Aircraft frame structure

Abstract

The invention discloses an aircraft frame structure, which comprises a frame main body used for accommodating a heating source; the plurality of phase change heat dissipation plates are fixed on the frame main body, are in contact with the heating source and are used for absorbing heat generated by the heating source; wherein a first lattice structure is arranged in the frame main body, and gaps of the first lattice structure are filled with a first phase change material; a second lattice structure is arranged in the phase change heat dissipation plate, and gaps of the second lattice structure are filled with a second phase change material. The invention has the characteristics of light weight and large heat capacity.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and in particular to an aircraft frame structure. Background Technology

[0002] In recent years, aircraft have been continuously developing towards high speed and ultra-long distance, which has led to increasingly harsh external aerodynamic environments during flight, causing aircraft to bear greater force and thermal loads. At the same time, the large-scale application of integrated circuits and power electronics in the internal electronic equipment of aircraft has significantly increased the heat generated by the aircraft itself. Under the combined effects of multiple harsh conditions such as confined space, inability to provide air or liquid cooling, limited heat sink capacity, and external aerodynamic heating, the heat dissipation problem of aircraft has become a bottleneck in research and development technology.

[0003] Furthermore, ultra-long-distance flights place higher demands on the weight of aircraft, making the research on lightweight materials or structures while ensuring structural strength an urgent priority.

[0004] The statements herein provide only background information in relation to this invention and do not necessarily constitute prior art. Summary of the Invention

[0005] The purpose of this invention is to provide an aircraft frame structure that is both lightweight and has a large heat capacity.

[0006] To achieve the above objectives, the present invention is implemented through the following technical solution:

[0007] An aircraft frame structure, comprising:

[0008] The main frame is used to house the heat source;

[0009] Multiple phase change heat sinks are fixed to the frame body and in contact with the heat source to absorb the heat generated by the heat source.

[0010] The frame body is provided with a first lattice structure, and the gaps in the first lattice structure are filled with a first phase change material.

[0011] The phase change heat sink has a second lattice structure inside, and the gaps in the second lattice structure are filled with a second phase change material.

[0012] Optionally, the heat source includes a first heat source and a second heat source; the frame body includes:

[0013] An annular shell; the inner side of the annular shell forms a first receiving space to accommodate the first heat source;

[0014] The first isolation plate is fixedly connected to the annular shell.

[0015] The second isolation plate is disposed opposite to the first isolation plate;

[0016] Multiple crossbeams; one end of each crossbeam is fixedly connected to the first isolation plate, and the other end is fixedly connected to the second isolation plate;

[0017] The first isolation plate, the crossbeam, and the second isolation plate form a second accommodating space to accommodate the second heat source.

[0018] Optionally, the phase change heat sink is located between the first isolation plate and the second isolation plate and is detachably connected to the crossbeam.

[0019] Optionally, the aircraft frame structure is characterized by further comprising: a plurality of liquid-cooled heat dissipation plates (300) located between the first isolation plate and the second isolation plate, detachably connected to the crossbeam and in contact with the heat source, for absorbing the heat generated by the heat source;

[0020] The liquid cooling heat sink is provided with a liquid cooling channel for containing coolant, and either the liquid cooling heat sink or the phase change heat sink can be used.

[0021] Optionally, the annular shell is provided with a first flow channel, the first isolation plate is provided with a second flow channel, and the second isolation plate is provided with a third flow channel;

[0022] The inlet of the second flow channel is connected to the first flow channel, the outlet of the second flow channel is connected to the inlet of the liquid cooling flow channel, and the outlet of the liquid cooling channel is connected to the third flow channel.

[0023] Optionally, the frame body is provided with a plurality of first filling ports for filling the gaps in the first lattice structure with the first phase change material;

[0024] The phase change heat sink is provided with multiple second filling ports for filling the gaps in the second lattice structure with the second phase change material.

[0025] Optionally, both the first filling port and the second filling port are sealed with cover plates, and both the first filling port and the second filling port are provided with sealing components on their periphery.

[0026] Optionally, both the first lattice structure and the second lattice structure are formed by arranging and combining multiple face-centered cubic cells.

[0027] Optionally, both the first phase change material and the second phase change material are graphene-composite paraffin.

[0028] Optionally, the first heat source is a transceiver component, and the second heat source is an electronic device.

