Method and device for determining service life of radar assembly, electronic equipment and medium

Abstract

The invention provides a method and device for determining the service life of a radar assembly, electronic equipment and a medium, the heat conductivity coefficient of the radar assembly is obtained, the radar assembly comprises a heat dissipation structure, the heat dissipation structure comprises an assembly heat dissipation layer, a heat conduction silicone grease layer and a uniform temperature plate layer, and the heat conduction silicone grease layer comprises a normal area and a dry area. The normal area is an area in which interlayer silicone grease loss does not occur, and the dry area is an area in which interlayer silicone grease loss occurs; determining an interlayer silicone grease loss amount of the radar assembly, and determining a first area corresponding to the dry area according to the interlayer silicone grease loss amount; and obtaining the total area of the heat-conducting silicone grease layer, and determining the remaining use time of the radar assembly according to the first area, the total area and the heat conductivity coefficient. According to the invention, accurate prediction of the service life of the radar assembly is realized.

Description

Technical Field

[0001] The present disclosure relates to the field of data processing, and in particular to a method, device, electronic device, and medium for determining the lifespan of a radar component. Background Art

[0002] The TR assembly is a core component of radar equipment, primarily responsible for functions such as transmit power amplification, low-noise amplification of received signals, transceiver conversion, array amplitude correction, and beam scanning within the phased array antenna. During radar operation, the high transmit and receive power of the TR assembly generates significant heat, raising its operating temperature, affecting proper functioning and even causing damage. To minimize thermal damage, TR assemblies typically utilize thermally conductive silicone grease as a thermal interface material to improve heat dissipation efficiency. However, over long-term use, the thermally conductive silicone grease can degrade heat dissipation performance due to extrusion and volatilization, shortening the lifespan of the TR assembly.

[0003] At present, traditional life prediction methods usually rely on a large number of preliminary tests, which not only require a long period of data accumulation, but also require a large amount of manpower and material resources, resulting in high costs and long cycles, and it is difficult to meet the needs of engineering applications for fast and accurate evaluation. Summary of the Invention

[0004] In view of this, an object of the present disclosure is to provide a method, device, electronic device, and medium for determining the lifespan of a radar component, so as to solve or partially solve the above-mentioned problems.

[0005] Based on the above objectives, a first aspect of the present disclosure provides a method for determining the lifespan of a radar component, the method comprising:

[0006] Obtaining a thermal conductivity coefficient of a radar component, wherein the radar component includes a heat dissipation structure, the heat dissipation structure including a component heat dissipation layer, a thermal grease layer, and a vapor chamber layer, the thermal grease layer including a normal region and a dry region, wherein the normal region is a region where no interlayer grease loss has occurred, and the dry region is a region where interlayer grease loss has occurred;

[0007] Determining an amount of interlayer silicone grease loss of the radar component, and determining a first area corresponding to the dry region according to the amount of interlayer silicone grease loss;

[0008] A total area of ​​the thermal grease layer is obtained, and a remaining service life of the radar component is determined according to the first area, the total area, and the thermal conductivity.

[0009] Based on the same inventive concept, a second aspect of the present disclosure provides a device for determining the life of a radar component, the device comprising:

[0010] a data acquisition module configured to acquire a thermal conductivity coefficient of a radar component, wherein the radar component includes a heat dissipation structure, the heat dissipation structure includes a component heat dissipation layer, a thermal grease layer, and a temperature vapor chamber layer, the thermal grease layer includes a normal region and a dry region, the normal region being a region where interlayer grease loss has not occurred, and the dry region being a region where interlayer grease loss has occurred;

[0011] an area determination module configured to determine an amount of silicone grease loss between layers of the radar assembly, and determine a first area corresponding to the dry region according to the amount of silicone grease loss between layers;

[0012] The remaining time determination module is configured to obtain the total area of ​​the thermal grease layer and determine the remaining usage time of the radar component according to the first area, the total area and the thermal conductivity.

[0013] Based on the same inventive concept, the third aspect of the present disclosure proposes an electronic device, including a memory, a processor, and a computer program stored in the memory and executable by the processor. When the processor executes the computer program, it implements the above-mentioned method for determining the life of the radar component.

[0014] Based on the same inventive concept, a fourth aspect of the present disclosure proposes a non-transitory computer-readable storage medium, wherein the non-transitory computer-readable storage medium stores computer instructions, and the computer instructions are used to enable a computer to execute the above-mentioned method for determining the lifetime of a radar component.

[0015] As can be seen from the above, the present disclosure proposes a method, device, electronic device, and medium for determining the lifespan of a radar assembly. The method obtains the thermal conductivity of the radar assembly, determines the amount of interlayer silicone grease loss in the radar assembly, and determines the first area corresponding to the dried-up region based on the interlayer silicone grease loss. The total area of ​​the thermal grease layer is obtained, and the remaining service life of the radar assembly is determined based on the first area, the total area, and the thermal conductivity. The heat dissipation performance of the radar assembly is indirectly determined using the weight loss method, significantly reducing testing difficulty, simplifying data collection, and effectively saving testing costs. By combining the relationship between the first area of ​​the dried-up region and the total area of ​​the thermal grease layer with the thermal conductivity, an accurate prediction of the remaining service life of the radar assembly is achieved. This avoids the problem of a radar assembly being used for too long, with its heat dissipation performance deteriorating, but the user continuing to use the radar assembly without being aware of it, resulting in low accuracy in radar detection and other functions implemented using the radar assembly. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the present disclosure or related technologies, the following briefly introduces the drawings required for use in the embodiments or related technical descriptions. Obviously, the drawings described below are only embodiments of the present disclosure. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0017] Figure 1 A flowchart of a method for determining the life of a radar component according to an embodiment of the present disclosure;

[0018] Figure 2 is a schematic diagram of a heat dissipation structure of a radar assembly according to an embodiment of the present disclosure;

[0019] Figure 3 Schematic diagram of silicone grease loss in a thermally conductive silicone grease layer according to an embodiment of the present disclosure;

[0020] Figure 4 A schematic diagram of interlayer silicone grease of a thermally conductive silicone grease layer according to an embodiment of the present disclosure;

[0021] Figure 5 This is a schematic diagram of an embodiment of the present disclosure after the loss of interlayer silicone grease;

[0022] Figure 6 Schematic diagram of the regional distribution of the thermal grease layer according to an embodiment of the present disclosure;

[0023] Figure 7 Schematic top view of the heat dissipation structure of the TR assembly according to an embodiment of the present disclosure;

[0024] Figure 8 is a cross-sectional schematic diagram of the heat dissipation structure of the TR assembly according to an embodiment of the present disclosure;

[0025] Figure 9 A schematic diagram of the composition of a radar assembly according to another embodiment of the present disclosure;

[0026] Figure 10 This is a schematic diagram of fitting results of another embodiment of the present disclosure;

[0027] Figure 11 This is a schematic diagram of a fitting curve according to another embodiment of the present disclosure;

[0028] Figure 12 A schematic diagram of the degradation trajectory of a TR component over time according to another embodiment of the present disclosure;

[0029] Figure 13 This is a structural block diagram of a device for determining the life of a radar component according to an embodiment of the present disclosure;

[0030] Figure 14 Schematic diagram of the structure of an electronic device according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0031] In order to make the objectives, technical solutions and advantages of the present disclosure more clearly understood, the present disclosure is further described in detail below in conjunction with specific embodiments and with reference to the accompanying drawings.

