Temperature characteristics calculation method and device for reentry process of spherical nose cone vehicle

Abstract

The embodiments of the present invention relate to the technical field of temperature characteristic research, and in particular to a method and device for calculating the temperature characteristics of a spherical nose cone aircraft during its reentry process. The method comprises: obtaining a target model of a target spherical nose cone aircraft; calculating the head stagnation temperature of the target spherical nose cone aircraft at various flight altitudes during its reentry process based on the target model; determining a temperature estimation model for the target spherical nose cone aircraft based on the target model; and determining the surface temperature distribution of the target spherical nose cone aircraft at each flight altitude during its reentry process based on the head stagnation temperature of the target spherical nose cone aircraft at various flight altitudes and the temperature estimation model for the target spherical nose cone aircraft. This solution can improve the calculation speed of the temperature characteristics of the spherical nose cone aircraft during its reentry process.

Description

Technical Field

[0001] The embodiments of the present invention relate to the technical field of temperature characteristic research, and in particular to a method and device for calculating the temperature characteristics of a bulbous-nosed cone vehicle during a reentry process. Background Art

[0002] At present, the study of temperature characteristics of the re-entry process of the bulbous-nosed cone vehicle is of great significance. During the re-entry process of the bulbous-nosed cone vehicle, very complex aerodynamic heating phenomena will occur.

[0003] Existing methods for calculating the temperature characteristics of the reentry process of a bulbous-nosed cone vehicle are mostly numerical simulation methods. Although numerical simulation methods can more accurately calculate the temperature characteristics caused by aerodynamic thermal effects, the calculation time of this method is relatively long and it is not suitable for situations where high calculation speed requirements are required in daily research.

[0004] Therefore, a new method for calculating the temperature characteristics of the reentry process of a spherical-nosed cone vehicle is urgently needed. Summary of the Invention

[0005] In order to reduce the calculation time of the temperature characteristics of a bulbous-nosed cone vehicle during a re-entry process, an embodiment of the present invention provides a method and apparatus for calculating the temperature characteristics of a bulbous-nosed cone vehicle during a re-entry process.

[0006] In a first aspect, an embodiment of the present invention provides a method for calculating temperature characteristics of a bulbous-nosed cone vehicle during a reentry process, comprising:

[0007] Obtain the target model of the target ball-nosed cone aircraft;

[0008] Calculating the head stagnation temperature of the target bulbous-nosed cone vehicle at various flight altitudes during the reentry process according to the target model;

[0009] Determine a temperature estimation model of the target spherical nose cone aircraft according to the target model;

[0010] According to the head stagnation point temperature of the target spherical nose cone aircraft at various flight altitudes and the temperature estimation model of the target spherical nose cone aircraft, the surface temperature distribution of the target spherical nose cone aircraft at each flight altitude during the reentry process is determined respectively.

[0011] Preferably, the step of calculating the head stagnation temperature of the target bulbous-nosed cone vehicle at various flight altitudes during the reentry process according to the target model includes:

[0012] For each flight altitude of the target ball-nosed cone vehicle during the reentry process, the following operations are performed:

[0013] Determining the flight speed of the target spherical nose cone aircraft at the current flight altitude;

[0014] Determining a stagnation point heat flux at the head of the target spherical nose-conical aircraft at the current flight altitude according to the target model, the current flight altitude, and the flight speed of the target spherical nose-conical aircraft at the current flight altitude;

[0015] The stagnation point temperature of the head of the target spherical nose-conical aircraft at the current flight altitude is determined according to the stagnation point heat flux of the head of the target spherical nose-conical aircraft at the current flight altitude.

[0016] Preferably, the head stagnation point heat flux of the target spherical nose cone aircraft at the current flight altitude is calculated by the following formula:

[0017]

[0018] Where q is the head stagnation heat flux, R is the spherical head radius of the target spherical nose cone aircraft, V * and ρ * are the preset reference speed and reference density, U ∞ is the flight speed of the target spherical nose cone aircraft at the current flight altitude, ρ ∞ is the atmospheric density corresponding to the current flight altitude.