[0029] Compared with the prior art, the present invention has at least one of the following advantages:

[0030] This invention provides an aircraft frame structure, in which the frame body and phase change heat sink are internally equipped with a lattice structure. Based on the mechanical properties of the lattice structure, this invention can effectively reduce the weight of the aircraft frame structure while meeting its load requirements. When the temperature of the heat source rises, the phase change material filling the frame body and the phase change heat sink undergoes a phase change, significantly improving the heat sink capacity and heat absorption capacity of the aircraft frame structure. This slows down the heating rate of the heat source (e.g., T / R components, electronic devices), thereby extending the operating time of the heat source and improving its reliability.

[0031] In this invention, the flow channels within the main frame and the liquid cooling flow channels within the liquid cooling heat sink form a circulating flow channel surrounding the main frame, which can also improve the heat sink capacity and heat absorption capacity of the aircraft frame structure, thereby slowing down the heating rate of heat sources (such as T / R components and electronic devices), and thus improving the ability of the whole machine to be tested for a long time.

[0032] This invention features integrated molding, light weight, large heat capacity, and high reliability. Attached Figure Description

[0033] Figure 1 This is a perspective view of an aircraft frame structure provided in an embodiment of the present invention;

[0034] Figure 2 yes Figure 1 Cross-sectional view along the AA direction;

[0035] Figure 3 This is an installation view of a filling port cover plate in an aircraft frame structure according to an embodiment of the present invention;

[0036] Figure 4 This is a cross-sectional view of the second lattice structure inside the phase change heat sink in an aircraft frame structure according to an embodiment of the present invention;

[0037] Figure 5 This is a flow channel diagram of a liquid cooling heat dissipation plate in an aircraft frame structure provided by an embodiment of the present invention. Detailed Implementation

[0038] The following detailed description, in conjunction with the accompanying drawings and specific embodiments, provides a further detailed explanation of the aircraft frame structure proposed in this invention. The advantages and features of this invention will become clearer from the following description. It should be noted that the drawings are in a very simplified form and use non-precise proportions, intended only to facilitate and clearly illustrate the embodiments of this invention. Please refer to the drawings to make the objectives, features, and advantages of this invention more apparent and understandable. It should be understood that the structures, proportions, sizes, etc., depicted in the accompanying drawings are only for illustrative purposes and to aid those skilled in the art, and are not intended to limit the implementation conditions of this invention. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in proportions, or adjustments to the size, without affecting the effects and objectives achieved by this invention, should still fall within the scope of the technical content disclosed in this invention.

[0039] As described in the background section, while aircraft are developing towards high speed and ultra-long distance, heat dissipation and weight reduction have become bottlenecks restricting technological innovation. Current technologies typically optimize the aircraft frame structure through simulation and experimentation, reducing weight to a certain extent while maintaining strength margins. However, this method results in a frame structure with limited heat capacity, making it increasingly difficult to meet the heat dissipation requirements of high-power aircraft.

[0040] In view of this, such as Figures 1-5 As shown, this embodiment provides an aircraft frame structure, including: a frame body 100 and multiple phase change heat sinks 200 (see...). Figure 4 The frame body 100 is used to house and fix the heat source in the aircraft; optionally, the heat source includes a first heat source and a second heat source; in one embodiment, the first heat source is a transceiver assembly (i.e., a T / R assembly), and the second heat source is an electronic device. The phase change heat sink 200 is fixed to the frame body 100 and in contact with the heat source to absorb the heat generated by the heat source.

[0041] Specifically, the frame body 100 is provided with a first lattice structure 101 (see... Figure 2 The first lattice structure 101 is filled with a first phase change material in its gaps; the phase change heat sink 200 is provided with a second lattice structure 201 (see...). Figure 4The gaps in the second lattice structure 201 are filled with a second phase change material. More specifically, when the temperature of the heat source exceeds the phase change temperature of the first phase change material in the frame body 100 or the phase change temperature of the second phase change material in the phase change heat sink 200, the first or second phase change material gradually undergoes a solid-liquid phase change. Based on the characteristic that the phase change material absorbs a large amount of heat during the phase change process, the first or second phase change material will absorb a large amount of heat generated by the heat source when the solid-liquid phase change occurs, so that the heat of the heat source is conducted to the frame body 100 or the phase change heat sink 200, thereby slowing down the heating rate of the heat source (e.g., T / R component, electronic device), thereby extending the working time of the heat source and improving the reliability of the heat source.