[0032] It should be noted that, unless otherwise defined, the technical terms or scientific terms used in the embodiments of the present disclosure should have the usual meanings understood by people with ordinary skills in the field to which the present disclosure belongs. The "first", "second" and similar words used in the embodiments of the present disclosure do not indicate any order, quantity or importance, but are only used to distinguish different components. "Include" or "comprise" and similar words mean that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects. "Connect" or "connected" and similar words are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "Up", "down", "left", "right" and the like are only used to indicate relative position relationships. When the absolute position of the described object changes, the relative position relationship may also change accordingly.

[0033] The terms used in this disclosure are explained as follows:

[0034] TR component: The T / R component refers to the part between the radio frequency and the antenna in a wireless transceiver system. That is, a wireless transceiver system is formed when one end of the T / R component is connected to the antenna and the other end is connected to the intermediate frequency processing unit.

[0035] Lucas-Washburn Equation: The Washburn equation, the Lucas-Washburn equation is a basic expression used to describe capillary rise in porous materials in terms of mean pore size, liquid viscosity, surface tension, contact angle, and time.

[0036] The TR assembly is a core component of radar equipment, primarily responsible for functions such as transmit power amplification, low-noise amplification of received signals, transceiver conversion, array amplitude correction, and beam scanning within the phased array antenna. During radar operation, the high transmit and receive power of the TR assembly generates significant heat, raising its operating temperature, affecting proper functioning and even causing damage. To minimize thermal damage, TR assemblies typically utilize thermally conductive silicone grease as a thermal interface material to improve heat dissipation efficiency. However, over long-term use, the thermally conductive silicone grease can degrade heat dissipation performance due to extrusion and volatilization, shortening the lifespan of the TR assembly.

[0037] Currently, research on the thermal degradation of TR modules focuses primarily on field trials and empirical data analysis. Physical modeling methods are lacking to quantify the impact of thermal degradation and to predict module lifespans based on this. Furthermore, traditional lifespan prediction methods typically rely on extensive baseline testing, which not only requires extensive data accumulation but also significant human and material resources. This results in high costs and long lead times, making it difficult to meet the requirements of rapid and accurate assessments in engineering applications.

[0038] Based on the above description, this embodiment proposes a method for determining the life of a radar component, such as Figure 1 As shown, the method includes:

[0039] Step 101: Obtaining a thermal conductivity coefficient of a radar component, wherein the radar component includes a heat dissipation structure, the heat dissipation structure including a component heat dissipation layer, a thermal grease layer, and a vapor chamber layer, the thermal grease layer including a normal region and a dry region, wherein the normal region is a region where no interlayer grease loss occurs, and the dry region is a region where interlayer grease loss occurs;

[0040] Step 102: determining the loss of interlayer silicone grease of the radar component, and determining a first area corresponding to the dry region according to the loss of interlayer silicone grease;

[0041] Step 103 : Obtain a total area of ​​the thermal grease layer, and determine a remaining service life of the radar component according to the first area, the total area, and the thermal conductivity.

[0042] In a specific implementation, the radar assembly includes a heat dissipation structure, such as Figure 2 As shown, the heat dissipation structure includes a component heat dissipation layer, a thermal grease layer and a temperature-averaging plate layer, wherein the base plate and the temperature-averaging plate are fixed and installed through threaded connections, and the temperature-averaging plate is connected to the heat sink on the antenna array surface for centralized heat dissipation.

[0043] The radar assembly in question is a TR assembly. However, during long-term storage and operation, the thermal grease layer between the TR assembly layers can be lost due to factors such as grease extrusion and silicone oil drying, causing the TR assembly's heat dissipation performance to degrade. Grease pumping is primarily manifested as the relative displacement of the two connecting surfaces, leading to the loss of thermal grease from the contact gap. This phenomenon is typically driven by a combination of thermal and mechanical stresses and is common in situations of high heat loads or improper assembly.

[0044] Under the action of external forces, silicone grease continuously transfers outward along the capillary channel. There are two main ways for the formation of capillary channels: one is the void cavity caused by surface roughness at the thermal interface; the other is the channel formed by the change of the internal structure of the thermal grease during long-term use. Silicone oil drying is manifested as the volatilization of silicone oil in the silicone grease. As time goes by, the silicone oil molecules gradually decrease from the center to the outside, eventually leading to the continuous loss of silicone oil, such as Figure 3 As the silicone oil is lost, the connection between the thermally conductive particles is destroyed, the contact thermal resistance increases, the effective thermal conductivity of the thermal grease changes, and the heat dissipation performance gradually decreases.

[0045] That is, the main mechanism for the decline in heat dissipation performance of TR components is the loss and volatilization of the interlayer silicone grease. The thermal grease in the thermal grease layer is usually prepared by fully mixing thermal conductive filler particles and silicone oil. For this reason, the thermal conductive filler particles in the silicone grease can be assumed to be evenly stacked to form a solid matrix structure, and its ideal distribution is as follows: Figure 4 shown.

[0046] As degradation occurs, the edge of the silicone grease will be squeezed out, and the silicone oil will continue to lose and evaporate, causing the intact thermal grease interface to gradually shrink from the periphery to the center, and forming two parts in the interlayer silicone grease: a normal area and a dry area. Figure 5 That is, the thermal grease layer includes a normal area and a dry area, as shown in FIG. Figure 6 The normal area is the area where the interlayer silicone grease loss does not occur, and the dry area is the area where the interlayer silicone grease loss occurs.

[0047] Determine the amount of interlayer silicone grease loss of the radar assembly, wherein the interlayer silicone grease loss is the weight of the silicone grease lost between the layers of the TR assembly, i.e., the weight loss of the silicone grease between the layers of the TR assembly. Determine a first area corresponding to the dried-up region based on the interlayer silicone grease loss, wherein the first area is the area where the interlayer silicone grease loss occurred.

[0048] The total area of ​​the thermal grease layer is obtained, and the remaining service life of the radar assembly is determined based on the first area, the total area, and the thermal conductivity. The lifespan of a radar assembly can be represented by its heat dissipation performance. Therefore, the remaining service life represents the time interval for the heat dissipation performance of the radar assembly to degrade from a current state to a preset threshold. Specifically, the time required for the heat dissipation performance of the radar assembly to degrade to the preset threshold represents the remaining operating time of the radar assembly. If the operating time exceeds the remaining service life, the radar assembly may continue to operate, but due to poor heat dissipation performance, there is a risk that the radar assembly may malfunction.