[0019] Preferably, determining the stagnation point temperature of the head of the target spherical nose-conical aircraft at the current flight altitude according to the stagnation point heat flux of the head of the target spherical nose-conical aircraft at the current flight altitude includes:

[0020] Determining an initial shell temperature of the target bulbous-nosed cone vehicle; the initial shell temperature is the shell temperature of the target bulbous-nosed cone vehicle before the reentry process begins;

[0021] Determining the shell thickness of the target spherical nose cone aircraft according to the target model;

[0022] Determining the duration of the target bulbous-nosed cone vehicle entering a reentry process at a current flight altitude;

[0023] The stagnation point temperature of the head of the target spherical nose-cone aircraft at the current flight altitude is determined based on the stagnation point heat flux at the head of the target spherical nose-cone aircraft at the current flight altitude, the initial shell temperature, the shell thickness and the duration of the target spherical nose-cone aircraft entering the re-entry process at the current flight altitude.

[0024] Preferably, the stagnation point temperature of the head of the target spherical nose cone aircraft at the current flight altitude is calculated by the following formula:

[0025]

[0026]

[0027] Wherein, l is the shell thickness, x is the position variable in the shell thickness direction, x∈[0,l]; T is the temperature at each shell thickness position of the head stagnation point, T0 is the initial shell temperature, t is the time length of the target spherical nose cone vehicle entering the reentry process at the current flight altitude, λ is the shell thermal conductivity of the target spherical nose cone vehicle, ρ is the shell density, c is the shell specific heat, and q is the head stagnation point heat flux of the target spherical nose cone vehicle at the current flight altitude.

[0028] Preferably, determining a target ball-nosed cone aircraft temperature estimation model according to the target model includes:

[0029] According to the numerical simulation results of different types of spherical nose cone aircraft, a temperature estimation model library of spherical nose cone aircraft is constructed;

[0030] A target spherical nose cone aircraft temperature estimation model is determined according to the target model and the spherical nose cone aircraft temperature estimation model library.

[0031] Preferably, the surface temperature distribution of the target spherical nose cone vehicle at each flight altitude during the reentry process is calculated by the following formula:

[0032] T(x)=A1·exp(-x / t1)+A2·exp(-x / t2)+t0+T l

[0033] Where, T(x) is the surface temperature distribution of the target spherical nose cone vehicle at the current flight altitude during the reentry process, x is the distance between each position on the surface of the target spherical nose cone vehicle and the head stationary point, and T l is the head stagnation point temperature of the target spherical nose cone aircraft at the current flight altitude, and A1, A2, t1, t2, and t0 are constants of the temperature estimation model of the target spherical nose cone aircraft.

[0034] In a second aspect, an embodiment of the present invention further provides a device for calculating temperature characteristics of a bulbous-nosed cone vehicle during a reentry process, comprising:

[0035] An acquisition unit, used for acquiring a target model of a target spherical nose cone aircraft;

[0036] a calculation unit, configured to calculate, according to the target model, the head stagnation point temperature of the target bulbous-nosed cone vehicle at various flight altitudes during the reentry process;

[0037] A determination unit, configured to determine a temperature estimation model of a target spherical nose cone aircraft according to the target model;

[0038] The estimation unit is used to determine the surface temperature distribution of the target spherical nose cone aircraft at each flight altitude during the re-entry process according to the head stagnation point temperature of the target spherical nose cone aircraft at each flight altitude and the temperature estimation model of the target spherical nose cone aircraft.

[0039] In a third aspect, an embodiment of the present invention further provides a computing device, including a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, the method described in any embodiment of this specification is implemented.

[0040] In a fourth aspect, an embodiment of the present invention further provides a computer-readable storage medium having a computer program stored thereon, which, when executed in a computer, enables the computer to execute the method described in any embodiment of this specification.