[0042] Optionally, both the first and second phase change materials are high-enthalpy paraffin materials, enabling them to absorb more heat during the phase change process. In one embodiment, both the first and second phase change materials are graphene composite paraffins, and the enthalpy of the graphene composite paraffins is greater than 250 KJ / kg.

[0043] Optionally, the phase transition temperatures of the first phase change material and the second phase change material are 70°C to 75°C. This not only prevents the first and second phase change materials from undergoing premature phase transitions, but also allows them to absorb the heat generated by the heat source before it fails due to high temperature, thereby preventing the heat source from overheating and becoming inoperable. In one embodiment, the phase transition temperatures of both the first and second phase change materials are 72°C, but this invention is not limited thereto.

[0044] Optionally, both the first lattice structure 101 within the frame body 100 and the second lattice structure 201 within the phase change heat sink 200 are formed by arranging and combining multiple face-centered cubic (FCC) cells. This allows the first lattice structure 101 and the second lattice structure 201 to be filled with a larger amount of phase change material, thereby enabling the frame body 100 and the phase change heat sink 200 to have a larger heat sink capacity or a stronger heat absorption capacity, thus better slowing down the heating rate of the heat source (e.g., T / R components, electronic devices). Optionally, the side length of the face-centered cubic cell is not less than 6 mm to facilitate the filling of the first and second phase change materials. It is understood that the rods of the face-centered cubic cells in the first lattice structure 101 are integrally connected to the wall of the frame body 100, and the rods of the face-centered cubic cells in the second lattice structure 201 are integrally connected to the wall of the phase change heat sink 200.

[0045] Please continue to refer to this. Figures 1 to 4The frame body 100 is provided with a plurality of first filling and sealing ports 102 (see Figure 3 The first phase change material is used to fill the gaps in the first lattice structure 101; the phase change heat sink 200 is provided with a plurality of second filling ports 202 (see...). Figure 4 This is used to fill the voids in the second lattice structure 201 with the second phase change material. More specifically, both the first filling port 102 and the second filling port 202 are covered with a cover plate 400 (see...). Figure 1 The frame body 100 and the phase change heat sink 200 are sealed to prevent leakage of the first phase change material filled in the frame body 100 and the second phase change material filled in the phase change heat sink 200, thereby ensuring the reliability of the frame body 100 and the phase change heat sink 200.

[0046] Optionally, both the first filling port 102 and the second filling port 202 are provided with sealing components on their periphery, and the sealing components are covered by the cover plate 400 to further improve the sealing performance of the first filling port 102 and the second filling port 202. In one embodiment, such as Figure 3 and Figure 4 As shown, the sealing assembly includes a sealing groove 401 disposed around the first filling port 102 and the second filling port 202, and a sealing ring (not shown in the figure) located in the sealing groove 401.

[0047] Optionally, the periphery of the first filling port 102 and the second filling port 202 is further provided with threaded holes 402 (see...). Figure 3 Each of the cover plates 400 is fixed to the corresponding threaded hole 402 by countersunk screws, thereby realizing the fixed connection between the cover plate 400 and the frame body 100 and the phase change heat sink 200.

[0048] Please continue to refer to this. Figures 1 to 3 The frame body 100 includes an annular shell 110, a first isolation plate 120, a second isolation plate 130, and a plurality of crossbeams 140. A first receiving space is formed on the inner side of the annular shell 110 to accommodate the first heat source (e.g., a T / R assembly). The first isolation plate 120 is fixedly connected to the annular shell 110, and the second isolation plate 130 is disposed opposite to the first isolation plate 120. One end of each crossbeam 140 is fixedly connected to the first isolation plate 120, and the other end is fixedly connected to the second isolation plate 130; and the plurality of crossbeams 140 are distributed circumferentially at intervals along the first isolation plate 120 and / or the second isolation plate 130. The first isolation plate 120, the crossbeams 140, and the second isolation plate 130 form a second receiving space to accommodate the second heat source (e.g., an electronic device).