[0049] Through the above scheme, the thermal conductivity of the radar assembly is obtained, the loss of interlayer silicone grease in the radar assembly is determined, and the first area corresponding to the dried-up region is determined based on the loss of interlayer silicone grease. The total area of ​​the thermal grease layer is obtained, and the remaining service life of the radar assembly is determined based on the first area, the total area, and the thermal conductivity. By indirectly determining the heat dissipation performance of the radar assembly through the weight loss method, the testing difficulty is greatly reduced, data collection is simplified, and testing costs can be effectively saved. By combining the relationship between the first area of ​​the dried-up region and the total area of ​​the thermal grease layer with the thermal conductivity, an accurate prediction of the remaining service life of the radar assembly can be achieved. This avoids the problem of the radar assembly being used for too long, the heat dissipation performance being degraded, and the user continuing to use the radar assembly without being aware of it, resulting in low accuracy of radar detection and other functions implemented using the radar assembly.

[0050] In some embodiments, the thermal conductivity includes a first thermal conductivity of a normal region and a second thermal conductivity of a dry region, and step 103 includes:

[0051] Step 1031: determining a heat dissipation change correspondence relationship based on the first thermal conductivity and the second thermal conductivity, wherein the heat dissipation change correspondence relationship is a correspondence relationship between heat dissipation capacity and usage time during use of the radar component;

[0052] Step 1032: Obtain a preset interlayer thermal conductivity threshold, and determine the remaining service life of the radar component based on the heat dissipation change correspondence and the interlayer thermal conductivity threshold.

[0053] In specific implementations, the thermal conductivity coefficient includes a first thermal conductivity coefficient for the normal area and a second thermal conductivity coefficient for the dry area. The thermal conductivity coefficient represents the interlayer thermal conductivity of the thermal grease layer of the radar assembly. A heat dissipation variation relationship is determined based on the first and second thermal conductivity coefficients. The heat dissipation variation relationship represents the relationship between the heat dissipation capacity and the duration of use during the radar assembly's operation. Specifically, different durations of use correspond to different heat dissipation capacities. It is understood that as the radar assembly ages, its heat dissipation capacity gradually decreases.

[0054] Obtain a preset interlayer thermal conductivity threshold. The interlayer thermal conductivity corresponds to the heat dissipation capacity of the radar assembly and is the minimum limit for maintaining normal operation of the radar assembly. Determine the remaining service life of the radar assembly based on the heat dissipation change relationship and the interlayer thermal conductivity threshold.

[0055] In this embodiment, the heat dissipation change correspondence is expressed as an equation relating heat dissipation capacity to usage time. Therefore, after determining the interlayer thermal conductivity threshold, the interlayer thermal conductivity threshold can be substituted into the heat dissipation change correspondence to obtain the remaining usage time of the radar component.

[0056] In some embodiments, determining the heat dissipation change correspondence relationship based on the first thermal conductivity and the second thermal conductivity in step 1031 specifically includes:

[0057] Step 10311: Subtract the total area from the first area to obtain an area difference;

[0058] Step 10312: performing a ratio processing on the area difference and the total area to obtain a first area weight value corresponding to the normal area;

[0059] Step 10313: performing ratio processing on the first area and the total area to obtain a second area weight value corresponding to the dry area;

[0060] Step 10314: Weighting the first thermal conductivity and the second thermal conductivity according to the first area weight value and the second area weight value to obtain a heat dissipation change correspondence relationship, wherein the heat dissipation change correspondence relationship is expressed by the formula:

[0061]

[0062] Among them, k eff is the interlayer thermal conductivity of the radar component, k eff1 is the first thermal conductivity, k eff2 is the second thermal conductivity, A0 is the total area, A2(t) is the first area, and t is the usage time.

[0063] During specific implementation, the total area is subtracted from the first area to obtain an area difference value, and the area difference value is the area value corresponding to the normal area.

[0064] The area difference is ratioed to the total area to obtain a first area weight value corresponding to the normal area. The first area is ratioed to the total area to obtain a second area weight value corresponding to the dry area.

[0065] The first thermal conductivity and the second thermal conductivity are weighted according to the first area weight value and the second area weight value to obtain a heat dissipation change correspondence relationship, wherein the heat dissipation change correspondence relationship is expressed by the formula:

[0066]

[0067] Among them, keff is the interlayer thermal conductivity of the radar component, k eff1 is the first thermal conductivity, k eff2 is the second thermal conductivity, A0 is the total area, A2(t) is the first area, and t is the usage time.

[0068] In some embodiments, determining the loss of interlayer silicone grease of the radar component in step 102 specifically includes:

[0069] Step 1021: Obtaining a silicone grease density in the thermal grease layer, and determining a silicone grease loss amount based on the silicone grease density, wherein the silicone grease loss amount is a loss caused by silicone grease being squeezed out of the thermal grease layer during use of the radar component.

[0070] Step 1022: determining a silicone oil flow rate in the thermal grease layer, and determining a silicone grease volatilization loss amount based on the silicone oil flow rate, wherein the silicone grease volatilization loss amount is a loss caused by volatilization of the silicone grease in the thermal grease layer during use of the radar component.

[0071] Step 1023 : Add the silicone grease loss amount and the silicone grease volatilization loss amount to obtain the interlayer silicone grease loss amount of the radar component.

[0072] In specific implementation, in the dry area, the silicone grease mainly has two states, such as Figure 4 One is that the silicone grease is continuously squeezed outward along the capillary channel under the action of external load, that is, Figure 4 The middle shaded area is the area where the silicone grease is lost. The other is the area where the silicone oil evaporates and dries up. Figure 4 The gray area in the figure is the area where the silicone grease evaporates.

[0073] Obtaining the density of the thermal grease layer, and determining the amount of grease loss based on the density of the grease, wherein the grease loss is the loss caused by the grease in the thermal grease layer being squeezed out during the use of the radar component. The process of determining the amount of grease loss specifically includes:

[0074] The grease density in the thermal grease layer is obtained, and the grease loss amount is determined according to the grease density, wherein the grease loss amount is expressed by the formula:

[0075] Δm l (t)=h1A2(t)ρ

[0076] Where ρ is the density of silicone grease, h1 is the first thickness corresponding to the silicone grease loss area, Δm l (t) is the loss of silicone grease.

[0077] Regarding silicone oil loss caused by volatilization, this embodiment describes the mass change in this region based on the classical theory of evaporation and condensation. This theory assumes that at the gas-liquid interface, saturated vapor condenses at a gas phase pressure pg and a liquid phase temperature Tl, and that the difference in mass flow rate between gas and liquid phase molecules is the driving force of the volatilization process. The silicone oil flow rate in the thermal grease layer is determined as follows:

[0078] Obtaining a preset liquid phase pressure and a gas phase pressure, and determining the silicone oil flow rate in the thermal grease layer according to the liquid phase pressure and the gas phase pressure, wherein the silicone oil flow rate is expressed by the formula:

[0079]

[0080] Where j is the silicone oil rate, p l With p g are the liquid phase pressure and gas phase pressure respectively, M is the average molar mass of silicone oil components, R is the gas constant, T l is the liquidus temperature, k e is the correction factor for evaporation-condensation time.