[0041] An embodiment of the present invention provides a method and device for calculating the temperature characteristics of a spherical nose-cone aircraft during a re-entry process. First, the target model of the target spherical nose-cone aircraft to be calculated is obtained, and according to the target model, the head stagnation point temperature of the target spherical nose-cone aircraft at various flight altitudes during the re-entry process is calculated; then, a temperature estimation model of the target spherical nose-cone aircraft is determined according to the target model; finally, according to the head stagnation point temperature of the target spherical nose-cone aircraft at various flight altitudes and the temperature estimation model of the target spherical nose-cone aircraft, the surface temperature distribution of the target spherical nose-cone aircraft at each flight altitude during the re-entry process is determined respectively, so as to improve the calculation speed of the temperature characteristics of the spherical nose-cone aircraft during the re-entry process. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0043] Figure 1 This is a flow chart of a method for calculating temperature characteristics of a bulbous-nosed cone vehicle during a reentry process provided by one embodiment of the present invention;

[0044] Figure 2 This is a schematic diagram of a model of a spherical-nosed cone aircraft provided by one embodiment of the present invention;

[0045] Figure 3 This is a schematic diagram of the temperature change at the head stagnation point of a bulbous-nosed cone vehicle during reentry provided by one embodiment of the present invention;

[0046] Figure 4 This is a hardware architecture diagram of an electronic device provided by one embodiment of the present invention;

[0047] Figure 5 This is a structural diagram of a temperature characteristic calculation device for a spherical-nosed cone vehicle re-entry process provided by one embodiment of the present invention. DETAILED DESCRIPTION

[0048] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0049] As previously mentioned, during the reentry of a bulbous-nosed cone vehicle, the airflow rubs intensely against the vehicle's surface. The kinetic energy lost in the boundary layer of the vehicle's surface is converted into heat, causing the temperature of the airflow in the boundary layer to rise. Simultaneously, the gas surrounding the vehicle is subjected to intense compression, reaching a high temperature. Consequently, the high-temperature gas transfers heat to the vehicle's walls, causing aerodynamic heating. Aerodynamic heating is a complex phenomenon, related not only to flight conditions, such as speed and altitude, but also to the flow field structure. Existing numerical simulation methods can relatively accurately simulate the temperature distribution caused by aerodynamic heating during the reentry of a target bulbous-nosed cone vehicle, but these methods require a long computational time. Therefore, numerical simulation methods are not suitable for routine research where high computational speed is required.

[0050] To address the aforementioned technical issues, the inventors considered pre-setting temperature prediction models for various bulbous-nosed aircraft models. Based on the target model of the target bulbous-nosed aircraft to be calculated, the target bulbous-nosed aircraft temperature prediction model corresponding to that target bulbous-nosed aircraft was determined. This temperature prediction model could then be used to calculate the surface temperature distribution of the target bulbous-nosed aircraft at each flight altitude during reentry. Therefore, this solution can reduce the calculation time for the temperature characteristics of the bulbous-nosed aircraft during reentry, improving the calculation speed.

[0051] The specific implementation of the above concept is described below.

[0052] Please refer to Figure 1 The embodiment of the present invention provides a method for calculating the temperature characteristics of a bulbous-nosed cone vehicle during a reentry process, the method comprising:

[0053] Step 100: Obtain the target model of the target spherical nose cone aircraft;

[0054] Step 102: Calculate the head stagnation point temperature of the target bulbous-nosed cone vehicle at various flight altitudes during the reentry process according to the target model;

[0055] Step 104: determining a temperature estimation model of the target spherical nose cone aircraft according to the target model;

[0056] Step 106: Based on the head stagnation point temperature of the target bulbous-nosed cone vehicle at each flight altitude and the target bulbous-nosed cone vehicle temperature estimation model, the surface temperature distribution of the target bulbous-nosed cone vehicle at each flight altitude during the reentry process is determined respectively.