[0049] Specifically, the end of the annular housing 110 away from the first isolation plate 120 is fixedly connected to a cooling plate (not shown in the figure), and the cooling plate is disposed opposite to the first isolation plate 120. The first heat source located in the first accommodating space is fixed to the cooling plate by screws, and the first heat source and the cooling plate are tightly bonded together by a thermally conductive interface material; wherein, the thermally conductive interface material can eliminate the thermal resistance at the interface between the first heat source (e.g., a T / R component) and the cooling plate to ensure heat transfer efficiency. In one embodiment, there is an assembly gap of about 0.2 mm between the first heat source (e.g., a T / R component) and the inner wall of the annular housing 110, so that the first heat source can be assembled into the first accommodating space of the annular housing 110 after being fixed to the cooling plate.

[0050] Specifically, the second heat source (e.g., an electronic device) is fixedly connected to the crossbeam 140; optionally, the second heat source (e.g., an electronic device) is fixed to the crossbeam 140 by means of side lugs. The phase change heat sink 200 is located between the first isolation plate 120 and the second isolation plate 130, and is detachably connected to the crossbeam 400; and the plane of the phase change heat sink 200 intersects perpendicularly with the plane of the first isolation plate 120 and the second isolation plate 130. Optionally, the second heat source and the phase change heat sink 200 are tightly bonded by a thermally conductive interface material to eliminate the thermal resistance at the interface between the second heat source (e.g., an electronic device) and the phase change heat sink 200, thereby ensuring heat transfer efficiency.

[0051] In one embodiment, there are four crossbeams 140 and two phase change heat sinks 200. One phase change heat sink 200 is detachably connected to two crossbeams 140 at both ends, and the other phase change heat sink 200 is detachably connected to two other crossbeams 140 at both ends. However, the present invention is not limited thereto.

[0052] It is understood that since the annular shell 110, the first isolation plate 120, the second isolation plate 130, and the multiple crossbeams 140 together constitute the frame body 100, the interior of the annular shell 110, the first isolation plate 120, the second isolation plate 130, and the crossbeams 140 are all provided with the first lattice structure 101. Optionally, the annular shell 110 has four first filling ports 102 on its end face away from the first isolation plate 120, and the first isolation plate 120 and the second isolation plate 130 each have one first filling port 102 on their side. Each crossbeam 140 has two first filling ports 102 on its end face away from the second accommodating space, so that the first phase change material can be filled into the corresponding first lattice structure 101 through the first filling ports 102.

[0053] Please also refer to Figures 1 to 3 , Figure 5 The aircraft frame structure further includes: a plurality of liquid-cooled heat sinks 300, located between the first isolation plate 120 and the second isolation plate 130, detachably connected to the crossbeam 140 and in contact with the heat source, for absorbing the heat generated by the heat source. Specifically, the plane of the liquid-cooled heat sink 300 intersects perpendicularly with the plane of the first isolation plate 120 and the second isolation plate 130; and either the liquid-cooled heat sink 300 or the phase change heat sink 200 is used.

[0054] Specifically, the liquid-cooled heat sink 300 is provided with a liquid-cooled flow channel 301 for containing coolant (see...). Figure 2 and Figure 5 When the temperature of the heat source is higher than the temperature of the coolant in the liquid cooling channel 301, the coolant absorbs the heat generated by the heat source, causing the heat to be conducted to the liquid cooling heat sink 300. This slows down the heating rate of the heat source (e.g., T / R components, electronic devices), thereby extending the operating time of the heat source and improving its reliability. It is understood that when the coolant in the liquid cooling channel 301 absorbs heat and its temperature rises, and it can no longer absorb heat, the liquid cooling heat sink 300 will conduct the heat to the frame body 100, whereby the first phase change material within the frame body 100 absorbs the heat generated by the heat source.

[0055] Optionally, the liquid cooling channel 301 is in a tortuous shape. The tortuous shape can increase the length of the liquid cooling channel 301 to accommodate more coolant, thereby giving the liquid cooling heat sink 300 a larger heat sink capacity or a stronger heat absorption capacity.

[0056] Optionally, the second heat source and the liquid cooling heat sink 300 are tightly bonded together through a thermally conductive interface material to eliminate the thermal resistance at the interface between the second heat source (e.g., electronic device) and the liquid cooling heat sink 300, thereby ensuring heat transfer efficiency.