[0081] The amount of silicone grease volatilization loss is determined based on the silicone oil flow rate, wherein the silicone grease volatilization loss is the loss caused by volatilization of silicone grease in the thermal grease layer during use of the radar component. The silicone grease volatilization loss is determined specifically as follows:

[0082] The volatilization loss of silicone grease is determined according to the silicone oil flow rate, wherein the volatilization loss of silicone grease is expressed by the formula:

[0083]

[0084] Where, Δm e (t) is the volatilization loss of silicone grease, and A2 is the first area.

[0085] The loss amount of the silicone grease is added to the loss amount of the silicone grease volatilization to obtain the loss amount of the silicone grease between the layers of the radar component. The loss amount of the silicone grease between the layers is specifically:

[0086]

[0087] P2=2h1ρ

[0088] P1=(a+b)h1ρ

[0089] Wherein, Δm(t) is the loss of interlayer silicone grease, B is the target silicone grease parameter, h1 is the first thickness corresponding to the silicone grease loss area, a is the length of the initial rectangular area of ​​silicone grease, b is the width of the initial rectangular area of ​​silicone grease, and k e are preset parameters.

[0090] In this embodiment, the target silicone grease parameters can be determined by accelerated testing. Specifically, the target silicone grease parameters can be determined by fitting the test data using tools such as MATLAB. The specific method is as follows:

[0091] A preset data set and a preset silicone grease penetration creep time correction coefficient are obtained, and the preset data set is fitted according to the interlayer silicone grease loss amount and the silicone grease penetration creep time correction coefficient to obtain a target silicone grease parameter, wherein the target silicone grease parameter is expressed by the formula:

[0092]

[0093] Where h1 is the first thickness corresponding to the silicone grease loss area, t is time, μ is the silicone grease viscosity, γ is the surface tension of the silicone grease, θ is the contact angle, and k c It is the correction factor for the creeping time of silicone grease penetration, which is mainly used to consider the influence of temperature alternation, vibration, impact and other loads on the TR component in the actual working environment.

[0094] Through the above scheme, the combination of accelerated damage testing and physical modeling can reduce the test cycle and cost, providing a more economical and efficient solution for design, maintenance and life assessment.

[0095] In some embodiments, determining the first area corresponding to the dried-up region according to the loss of interlayer silicone grease in step 102 specifically includes:

[0096] Step 102A: Determine the shrinkage distance corresponding to the dry area according to the Washburn equation and the target silicone grease parameters, wherein the shrinkage distance is expressed by the formula:

[0097]

[0098] Wherein, L is the shrinkage distance;

[0099] Step 102B: determining a first area corresponding to the dry region according to the shrinkage distance, wherein the first area is expressed by the formula:

[0100]

[0101] In specific implementation, assuming that the normal area shrinks uniformly inward, the area formed by the extrusion of silicone grease and the volatilization of silicone oil is also the area of ​​the dry area. The shrinkage distance is recorded as L. The top view of the heat dissipation structure of the TR component is as follows: Figure 7 As shown, the cross-sectional view of the heat dissipation structure of the TR component is as follows Figure 8 As shown in Figure 2, the shrinkage of the “normal area” is continuous over time, so the shrinkage distance can be expressed as a function of time, denoted as L(t).

[0102] A2(t)=ab-(a-2L(t))(b-2L(t))

[0103] =2[(a+b)L(t)-2L(t) 2 ]

[0104] Since the "normal area" shrinks uniformly inward, the area where the silicone grease is squeezed out is equal to the area where the silicone oil evaporates. The squeeze out of the silicone grease is mainly caused by capillary forces. The mass flow rate of capillary flow is usually described by the Lucas-Washburn (LW) equation.

[0105] To accurately simulate this phenomenon, in this embodiment, the shrinkage distance corresponding to the dry area is determined according to the Washburn equation and the target silicone grease parameters, wherein the shrinkage distance is expressed by the formula:

[0106]

[0107] Where L is the shrinkage distance.

[0108] By correcting the LW equation, it can be seen that the contraction distance is t 1 / 2 A linear function of , and then determining the first area corresponding to the dry area according to the shrinkage distance, wherein the first area is expressed by the formula:

[0109]

[0110] In some embodiments, the heat dissipation performance of the TR component is mainly measured by the effective thermal conductivity of the thermal interface, that is, the interlayer thermal conductivity k eff It indicates that the interlayer thermal conductivity is defined as follows:

[0111]

[0112] Where Φ is the total heat flux transferred along the heat dissipation channel within time Δt, h is the interlayer thickness, A0 is the area of ​​the entire thermal interface, Φ1 is the heat flux in the normal region, and Φ2 is the heat flux in the dry region, which can be determined using the effective thermal conductivity of the normal region and the dry region, respectively. The first thermal conductivity of the normal region and the second thermal conductivity of the dry region can be expressed using the formula:

[0113]

[0114] Among them, A1 is the area of ​​the normal area, and A2 is the area of ​​the dry area.

[0115] Furthermore, the interlayer thermal conductivity is expressed as follows:

[0116]

[0117] In some embodiments, the first thermal conductivity of the normal region is determined by referring to the Maxwell model of the composite material. The first thermal conductivity is determined as follows:

[0118] Obtain the filler thermal conductivity, matrix thermal conductivity, and filler volume fraction of the silicone grease filler in the thermal grease layer, and determine a first thermal conductivity in a normal area based on the filler thermal conductivity, matrix thermal conductivity, and filler volume fraction. The first thermal conductivity is expressed as follows:

[0119]

[0120] Among them, k eff1 is the first thermal conductivity, k1 is the filler thermal conductivity, k2 is the matrix thermal conductivity, and ε1 is the volume fraction of the filler in the silicone grease.

[0121] In some embodiments, the dried-up area includes the silicone grease loss area and the silicone grease volatilization area. Therefore, the second thermal conductivity of the dried-up area can be obtained by calculating the thermal conductivity of each layer separately and then comprehensively calculating the thermal conductivity of each layer. Specifically, the second thermal conductivity is determined as follows:

[0122] The thermal conductivity of air is obtained and used as the first initial thermal conductivity corresponding to the silicone grease loss area. The first initial thermal conductivity is expressed by the formula:

[0123] k eff21 =k3

[0124] Among them, k eff21 is the first initial thermal conductivity, k3 is the thermal conductivity of air.

[0125] Obtain the filler thermal conductivity and filler volume fraction of the silicone grease filler in the thermal grease layer, and determine the second initial thermal conductivity corresponding to the silicone grease volatilization area based on the filler thermal conductivity, the air thermal conductivity, and the filler volume fraction. The second initial thermal conductivity is expressed as follows:

[0126]

[0127] A first thickness corresponding to the silicone grease loss area and a second thickness corresponding to the silicone grease volatilization area are determined, and an equivalent thermal resistance conversion is performed according to the first initial thermal conductivity, the second initial thermal conductivity, the first thickness, and the second thickness to obtain a second thermal conductivity of the dried-up area.

[0128] In this embodiment, the first thickness of the silicone grease loss area is 1 / 2 of the total thickness of the thermal grease layer, and the second thickness of the silicone grease volatilization area is 1 / 4 of the total thickness of the thermal grease layer. Furthermore, in this embodiment, the second thermal conductivity is expressed by the formula:

[0129]

[0130] Wherein, h1 is the first thickness corresponding to the silicone grease loss area, h2 is the second thickness corresponding to the silicone grease volatilization area, k3 is the thermal conductivity of air, and H2 is the total thickness of the thermal grease layer.