[0057] In an embodiment of the present invention, a target model of a target spherical nose-cone aircraft to be calculated is first obtained, and based on the target model, the stagnation point temperature of the head of the target spherical nose-cone aircraft at various flight altitudes during the re-entry process is calculated; then, a temperature estimation model of the target spherical nose-cone aircraft is determined based on the target model; finally, based on the stagnation point temperature of the head of the target spherical nose-cone aircraft at various flight altitudes and the temperature estimation model of the target spherical nose-cone aircraft, the surface temperature distribution of the target spherical nose-cone aircraft at each flight altitude during the re-entry process is determined respectively, so as to improve the calculation speed of the temperature characteristics of the spherical nose-cone aircraft during the re-entry process.

[0058] Described below Figure 1 How to perform the steps shown.

[0059] For step 100:

[0060] like Figure 2 The figure shows a schematic diagram of a ball-nosed cone aircraft model provided in this embodiment.

[0061] In an embodiment of the present invention, different models of spherical-nosed cone aircraft have different sizes, shell materials and shell thicknesses. Therefore, by obtaining the target model of the target spherical-nosed cone aircraft to be calculated, the shape, size, shell material and shell thickness of the target spherical-nosed cone aircraft can be determined.

[0062] Regarding step 102:

[0063] In some implementations, step 102 may include the following steps S1-S3:

[0064] Step S1, for each flight altitude of the target spherical nose cone aircraft during the reentry process, the following steps are performed: determining the flight speed of the target spherical nose cone aircraft at the current flight altitude;

[0065] Step S2, determining the head stagnation point heat flux of the target spherical nose cone aircraft at the current flight altitude according to the target model, the current flight altitude, and the flight speed of the target spherical nose cone aircraft at the current flight altitude;

[0066] Step S3, determining the stagnation point temperature of the head of the target spherical nose-conical aircraft at the current flight altitude according to the stagnation point heat flux of the head of the target spherical nose-conical aircraft at the current flight altitude.

[0067] In this embodiment, the flight trajectory of the target spherical nose-cone aircraft during the re-entry process can be obtained, and for the flight altitude of each trajectory point in the flight trajectory of the target spherical nose-cone aircraft, the following are performed: determining the flight speed of the target spherical nose-cone aircraft at the current trajectory point, that is, the flight speed at the current flight altitude; then, the head stagnation point heat flux of the target spherical nose-cone aircraft at the current flight altitude can be determined based on the target model, the current flight altitude and the flight speed of the target spherical nose-cone aircraft at the current flight altitude; finally, based on the head stagnation point heat flux at the current flight altitude, the head stagnation point temperature of the target spherical nose-cone aircraft at the current flight altitude can be determined, thereby determining the head stagnation point temperature of the target spherical nose-cone aircraft at various flight altitudes during the re-entry process.

[0068] In some embodiments, the head stagnation point heat flux of the target spherical nose cone aircraft at the current flight altitude in step S2 is calculated by the following formula:

[0069]

[0070] Where q is the head stagnation point heat flux, unit is W / m 2 ; R is the radius of the ball head of the target ball head cone aircraft, in m, V * and ρ * are the preset reference speed and reference density, U ∞ is the flight speed of the target spherical nose cone aircraft at the current flight altitude, ρ ∞ is the atmospheric density corresponding to the current flight altitude.

[0071] Among them, the head stationary point of the target ball nose cone aircraft is as follows Figure 2 Point P shown; the ball head radius R can be determined according to the target model of the target ball cone aircraft; the reference speed V in this embodiment * and the reference density ρ * V * =7900m / s and ρ * =1.2263kg / m 3 .

[0072] It should be noted that the method for determining the flight altitude of the target spherical nose cone aircraft during the re-entry process can determine the altitude of each flight trajectory point as each flight altitude, or the number of flight altitude values can be determined according to needs, so no specific limitation is made here.

