consisting of the relationship curves of the offset, incoming flow velocity and incoming flow temperature under different heat loads. Figure 9 As shown, the environmental sensing unit 109 sends the detected incoming flow velocity and incoming flow temperature on the surface of the skin structure to the controller, and the heat source sensing unit 50 sends the detected heat load to the controller. The controller searches for the offset corresponding to the three data in the characteristic database as the target value, and then controls the extension and contraction amount of the driving mechanism 106 so that the actual offset of the elastic fin 105 directly reaches the target value.

[0055] The cooling and regulating system provided in an embodiment of the present invention can sense changes in the incoming flow velocity, incoming flow temperature and heat load inside the heat source by setting a controller, a heat source sensing unit and an environment sensing unit, and then adjust the offset of the elastic fins according to the changes to achieve adaptive adjustment of the cooling and regulating system to the aircraft working environment, which not only meets the heat dissipation requirements of the aircraft, but also reduces the energy consumption of the cooling and regulating system.

[0056] like Figure 8 As shown, an embodiment of the present invention further provides a method for performing cooling regulation using a cooling regulation system, which specifically includes the following steps:

[0057] Step 01: Obtain the measured temperature of the liquid flowing through the second pipe and returning to the heat source 20; Step 02: When the measured temperature is greater than the set temperature, control the drive mechanism 106 to increase the offset of the elastic fin 105; when the measured temperature is less than the set temperature, control the drive mechanism to decrease the offset of the elastic fin 105.

[0058] Specifically, in this embodiment, the elastic fins 105 have a certain offset in the initial state. The higher-temperature liquid within the heat source 20 enters the first header 101 through the first pipeline 30, then enters the heat exchange tubes 104. After heat exchange with the cooling medium within the heat exchange tubes 104, the cooled liquid enters the annular conduit 103 and then enters the heat source 20 via the heat exchange tubes 104, the second header 102, and the second pipeline 40. The heat source sensing unit 50 detects the actual temperature of the liquid entering the heat source 20 and transmits this temperature to the data acquisition module 61. The data acquisition module 61 transmits the data to the central processing unit 62, which compares the measured temperature with the set temperature. If the measured temperature is greater than the set temperature, it indicates that the heat exchange capacity of the heat exchange tubes 104 is poor. In this case, the offset of the elastic fins 105 needs to be increased to increase the heat transfer area and convective heat transfer coefficient between the cooling medium and the heat exchange tubes 104, thereby further reducing the liquid temperature and thus the measured temperature. If the measured temperature is lower than the set temperature, it indicates that the heat exchange capacity of the heat exchange tube 104 is relatively strong. In this case, the offset of the elastic fins 105 can be reduced to reduce the heat transfer area and convection heat transfer coefficient between the cooling medium and the heat exchange tube 104, thereby reducing the heat exchange capacity of the heat exchange tube 104 and making the measured temperature equal to the set temperature.

[0059] The cooling adjustment method provided in an embodiment of the present invention can achieve adaptive adjustment of the heat exchange capacity of the skin structure and the aircraft working environment by adjusting the offset size of the elastic fins, which not only meets the heat dissipation requirements of the aircraft, but also reduces the energy consumption of the cooling adjustment system.

[0060] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A skin structure, characterized in that: include: An annular heat exchanger is used to be installed on the outside of the aircraft; a first pipeline, wherein a first end of the first pipeline is used to communicate with a heat source of the aircraft, and a second end of the first pipeline is communicated with the annular heat exchanger; a second pipeline, wherein a first end of the second pipeline is in communication with the annular heat exchanger, and a second end of the second pipeline is in communication with the heat source; The heat source, the first pipeline, the annular heat exchanger and the second pipeline form a circulation loop, and the annular heat exchanger is used to perform heat exchange with the liquid in the heat source; The annular heat exchanger comprises: a header tank, configured to be sleeved on the exterior of the aircraft, wherein a portion of the header tank is in communication with the first pipeline, and a remaining portion of the header tank is in communication with the second pipeline; an annular pipe, sleeved on the outside of the header, the annular pipe comprising an inner wall and an outer wall, a first flow channel formed between the inner wall and the outer wall, a cavity between the annular pipe and the header, the cavity being filled with a cooling medium; A plurality of groups of heat exchange tubes are disposed in the cavity and arranged in an annular shape along the circumferential surface of the header, and the header is connected to the annular pipeline through the heat exchange tubes; a plurality of elastic fins, wherein two adjacent heat exchange tubes in each group of the heat exchange tubes are connected by the elastic fins, so as to divide the cavity into a plurality of second flow channels; A plurality of drive mechanisms are arranged in the second flow channel, each of the drive mechanisms is respectively arranged between two oppositely arranged elastic fins, and the drive mechanisms on both sides of the plurality of elastic fins located on the same straight line are staggered. In which, the driving mechanism is used to drive the elastic fin to produce an offset relative to the heat exchange tube to adjust the flow direction of the cooling medium in the second flow channel, thereby adjusting the heat transfer area between the cooling medium and the heat exchange tube and the convective heat transfer coefficient between the cooling medium and the heat exchange tube.

2. The skin structure according to claim 1, characterized in that: The annular heat exchanger further comprises: A plurality of fixing plates are arranged in the cavity, the fixing plates and the heat exchange tubes are spaced apart, and two ends of the driving mechanism are respectively connected to the fixing plates and the elastic fins.

3. The skin structure according to claim 1, characterized in that: The header includes: a first header and a second header, the first header and the second header are arranged opposite to each other, the first header and the second header are semicircular headers, wherein the first header is communicated with the first pipeline, and the second header is communicated with the second pipeline.

4. A cooling and regulating system, characterized in that: The invention comprises a heat source and the skin structure according to any one of claims 1 to 3, wherein the heat source is connected to the skin structure.

5. The cooling and conditioning system according to claim 4, characterized in that: Also includes: a heat source sensing unit, disposed in the heat source, for detecting the actual temperature of the liquid flowing back into the heat source through the second pipeline; A controller is communicatively connected to the heat source sensing unit, and is used to control the driving mechanism to drive the elastic fin to generate an offset relative to the heat exchange tube according to the measured temperature and the set temperature.

6. The cooling and conditioning system according to claim 5, characterized in that: Also includes: an environmental sensing unit, provided on the surface of the annular pipe, and configured to detect an incoming flow velocity and an incoming flow temperature outside the skin structure; The heat source sensing unit is also used to detect the heat load inside the heat source. The controller is provided with a characteristic database. The controller is used to obtain a target value of the offset of the elastic fin based on the incoming flow velocity, the incoming flow temperature and the heat load in combination with the characteristic database, and control the driving mechanism to drive the actual offset of the elastic fin to reach the target value, wherein the characteristic database is a data set consisting of relationship curves corresponding to the offset, the incoming flow velocity and the incoming flow temperature under different heat loads.

7. A method for cooling and regulating using the cooling and regulating system according to claim 5, characterized in that: include: obtaining a measured temperature of the liquid flowing through the second pipeline and returning to the heat source; When the measured temperature is greater than the set temperature, the driving mechanism is controlled to increase the offset of the elastic fin; When the measured temperature is lower than the set temperature, the driving mechanism is controlled to reduce the offset of the elastic fin.

Images