[0057] Specifically, the number of liquid-cooled heat sinks 300 is the same as the number of phase-change heat sinks 200, and both are installed in the same way as the frame body 100, thereby enabling the replacement of the liquid-cooled heat sinks 300 and the phase-change heat sinks 200 under different operating conditions. It should be noted that either the liquid-cooled heat sink 300 or the phase-change heat sink 200 can be used; specifically, the liquid-cooled heat sink 300 is used during ground testing of the aircraft; and the phase-change heat sink 200 is used during normal flight to reduce the aircraft's weight and size, but this invention is not limited thereto.

[0058] In one embodiment, there are four crossbeams 140 and two liquid cooling heat sinks 300. One liquid cooling heat sink 300 is detachably connected to two crossbeams 140 at both ends, and the other liquid cooling heat sink 300 is detachably connected to two other crossbeams 140 at both ends.

[0059] Please also refer to Figures 1 to 3 , Figure 5 The annular shell 110 has a first flow channel 111, the first isolation plate 120 has a second flow channel 121, and the second isolation plate 130 has a third flow channel 131; the liquid inlet of the second flow channel 121 is connected to the liquid outlet of the first flow channel 111, and the liquid outlet of the second flow channel 121 is connected to the liquid inlet 3011 of the liquid cooling channel 301 (see...). Figure 5 The liquid outlet 3012 of the liquid cooling channel 301 (see...) is connected. Figure 5 It is connected to the liquid inlet of the third flow channel 131.

[0060] Specifically, such as Figure 2 As shown, there are two of each of the first flow channel 111, the second flow channel 121, and the third flow channel 131. Optionally, the overhead cooling plate has a fourth flow channel in a meandering shape, and the liquid inlets of the two first flow channels 111 are respectively connected to the liquid inlet and outlet of the fourth flow channel in the overhead cooling plate, and the liquid outlets of the two third flow channels 131 are respectively connected to the liquid inlet and outlet of a liquid cooling device (not shown in the figure), so that the fourth flow channel, the two first flow channels 111, the two second flow channels 121, the two third flow channels 131, and the liquid cooling device in the overhead cooling plate are connected in series to form a circulating flow channel surrounding the entire frame body 100. Optionally, the liquid cooling device is fixedly connected to the second isolation plate 130; due to the large size of the liquid cooling device, the liquid cooling device is only used when the aircraft is being ground tested, and is not used when the aircraft is in normal flight.

[0061] More specifically, the liquid cooling device can cool the coolant in the circulating channel, so the heat generated by the heat source will be continuously carried away by the low-temperature coolant, thereby slowing down the heating rate of the heat source (e.g., T / R components, electronic equipment), and thus extending the working time of the heat source, improving the long-term testing capability of the entire aircraft (i.e., the aircraft). It is understood that in this case, the coolant in the liquid cooling channel 301 will not be unable to continue absorbing heat due to its own temperature rising.

[0062] Furthermore, the frame body 100 and phase change heat sink 200 provided in this embodiment can be integrally manufactured by 3D printing to reduce the mechanical connection interfaces between structures such as the annular shell 110, the first isolation plate 120, the second isolation plate 130, and multiple crossbeams 140. It is understood that the first filling port 102 and the second filling port 202 are powder cleaning ports reserved when printing the lattice structure of the frame body 100 and the phase change heat sink 200; and after the frame body 100 and the phase change heat sink 200 are printed, the first filling port 102 and the second filling port 202 are used to fill the gaps in the corresponding lattice structure with phase change material. Optionally, the diameter of the first filling port 102 and the second filling port 202 is not less than 6mm to facilitate powder cleaning of the lattice structure and to facilitate filling with phase change material.

[0063] In summary, the aircraft frame structure provided in this embodiment features a lattice structure within the frame body and phase change heat sink. Based on the mechanical properties of the lattice structure, the weight of the aircraft frame structure can be effectively reduced while meeting its load requirements. When the temperature of the heat source within the aircraft frame structure rises, the phase change material filling the frame body and phase change heat sink undergoes a phase change, significantly increasing the heat sink capacity and heat absorption capacity of the aircraft frame structure. This slows down the heating rate of the heat source (e.g., T / R components, electronic devices), thereby extending the operating time of the heat source and improving its reliability. Furthermore, in this embodiment, the flow channels within the frame body and the liquid cooling flow channels within the liquid cooling heat sink form a circulating flow channel surrounding the frame body, which also enhances the heat sink capacity and heat absorption capacity of the aircraft frame structure, thereby slowing down the heating rate of the heat source (e.g., T / R components, electronic devices) and improving the overall aircraft's (i.e., the aircraft's) ability to withstand long-term testing.