[0073] In some embodiments, step S3 may include:

[0074] determining an initial shell temperature of the target bulbous-nosed aircraft; the initial shell temperature is the shell temperature of the target bulbous-nosed aircraft before the reentry process begins;

[0075] Determine the shell thickness of the target ball-nosed cone aircraft according to the target model;

[0076] Determine the time it takes for the target bulbous-nosed vehicle to enter the reentry process at the current flight altitude;

[0077] The stagnation point temperature of the head of the target spherical nose cone aircraft at the current flight altitude is determined according to the head stagnation point heat flux, initial shell temperature, shell thickness and the duration of the target spherical nose cone aircraft entering the reentry process at the current flight altitude.

[0078] For example, if the target bulbous nose cone aircraft enters the atmosphere at a flight altitude of 100km and begins the re-entry process, when the current flight altitude is 90km, the duration of the target bulbous nose cone aircraft entering the re-entry process is the flight time from 100km to 90km. If the current flight altitude is 80km, the duration of the target bulbous nose cone aircraft entering the re-entry process is the flight time from 100km to 80km.

[0079] Then, based on the head stagnation heat flux, initial shell temperature, shell thickness and the duration of the target spherical nose cone aircraft entering the re-entry process at the current flight altitude calculated in step S2, the head stagnation temperature of the target spherical nose cone aircraft at the current flight altitude can be determined.

[0080] In some embodiments, the head stagnation temperature of the target bulbous-nosed aircraft at the current flight altitude is calculated using the following formula:

[0081]

[0082]

[0083] where l is the shell thickness, x is the position variable in the shell thickness direction, x∈[0,l]; T is the temperature at each shell thickness position of the head stagnation point, T0 is the initial shell temperature, t is the time it takes for the target spherical nose cone vehicle to enter the reentry process at the current flight altitude, λ is the shell thermal conductivity of the target spherical nose cone vehicle, ρ is the shell density, c is the shell specific heat, and q is the heat flux at the head stagnation point of the target spherical nose cone vehicle at the current flight altitude.

[0084] In this embodiment, before the target spherical nose cone aircraft begins the reentry process, the shell temperatures at various thickness positions at the head stagnation point of the target spherical nose cone aircraft are the same. When the reentry process begins, aerodynamic heating occurs on the shell surface of the target spherical nose cone aircraft. Then, the temperature of the outer surface of the shell at the head stagnation point of the target spherical nose cone aircraft begins to change. The shell thickness of the target spherical nose cone aircraft is sufficient to ensure that the inner surface of the shell at the head stagnation point of the target spherical nose cone aircraft will not change due to the temperature change of the outer surface of the shell. Therefore, when x=0, it represents the innermost layer of the shell. The temperature of the innermost layer of the shell will not change, so it is equal to the initial shell temperature, that is, T=T0. When x=1, it represents the outermost layer of the shell. The temperature of the outermost layer of the shell needs to be determined based on the heat flux of the head stagnation point of the target spherical nose cone aircraft at the current flight altitude obtained in step 2. According to the heat flux at the head stagnation point of the target spherical nose cone aircraft at the current flight altitude, the transient heat conduction differential equation shown in the above formula can be solved for the head stagnation point, and the temperature at each shell thickness position of the head stagnation point of the target spherical nose cone aircraft at the current flight altitude can be obtained.

[0085] However, in this embodiment, the required head stagnation temperature is the temperature of the outermost layer of the shell of the target spherical nose cone aircraft at the head stagnation point. Therefore, the head stagnation temperature of the target spherical nose cone aircraft at the current flight altitude is T calculated according to the above formula. l .

[0086] Regarding step 104:

[0087] In some implementations, step 104 may include:

[0088] According to the numerical simulation results of different types of spherical nose cone aircraft, a temperature estimation model library of spherical nose cone aircraft is constructed;

[0089] The target spherical nose cone aircraft temperature estimation model is determined according to the target model and the spherical nose cone aircraft temperature estimation model library.