[0131] Based on the same inventive concept, another embodiment of the present disclosure provides a specific example of the method for determining the life of a radar component in the above embodiment. The radar component is a TR component. Figure 9 shown.

[0132] The structure of the radar assembly includes a heat dissipation layer, a thermal grease layer, and a temperature plate layer. The constituent materials of each layer are shown in Table 1.

[0133] Table 1

[0134] composition Material Remark Component heat dissipation layer Aluminum alloy 6063 H1=6.9mm Thermal grease layer TC-5021 thermal grease H2=0.5mm Temperature distribution plate layer Aluminum alloy 6063 H3=5mm

[0135] The relevant parameters of the silicone grease material used in the thermal grease layer are shown in Table 2.

[0136]

[0137]

[0138] Based on the target TR module's storage and use benchmark profile, an accelerated test of module heat dissipation structure damage was designed and implemented. The collected silicone grease mass loss data is shown in Table 3. This collected data represents the preset data set in the aforementioned embodiment.

[0139] Table 3

[0140]

[0141] Based on the data from 0 to 3 cycles, the unknown parameters were fitted using the MATLAB fitting tool, and the fitting result of the target silicone grease parameter B was 3.0346×10 -6 , preset parameter k e The fitting result is 2.733×10 4 .

[0142] At the same time, the fourth cycle prediction data obtained by extrapolating the model are compared with the measured data, such as Figure 10 The predicted result for the fourth cycle curve is 1.0153g, with a relative error of only 1.53% compared to the measured data of 1g. The predicted fourth cycle result based on the test data from the first three cycles is close to the measured result, demonstrating that the method used in this example to determine the loss of interlayer silicone grease is effective and accurate, and can reflect the changing pattern of silicone grease weight loss in TR modules.

[0143] The target silicone grease parameters were fitted using all the data in the preset data set, and the estimated result of the target silicone grease parameter B was updated to 3.0555×10 -6 , and the interlayer silicone grease loss of the radar component is obtained. The corresponding fitting curve of the interlayer silicone grease loss is as follows: Figure 11 The interlayer silicone grease loss is expressed as follows:

[0144] Δm(t)=-3.8498×10 -4 t 2 +1.07×10 -2 t 3 / 2 -1.07×10 -2 t+0.2967t 1 / 2

[0145] According to the parameter information in Table 2 and the target silicone grease parameters, the corresponding relationship of heat dissipation change is determined, and the required parameter information is summarized to obtain Table 4.

[0146] Table 4

[0147]

[0148] The corresponding relationship of heat dissipation change is expressed by the formula:

[0149]

[0150] It is believed that when the interlayer thermal conductivity of the TR component drops to 50% of the initial value, the heat dissipation performance does not meet the normal working requirements. Based on the corresponding relationship of heat dissipation change, the 50% interlayer thermal conductivity threshold is used as the degradation failure threshold to predict the life of the TR component. The remaining service life is 9.0265 years. The degradation trajectory of the TR component during service time is as follows: Figure 12 shown.

[0151] This example proposes a new ideal model for interlayer silicone grease in the modeling of TR module thermal performance degradation. This model divides the interlayer silicone grease "drying-out zone" into three layers: the silicone oil volatilization drying-out zone, the silicone grease loss zone, and the silicone oil volatilization drying-out zone. Furthermore, an innovative physical modeling approach, combining the modified Lucas-Washburn equation with the classic volatilization model, enables accurate simulation of thermal performance degradation. This approach differs from traditional statistically based lifespan prediction models, which often rely on large amounts of experimental data and struggle to accurately model in complex environments.

[0152] In addition, this embodiment proposes to construct a correlation model of "silicone grease loss weight → area of ​​the "dry area" between layers → heat dissipation performance of the TR component". The heat dissipation performance of the TR component can be indirectly obtained through the weight loss method, which greatly reduces the test difficulty and can effectively reduce the test cost.

[0153] Through this innovative modeling approach, this embodiment can achieve modeling and analysis of TR component performance degradation with less test data, thereby improving the accuracy and efficiency of prediction.

[0154] It should be noted that the method of the embodiments of the present disclosure can be performed by a single device, such as a computer or server. The method of the embodiments of the present disclosure can also be applied in a distributed scenario, where multiple devices cooperate to perform the method. In such a distributed scenario, one of the multiple devices may only perform one or more steps of the method of the embodiments of the present disclosure, and the multiple devices will interact with each other to complete the method.

[0155] It should be noted that the above description is limited to some embodiments of the present disclosure. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recited in the claims may be performed in an order different from that described in the above embodiments and still achieve the desired results. Furthermore, the processes depicted in the accompanying drawings do not necessarily require the specific order or sequential order shown to achieve the desired results. In certain embodiments, multitasking and parallel processing are also possible or may be advantageous.

[0156] Based on the same inventive concept, corresponding to any of the above-mentioned embodiments and methods, the present disclosure further provides a device for determining the life of a radar component.

[0157] refer to Figure 13 , Figure 13 The life determination device of a radar component of an embodiment specifically includes:

[0158] The data acquisition module 201 is configured to acquire a thermal conductivity coefficient of a radar component, wherein the radar component includes a heat dissipation structure, the heat dissipation structure including a component heat dissipation layer, a thermal grease layer, and a vapor chamber layer, the thermal grease layer including a normal region and a dry region, wherein the normal region is a region where no interlayer grease loss has occurred, and the dry region is a region where interlayer grease loss has occurred;

[0159] an area determination module 202 configured to determine an amount of silicone grease loss between layers of the radar assembly, and determine a first area corresponding to the dry region according to the amount of silicone grease loss between layers;

[0160] The remaining time determination module 203 is configured to obtain the total area of ​​the thermal grease layer and determine the remaining usage time of the radar component according to the first area, the total area and the thermal conductivity.

[0161] In some embodiments, the thermal conductivity includes a first thermal conductivity of a normal region and a second thermal conductivity of a dry region, and the remaining time determination module 203 is specifically configured as follows:

[0162] Determining a heat dissipation change correspondence relationship based on the first thermal conductivity and the second thermal conductivity, wherein the heat dissipation change correspondence relationship is a correspondence relationship between heat dissipation capacity and usage time during use of the radar component;

[0163] A preset interlayer thermal conductivity threshold is obtained, and the remaining service life of the radar component is determined according to the heat dissipation change correspondence and the interlayer thermal conductivity threshold.

[0164] In some embodiments, the remaining time determination module 203 is specifically configured to:

[0165] Subtracting the total area from the first area to obtain an area difference;

[0166] Performing a ratio processing on the area difference and the total area to obtain a first area weight value corresponding to the normal area;

[0167] Performing ratio processing on the first area and the total area to obtain a second area weight value corresponding to the dry area;

[0168] The first thermal conductivity and the second thermal conductivity are weighted according to the first area weight value and the second area weight value to obtain a heat dissipation change correspondence relationship, wherein the heat dissipation change correspondence relationship is expressed by the formula:

[0169]

[0170] Among them, k eff is the interlayer thermal conductivity of the radar component, k eff1 is the first thermal conductivity, k eff2 is the second thermal conductivity, A0 is the total area, and A2 is the first area.