[0064] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0065] In the description of this invention, it should be understood that the terms "center," "height," "thickness," "upper," "lower," "vertical," "horizontal," "top," "bottom," "inner," "outer," "axial," "radial," and "circumferential," etc., indicating orientation or positional relationships, are based on the orientation or positional relationships shown in the accompanying drawings and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0066] In the description of this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0067] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0068] Although the present invention has been described in detail through the preferred embodiments above, it should be understood that the above description should not be considered as a limitation of the present invention. Various modifications and substitutions to the present invention will be apparent to those skilled in the art after reading the above description. Therefore, the scope of protection of the present invention should be defined by the appended claims.

Claims

1. An aircraft frame structure, characterized in that, include: The main frame (100) is used to house the heat source; Multiple phase change heat sinks (200) are fixed on the frame body (100) and in contact with the heat source to absorb the heat generated by the heat source; The frame body (100) is provided with a first lattice structure (101), and the gaps in the first lattice structure (101) are filled with a first phase change material. The phase change heat sink (200) is provided with a second lattice structure (201), and the gaps in the second lattice structure (201) are filled with a second phase change material.

2. The aircraft frame structure as described in claim 1, characterized in that, The heat source includes a first heat source and a second heat source; the frame body (100) includes: An annular housing (110); the inner side of the annular housing (110) forms a first receiving space to receive the first heat source; The first isolation plate (120) is fixedly connected to the annular shell (110); The second isolation plate (130) is disposed opposite to the first isolation plate (120); Multiple crossbeams (140); one end of each crossbeam (140) is fixedly connected to the first isolation plate (120), and the other end is fixedly connected to the second isolation plate (130); The first isolation plate (120), the crossbeam (140) and the second isolation plate (130) form a second accommodating space to accommodate the second heat source.

3. The aircraft frame structure as described in claim 2, characterized in that, The phase change heat sink (200) is located between the first isolation plate (120) and the second isolation plate (130) and is detachably connected to the crossbeam (400).

4. The aircraft frame structure as described in claim 2, characterized in that, Also includes: Multiple liquid-cooled heat dissipation plates (300) are located between the first isolation plate (120) and the second isolation plate (130), and are detachably connected to the crossbeam (140) and in contact with the heat source, for absorbing the heat generated by the heat source; The liquid cooling heat sink (300) is provided with a liquid cooling channel (301) for containing coolant, and the liquid cooling heat sink (300) and the phase change heat sink (200) can be used interchangeably.

5. The aircraft frame structure as described in claim 4, characterized in that, The annular shell (110) is provided with a first flow channel (111), the first isolation plate (120) is provided with a second flow channel (121), and the second isolation plate (130) is provided with a third flow channel (131). The inlet of the second flow channel (121) is connected to the first flow channel (111), the outlet of the second flow channel (121) is connected to the inlet (3011) of the liquid cooling flow channel (301), and the outlet (3012) of the liquid cooling channel (301) is connected to the third flow channel (131).

6. The aircraft frame structure as described in claim 1, characterized in that, The frame body (100) is provided with a plurality of first filling ports (102) for filling the gaps in the first lattice structure (101) with the first phase change material; The phase change heat sink (200) is provided with a plurality of second filling ports (202) for filling the gaps in the second lattice structure (201) with the second phase change material.

7. The aircraft frame structure as described in claim 6, characterized in that, Both the first filling port (102) and the second filling port (202) are sealed with a cover plate (400), and both the first filling port (102) and the second filling port (202) are provided with sealing components on their periphery.

8. The aircraft frame structure as described in claim 1 or 6, characterized in that, Both the first lattice structure (101) and the second lattice structure (201) are formed by the arrangement and combination of multiple face-centered cubic cells.

9. The aircraft frame structure as described in claim 1 or 6, characterized in that, Both the first phase change material and the second phase change material are graphene-composite paraffin.

10. The aircraft frame structure as described in claim 2, characterized in that, The first heat source is a transceiver component, and the second heat source is an electronic device.

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