[0090] In this embodiment, a numerical simulation method can be used in advance to simulate and calculate the temperature distribution caused by the aerodynamic heating phenomenon during the re-entry process of each model of bulbous-nosed cone aircraft, and a bulbous-nosed cone aircraft temperature prediction model corresponding to each model of bulbous-nosed cone aircraft can be constructed based on the numerical simulation results, so as to establish a bulbous-nosed cone aircraft temperature prediction model library; then, according to the target model, the target bulbous-nosed cone aircraft temperature prediction model can be determined from the bulbous-nosed cone aircraft temperature prediction model library.

[0091] Regarding step 106:

[0092] In some embodiments, the surface temperature distribution of the target bulbous-nosed vehicle at each flight altitude during the reentry process is calculated using the following formula:

[0093] T(x)=A1·exp(-x / t1)+A2·exp(-x / t2)+t0+T l

[0094] Where T(x) is the surface temperature distribution of the target spherical nose cone vehicle at the current flight altitude during the reentry process, x is the distance between each position on the surface of the target spherical nose cone vehicle and the head stationary point, and T l is the stagnation point temperature of the head of the target spherical nose cone aircraft at the current flight altitude, and A1, A2, t1, t2, and t0 are the constants of the temperature estimation model of the target spherical nose cone aircraft.

[0095] In this embodiment, after determining the target bulbous-nosed conical aircraft temperature estimation model according to step 104, the values of constants A1, A2, t1, t2, and t0 can be determined. Based on the stagnation point temperature of the head of the target bulbous-nosed conical aircraft at the current flight altitude obtained in step 102, the temperature of each position on the surface of the target bulbous-nosed conical aircraft can be calculated, that is, the surface temperature distribution of the target bulbous-nosed conical aircraft at the current flight altitude. Similarly, based on the stagnation point temperature of the head of the target bulbous-nosed conical aircraft at each flight altitude, the surface temperature distribution of the target bulbous-nosed conical aircraft at each flight altitude during the reentry process can be calculated.

[0096] For example, if the model diagram of the target spherical nose cone aircraft is as follows Figure 2 As shown, the spherical head radius of the target spherical nose cone aircraft is r=1500mm, the semi-cone angle θ=9°, and the overall length is L=1295mm.

[0097] Next, the temperature characteristics of the target bulbous-nosed cone vehicle during its re-entry process are calculated using the calculation method of the embodiment of the present invention.

[0098] Because Earth's dense atmosphere generally exists below 100 km, the primary consideration is aerodynamic heating caused by friction between the airflow and the surface of the target bulbous-nosed aircraft below 100 km. The flight trajectory of the target bulbous-nosed aircraft is obtained. If the target bulbous-nosed aircraft enters the atmosphere with an initial shell temperature of 300 K, it will gradually descend from an altitude of 100 km.

[0099] According to step 102, the temperature change of the head stagnation point on the shell surface of the target ball-nosed cone vehicle during the re-entry process can be calculated, such as Figure 3 shown.

[0100] According to step 104, the target ball-nosed cone aircraft temperature estimation model can be determined as:

[0101] T(x)=101.23017·exp(-x / 0.06418)+101.21496·exp(-x / 0.06302)-197+T l

[0102] will be as Figure 3 Each head stagnation point temperature shown is input into the temperature estimation model of the target spherical nose cone aircraft, and the surface temperature distribution at each flight altitude corresponding to each head stagnation point temperature can be calculated, that is, the temperature characteristic calculation result of the target spherical nose cone aircraft re-entry process.

[0103] against Figure 2 The target spherical nose cone aircraft shown uses the numerical simulation method and step 102 of the embodiment of the present invention (hereinafter referred to as the fast calculation method) to calculate the head stagnation point temperature at different flight altitudes, as shown in Table 1 below.