[0171] In some embodiments, the area determination module 202 is specifically configured to:

[0172] Obtaining a silicone grease density in the thermal grease layer, and determining a silicone grease loss amount based on the silicone grease density, wherein the silicone grease loss amount is a loss caused by silicone grease being squeezed out of the thermal grease layer during use of the radar component;

[0173] determining a silicone oil flow rate in the thermal grease layer, and determining a silicone grease volatilization loss amount based on the silicone oil flow rate, wherein the silicone grease volatilization loss amount is a loss caused by volatilization of the silicone grease in the thermal grease layer during use of the radar component;

[0174] The loss amount of the silicone grease runoff and the loss amount of the silicone grease volatilization are added together to obtain the loss amount of the silicone grease between layers of the radar component.

[0175] In some embodiments, the area determination module 202 is further configured to:

[0176] The grease density in the thermal grease layer is obtained, and the grease loss amount is determined according to the grease density, wherein the grease loss amount is expressed by the formula:

[0177] Δm l (t)=h1A2(t)ρ

[0178] Where ρ is the density of silicone grease, h1 is the first thickness corresponding to the silicone grease loss area, Δm l (t) is the loss of silicone grease.

[0179] In some embodiments, the area determination module 202 is further configured to:

[0180] Obtaining a preset liquid phase pressure and a gas phase pressure, and determining the silicone oil flow rate in the thermal grease layer according to the liquid phase pressure and the gas phase pressure, wherein the silicone oil flow rate is expressed by the formula:

[0181]

[0182] Where j is the silicone oil rate, p l With p g are the liquid phase pressure and gas phase pressure respectively, M is the average molar mass of silicone oil components, R is the gas constant, T l is the liquidus temperature, k e is the evaporation-condensation time correction factor;

[0183] The volatilization loss of silicone grease is determined according to the silicone oil flow rate, wherein the volatilization loss of silicone grease is expressed by the formula:

[0184]

[0185] Where, Δm e (t) is the volatilization loss of silicone grease, and A2 is the first area.

[0186] In some embodiments, the area determination module 202 is further configured to:

[0187] The loss amount of the silicone grease is added to the loss amount of the silicone grease volatilization to obtain the loss amount of the interlayer silicone grease of the radar component, wherein the loss amount of the interlayer silicone grease is expressed by the formula:

[0188]

[0189] P2=2h1ρ

[0190] P1=(a+b)h1ρ

[0191] Wherein, Δm(t) is the loss of interlayer silicone grease, B is the target silicone grease parameter, h1 is the first thickness corresponding to the silicone grease loss area, a is the length of the initial rectangular area of ​​silicone grease, b is the width of the initial rectangular area of ​​silicone grease, and k e are preset parameters.

[0192] In some embodiments, the apparatus further includes a parameter determination module, and the parameter determination module is expressed using the formula:

[0193] A preset data set and a preset silicone grease penetration creep time correction coefficient are obtained, and the preset data set is fitted according to the interlayer silicone grease loss amount and the silicone grease penetration creep time correction coefficient to obtain a target silicone grease parameter, wherein the target silicone grease parameter is expressed by the formula:

[0194]

[0195] Where h1 is the first thickness corresponding to the silicone grease loss area, t is time, μ is the silicone grease viscosity, γ is the surface tension of the silicone grease, θ is the contact angle, and k c It is the correction factor of silicone grease penetration creep time.

[0196] In some embodiments, the area determination module 202 is specifically configured to:

[0197] According to the Washburn equation and the target silicone grease parameters, the shrinkage distance corresponding to the dry area is determined, wherein the shrinkage distance is expressed by the formula:

[0198]

[0199] Wherein, L is the shrinkage distance;

[0200] A first area corresponding to the dry region is determined according to the shrinkage distance, wherein the first area is expressed by the formula:

[0201]

[0202] In some embodiments, the data acquisition module 201 is specifically configured to:

[0203] Obtain the filler thermal conductivity, matrix thermal conductivity, and filler volume fraction of the silicone grease filler in the thermal grease layer, and determine a first thermal conductivity in a normal area based on the filler thermal conductivity, matrix thermal conductivity, and filler volume fraction. The first thermal conductivity is expressed as follows:

[0204]

[0205] Among them, k eff1 is the first thermal conductivity, k1 is the filler thermal conductivity, k2 is the matrix thermal conductivity, and ε1 is the volume fraction of the filler in the silicone grease.

[0206] In some embodiments, the dry area includes a silicone grease loss area and a silicone grease volatilization area, and the data acquisition module 201 is specifically configured to:

[0207] Obtaining the thermal conductivity of air, and using the thermal conductivity of air as the first initial thermal conductivity corresponding to the silicone grease loss area;

[0208] Obtaining a filler thermal conductivity and a filler volume fraction of the silicone grease filler in the thermally conductive silicone grease layer, and determining a second initial thermal conductivity corresponding to a silicone grease volatilization region based on the filler thermal conductivity, the air thermal conductivity, and the filler volume fraction;

[0209] Determine a first thickness corresponding to the silicone grease loss area and a second thickness corresponding to the silicone grease volatilization area. Perform equivalent thermal resistance conversion based on the first initial thermal conductivity, the second initial thermal conductivity, the first thickness, and the second thickness to obtain a second thermal conductivity of the dried-up area. The second thermal conductivity is expressed as follows:

[0210]

[0211] Wherein, h1 is the first thickness corresponding to the silicone grease loss area, h2 is the second thickness corresponding to the silicone grease volatilization area, k3 is the thermal conductivity of air, and H2 is the total thickness of the thermal grease layer.

[0212] For the convenience of description, the above devices are described as being functionally divided into various modules. Of course, when implementing the present disclosure, the functions of each module can be implemented in the same or multiple software and / or hardware.

[0213] The apparatus of the above embodiment is used to implement the corresponding radar component life determination method in any of the above embodiments, and has the beneficial effects of the corresponding method embodiment, which will not be described in detail here.

[0214] Based on the same inventive concept, corresponding to any of the above-mentioned embodiments and methods, the present disclosure further provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the program, the method for determining the life of a radar component described in any of the above-mentioned embodiments is implemented.

[0215] Figure 14 10 is a schematic diagram showing a more specific hardware structure of an electronic device provided in this embodiment. The device may include: a processor 1010, a memory 1020, an input / output interface 1030, a communication interface 1040, and a bus 1050. The processor 1010, the memory 1020, the input / output interface 1030, and the communication interface 1040 are communicatively connected to each other within the device via the bus 1050.

[0216] The processor 1010 can be implemented using a general-purpose CPU (Central Processing Unit), a microprocessor, an application-specific integrated circuit (ASIC), or one or more integrated circuits, and is used to execute relevant programs to implement the technical solutions provided in the embodiments of this specification.

[0217] The memory 1020 can be implemented in the form of ROM (Read Only Memory), RAM (Random Access Memory), static storage devices, dynamic storage devices, etc. The memory 1020 can store an operating system and other application programs. When the technical solutions provided in the embodiments of this specification are implemented through software or firmware, the relevant program code is stored in the memory 1020 and is called and executed by the processor 1010.

[0218] The input / output interface 1030 is used to connect input / output modules to implement information input and output. The input / output modules can be configured as components within the device (not shown in the figure) or can be externally connected to the device to provide corresponding functions. Input devices may include a keyboard, mouse, touch screen, microphone, various sensors, etc., and output devices may include a display, speaker, vibrator, indicator light, etc.

[0219] The communication interface 1040 is used to connect to a communication module (not shown) to enable communication between the device and other devices. The communication module can communicate via a wired method (such as USB, network cable, etc.) or a wireless method (such as mobile network, WiFi, Bluetooth, etc.).

[0220] The bus 1050 comprises a path for transmitting information between the various components of the device (eg, the processor 1010 , the memory 1020 , the input / output interface 1030 , and the communication interface 1040 ).

[0221] It should be noted that although the above device only shows the processor 1010, the memory 1020, the input / output interface 1030, the communication interface 1040, and the bus 1050, in a specific implementation, the device may also include other components necessary for normal operation. In addition, it will be understood by those skilled in the art that the above device may only include the components necessary to implement the embodiments of this specification, and does not necessarily include all the components shown in the figure.

[0222] The electronic device of the above embodiment is used to implement the corresponding radar component life determination method in any of the above embodiments, and has the beneficial effects of the corresponding method embodiment, which will not be repeated here.

[0223] Based on the same inventive concept, corresponding to any of the above-mentioned embodiments and methods, the present disclosure further provides a non-transitory computer-readable storage medium, wherein the non-transitory computer-readable storage medium stores computer instructions, and the computer instructions are used to enable the computer to execute the method for determining the life of a radar component as described in any of the above embodiments.

[0224] The computer-readable media of this embodiment include permanent and non-permanent, removable and non-removable media that can be used to store information by any method or technology. The information can be computer-readable instructions, data structures, program modules or other data. Examples of computer storage media include, but are not limited to, phase change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technology, read-only compact disc read-only memory (CD-ROM), digital versatile disc (DVD) or other optical storage, magnetic cassettes, magnetic tape magnetic disk storage or other magnetic storage devices or any other non-transmission media that can be used to store information that can be accessed by a computing device.

[0225] The computer instructions stored in the storage medium of the above embodiment are used to enable the computer to execute the method for determining the life of a radar component as described in any of the above embodiments, and have the beneficial effects of the corresponding method embodiments, which will not be repeated here.

[0226] It is understandable that before using the technical solutions of each embodiment of the present disclosure, the type, scope of use, usage scenarios, etc. of the personal information involved will be informed to the user in an appropriate manner, and the user's authorization will be obtained.

[0227] For example, in response to a user's active request, a prompt message is sent to the user to clearly inform the user that the requested operation will require the acquisition and use of the user's personal information. This allows the user to independently choose whether to provide personal information to the electronic device, application, server, storage medium, or other software or hardware that performs the operation of the disclosed technical solution based on the prompt message.

[0228] As an optional but non-limiting implementation, in response to a user's active request, the prompt information may be sent to the user in the form of a pop-up window, in which the prompt information may be presented in text form. Furthermore, the pop-up window may also contain a selection control for the user to select "agree" or "disagree" to provide personal information to the electronic device.

[0229] It is understandable that the above notification and user authorization process are merely illustrative and do not constitute a limitation on the implementation of the present disclosure. Other methods that comply with relevant laws and regulations may also be applied to the implementation of the present disclosure.

[0230] Those skilled in the art should understand that the discussion of any of the above embodiments is merely illustrative and is not intended to imply that the scope of the present disclosure (including the claims) is limited to these examples. Within the scope of the present disclosure, the technical features in the above embodiments or different embodiments may be combined, the steps may be implemented in any order, and there are many other variations of the different aspects of the embodiments of the present disclosure as described above, which are not provided in detail for the sake of simplicity.

[0231] In addition, to simplify the description and discussion, and so as not to obscure the embodiments of the present disclosure, known power / ground connections to integrated circuit (IC) chips and other components may or may not be shown in the provided figures. In addition, devices may be shown in the form of block diagrams to avoid obscuring the embodiments of the present disclosure, and this also takes into account the fact that the details of the implementation of these block diagram devices are highly dependent on the platform on which the embodiments of the present disclosure are to be implemented (i.e., these details should be fully within the purview of those skilled in the art). Where specific details (e.g., circuits) are set forth to describe exemplary embodiments of the present disclosure, it will be apparent to those skilled in the art that the embodiments of the present disclosure may be implemented without these specific details or with variations in these specific details. Therefore, these descriptions should be considered illustrative rather than restrictive.

[0232] Although the present disclosure has been described in conjunction with specific embodiments thereof, many alternatives, modifications, and variations of these embodiments will be apparent to those skilled in the art based on the foregoing description. For example, other memory architectures (e.g., dynamic RAM (DRAM)) may use the embodiments discussed.

[0233] The embodiments of the present disclosure are intended to cover all such substitutions, modifications, and variations that fall within the broad scope of the appended claims. Therefore, any omissions, modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the embodiments of the present disclosure should be included in the scope of protection of the present disclosure.

Claims

1. A method for determining the life of a radar component, characterized in that: include: Obtaining a thermal conductivity coefficient of a radar component, wherein the radar component includes a heat dissipation structure, the heat dissipation structure including a component heat dissipation layer, a thermal grease layer, and a vapor chamber layer, the thermal grease layer including a normal region and a dry region, wherein the normal region is a region where no interlayer grease loss has occurred, and the dry region is a region where interlayer grease loss has occurred; Determining an amount of interlayer silicone grease loss of the radar component, and determining a first area corresponding to the dry region according to the amount of interlayer silicone grease loss; A total area of ​​the thermal grease layer is obtained, and a remaining service life of the radar component is determined according to the first area, the total area, and the thermal conductivity.

2. The method according to claim 1, characterized in that The thermal conductivity coefficient includes a first thermal conductivity coefficient of a normal area and a second thermal conductivity coefficient of a dry area. The determining the remaining usage time of the radar component according to the first area, the total area, and the thermal conductivity includes: Determining a heat dissipation change correspondence relationship based on the first thermal conductivity and the second thermal conductivity, wherein the heat dissipation change correspondence relationship is a correspondence relationship between heat dissipation capacity and usage time during use of the radar component; A preset interlayer thermal conductivity threshold is obtained, and the remaining service life of the radar component is determined according to the heat dissipation change correspondence and the interlayer thermal conductivity threshold.