[0104] Table 1 Head stagnation temperature at different heights

[0105]

[0106] As shown in the table above, the calculation error between the rapid calculation results and the numerical simulation results for the head stagnation point temperature at different heights is within 12%. However, the numerical simulation method takes about 3 hours to calculate, while the rapid calculation method of the embodiment of the present invention takes about 5 minutes.

[0107] In summary, this scheme can reduce the calculation time of the temperature characteristics of the ball-nosed cone vehicle reentry process and improve the calculation speed while meeting the accuracy requirements.

[0108] like Figure 4 、 Figure 5 As shown, an embodiment of the present invention provides a device for calculating the temperature characteristics of a ball-nosed cone vehicle during reentry. The device embodiment can be implemented by software, hardware, or a combination of software and hardware. From the hardware level, Figure 4 The figure shows a hardware architecture diagram of a computing device where a temperature characteristic calculation device for a ball-nosed cone vehicle reentry process is located, in addition to Figure 4 In addition to the processor, memory, network interface, and non-volatile memory shown, the computing device in the embodiment may also include other hardware, such as a forwarding chip responsible for processing messages, etc. Taking software implementation as an example, Figure 5 As shown, as a device in a logical sense, it is formed by the CPU of the computing device in which it is located reading the corresponding computer program in the non-volatile memory into the internal memory and running it.

[0109] like Figure 5As shown, this embodiment provides a temperature characteristic calculation device for a bulbous-nosed cone vehicle reentry process, comprising:

[0110] An acquisition unit 501 is used to acquire a target model of a target spherical nose cone aircraft;

[0111] The calculation unit 502 is used to calculate the head stagnation point temperature of the target bulbous-nosed cone vehicle at various flight altitudes during the reentry process according to the target model;

[0112] A determination unit 503 is configured to determine a temperature estimation model of a target spherical nose cone aircraft according to a target model;

[0113] The estimation unit 504 is used to determine the surface temperature distribution of the target bulbous-nosed cone aircraft at each flight altitude during the reentry process based on the head stagnation point temperature of the target bulbous-nosed cone aircraft at each flight altitude and the target bulbous-nosed cone aircraft temperature estimation model.

[0114] In one embodiment of the present invention, the computing unit 502 is configured to execute:

[0115] For each flight altitude of the target ball-nosed cone vehicle during the reentry process, the following operations are performed:

[0116] Determine the flight speed of the target spherical nose cone aircraft at the current flight altitude;

[0117] Determine the stagnation point heat flux of the head of the target spherical nose cone aircraft at the current flight altitude according to the target model, the current flight altitude and the flight speed of the target spherical nose cone aircraft at the current flight altitude;

[0118] The stagnation point temperature of the head of the target spherical nose cone aircraft at the current flight altitude is determined according to the stagnation point heat flux of the head of the target spherical nose cone aircraft at the current flight altitude.

[0119] In one embodiment of the present invention, in the calculation unit 502, the head stagnation point heat flux of the target spherical nose cone aircraft at the current flight altitude is calculated by the following formula:

[0120]

[0121] Where q is the head stagnation heat flux, R is the spherical head radius of the target spherical nose cone aircraft, V * and ρ * are the preset reference speed and reference density, U ∞ is the flight speed of the target spherical nose cone aircraft at the current flight altitude, ρ ∞ is the atmospheric density corresponding to the current flight altitude.

[0122] In one embodiment of the present invention, when determining the stagnation point temperature of the head of the target spherical nose-conical aircraft at the current flight altitude based on the stagnation point heat flux of the head of the target spherical nose-conical aircraft at the current flight altitude, the calculation unit 502 is configured to:

[0123] determining an initial shell temperature of the target bulbous-nosed aircraft; the initial shell temperature is the shell temperature of the target bulbous-nosed aircraft before the reentry process begins;

[0124] Determine the shell thickness of the target ball-nosed cone aircraft according to the target model;

[0125] Determine the time it takes for the target bulbous-nosed vehicle to enter the reentry process at the current flight altitude;

[0126] The stagnation point temperature of the head of the target spherical nose cone aircraft at the current flight altitude is determined according to the head stagnation point heat flux, initial shell temperature, shell thickness and the duration of the target spherical nose cone aircraft entering the reentry process at the current flight altitude.