3. The method according to claim 2, characterized in that The determining of the corresponding relationship of heat dissipation changes according to the first thermal conductivity and the second thermal conductivity includes: Subtracting the total area from the first area to obtain an area difference; Performing a ratio processing on the area difference and the total area to obtain a first area weight value corresponding to the normal area; Performing ratio processing on the first area and the total area to obtain a second area weight value corresponding to the dry area; The first thermal conductivity and the second thermal conductivity are weighted according to the first area weight value and the second area weight value to obtain a heat dissipation change correspondence relationship, wherein the heat dissipation change correspondence relationship is expressed by the formula: Among them, k eff is the interlayer thermal conductivity of the radar component, k eff1 is the first thermal conductivity, k eff2 is the second thermal conductivity, A0 is the total area, and A2 is the first area.

4. The method according to claim 1, wherein Determining the loss of interlayer silicone grease of the radar component includes: Obtaining a silicone grease density in the thermal grease layer, and determining a silicone grease loss amount based on the silicone grease density, wherein the silicone grease loss amount is a loss caused by silicone grease being squeezed out of the thermal grease layer during use of the radar component; determining a silicone oil flow rate in the thermal grease layer, and determining a silicone grease volatilization loss amount based on the silicone oil flow rate, wherein the silicone grease volatilization loss amount is a loss caused by volatilization of the silicone grease in the thermal grease layer during use of the radar component; The loss amount of the silicone grease runoff and the loss amount of the silicone grease volatilization are added together to obtain the loss amount of the silicone grease between layers of the radar component.

5. The method according to claim 4, characterized in that The obtaining of the thermal grease density in the thermal grease layer and determining the amount of grease loss according to the grease density include: The grease density in the thermal grease layer is obtained, and the grease loss amount is determined according to the grease density, wherein the grease loss amount is expressed by the formula: Δm l (t)=h1A2(t)ρ Where ρ is the density of silicone grease, h1 is the first thickness corresponding to the silicone grease loss area, Δm l (t) is the loss of silicone grease.

6. The method according to claim 5, characterized in that Determining the silicone oil flow rate in the thermally conductive silicone grease layer and determining the silicone grease volatilization loss amount according to the silicone oil flow rate includes: Obtaining a preset liquid phase pressure and a gas phase pressure, and determining the silicone oil flow rate in the thermal grease layer according to the liquid phase pressure and the gas phase pressure, wherein the silicone oil flow rate is expressed by the formula: Where j is the silicone oil rate, p l With p g are the liquid phase pressure and gas phase pressure respectively, M is the average molar mass of silicone oil components, R is the gas constant, T l is the liquidus temperature, k e is the evaporation-condensation time correction factor; The volatilization loss of silicone grease is determined according to the silicone oil flow rate, wherein the volatilization loss of silicone grease is expressed by the formula: Where, Δm e (t) is the volatilization loss of silicone grease, and A2 is the first area.

7. The method according to claim 6, characterized in that The summing up of the silicone grease loss and the silicone grease volatilization loss to obtain the interlayer silicone grease loss of the radar assembly includes: The loss amount of the silicone grease is added to the loss amount of the silicone grease volatilization to obtain the loss amount of the interlayer silicone grease of the radar component, wherein the loss amount of the interlayer silicone grease is expressed by the formula: P2=2h1ρ P1=(a+b)h1ρ Wherein, Δm(t) is the loss of interlayer silicone grease, B is the target silicone grease parameter, h1 is the first thickness corresponding to the silicone grease loss area, a is the length of the initial rectangular area of ​​silicone grease, b is the width of the initial rectangular area of ​​silicone grease, and k e are preset parameters.

8. The method according to claim 7, characterized in that The target silicone grease parameters are determined as follows: A preset data set and a preset silicone grease penetration creep time correction coefficient are obtained, and the preset data set is fitted according to the interlayer silicone grease loss amount and the silicone grease penetration creep time correction coefficient to obtain a target silicone grease parameter, wherein the target silicone grease parameter is expressed by the formula: Where h1 is the first thickness corresponding to the silicone grease loss area, t is time, μ is the silicone grease viscosity, γ is the surface tension of the silicone grease, θ is the contact angle, and k c It is the correction factor of silicone grease penetration creep time.

9. The method according to claim 8, characterized in that The determining the first area corresponding to the dry region according to the loss of the interlayer silicone grease includes: According to the Washburn equation and the target silicone grease parameters, the shrinkage distance corresponding to the dry area is determined, wherein the shrinkage distance is expressed by the formula: Wherein, L is the shrinkage distance; A first area corresponding to the dry region is determined according to the shrinkage distance, wherein the first area is expressed by the formula:

10. The method according to claim 1, characterized in that The obtaining of the thermal conductivity of the radar component includes: Obtain the filler thermal conductivity, matrix thermal conductivity, and filler volume fraction of the silicone grease filler in the thermal grease layer, and determine a first thermal conductivity in a normal area based on the filler thermal conductivity, matrix thermal conductivity, and filler volume fraction. The first thermal conductivity is expressed as follows: Among them, k eff1 is the first thermal conductivity, k1 is the filler thermal conductivity, k2 is the matrix thermal conductivity, and ε1 is the volume fraction of the filler in the silicone grease.

11. The method according to claim 1, wherein The dry area includes the silicone grease loss area and the silicone grease volatilization area. The obtaining of the thermal conductivity of the radar component includes: Obtaining the thermal conductivity of air, and using the thermal conductivity of air as the first initial thermal conductivity corresponding to the silicone grease loss area; Obtaining a filler thermal conductivity and a filler volume fraction of the silicone grease filler in the thermally conductive silicone grease layer, and determining a second initial thermal conductivity corresponding to a silicone grease volatilization region based on the filler thermal conductivity, the air thermal conductivity, and the filler volume fraction; Determine a first thickness corresponding to the silicone grease loss area and a second thickness corresponding to the silicone grease volatilization area. Perform equivalent thermal resistance conversion based on the first initial thermal conductivity, the second initial thermal conductivity, the first thickness, and the second thickness to obtain a second thermal conductivity of the dried-up area. The second thermal conductivity is expressed as follows: Wherein, h1 is the first thickness corresponding to the silicone grease loss area, h2 is the second thickness corresponding to the silicone grease volatilization area, k3 is the thermal conductivity of air, and H2 is the total thickness of the thermal grease layer.

12. A device for determining the life of a radar component, characterized in that: include: a data acquisition module configured to acquire a thermal conductivity coefficient of a radar component, wherein the radar component includes a heat dissipation structure, the heat dissipation structure includes a component heat dissipation layer, a thermal grease layer, and a temperature vapor chamber layer, the thermal grease layer includes a normal region and a dry region, the normal region being a region where interlayer grease loss has not occurred, and the dry region being a region where interlayer grease loss has occurred; an area determination module configured to determine an amount of silicone grease loss between layers of the radar assembly, and determine a first area corresponding to the dry region according to the amount of silicone grease loss between layers; The remaining time determination module is configured to obtain the total area of ​​the thermal grease layer and determine the remaining usage time of the radar component according to the first area, the total area and the thermal conductivity.

13. An electronic device, characterized in that: The method comprises a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the program, the method according to any one of claims 1 to 11 is implemented.

14. A non-transitory computer-readable storage medium, characterized in that The non-transitory computer-readable storage medium stores computer instructions, and the computer instructions are used to cause a computer to execute the method according to any one of claims 1 to 11.

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