[0127] In one embodiment of the present invention, in the calculation unit 502, the head stagnation temperature of the target spherical nose cone aircraft at the current flight altitude is calculated by the following formula:

[0128]

[0129]

[0130] where l is the shell thickness, x is the position variable in the shell thickness direction, x∈[0,l]; T is the temperature at each shell thickness position of the head stagnation point, T0 is the initial shell temperature, t is the time it takes for the target spherical nose cone vehicle to enter the reentry process at the current flight altitude, λ is the shell thermal conductivity of the target spherical nose cone vehicle, ρ is the shell density, c is the shell specific heat, and q is the heat flux at the head stagnation point of the target spherical nose cone vehicle at the current flight altitude.

[0131] In one embodiment of the present invention, the determining unit 503 is configured to execute:

[0132] According to the numerical simulation results of different types of spherical nose cone aircraft, a temperature estimation model library of spherical nose cone aircraft is constructed;

[0133] The target spherical nose cone aircraft temperature estimation model is determined according to the target model and the spherical nose cone aircraft temperature estimation model library.

[0134] In one embodiment of the present invention, in the estimation unit 504, the surface temperature distribution of the target bulbous-nosed cone vehicle at each flight altitude during the reentry process is calculated using the following formula:

[0135] T(x)=A1·exp(-x / t1)+A2·exp(-x / t2)+t0+T l

[0136] Where T(x) is the surface temperature distribution of the target spherical nose cone vehicle at the current flight altitude during the reentry process, x is the distance between each position on the surface of the target spherical nose cone vehicle and the head stationary point, and T l is the stagnation point temperature of the head of the target spherical nose cone aircraft at the current flight altitude, and A1, A2, t1, t2, and t0 are the constants of the temperature estimation model of the target spherical nose cone aircraft.

[0137] It should be understood that the structure illustrated in the embodiments of the present invention does not constitute a specific limitation on a device for calculating temperature characteristics during a bulbous-nosed conical vehicle reentry. In other embodiments of the present invention, a device for calculating temperature characteristics during a bulbous-nosed conical vehicle reentry may include more or fewer components than illustrated, or may combine or separate certain components, or employ a different component arrangement. The illustrated components may be implemented in hardware, software, or a combination of software and hardware.

[0138] The information interaction, execution process, etc. between the modules in the above-mentioned device are based on the same concept as the embodiment of the method of the present invention. For specific contents, please refer to the description in the embodiment of the method of the present invention and will not be repeated here.

[0139] An embodiment of the present invention also provides a computing device including a memory and a processor, wherein a computer program is stored in the memory. When the processor executes the computer program, a method for calculating the temperature characteristics of a spherical-nosed cone vehicle reentry process in any embodiment of the present invention is implemented.

[0140] An embodiment of the present invention also provides a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, the processor executes a method for calculating the temperature characteristics of a spherical-nosed cone vehicle reentry process in any embodiment of the present invention.

[0141] Specifically, a system or device equipped with a storage medium can be provided, on which software program codes that implement the functions of any of the above-mentioned embodiments are stored, and a computer (or CPU or MPU) of the system or device can be enabled to read and execute the program codes stored in the storage medium.

[0142] In this case, the program code itself read from the storage medium can realize the function of any one of the above-mentioned embodiments, and thus the program code and the storage medium storing the program code constitute part of the present invention.

[0143] Examples of storage media for providing program code include floppy disks, hard disks, magneto-optical disks, optical disks (such as CD-ROM, CD-R, CD-RW, DVD-ROM, DVD-RAM, DVD-RW, DVD+RW), magnetic tapes, non-volatile memory cards, and ROMs. Alternatively, the program code can be downloaded from a server computer via a communication network.

[0144] In addition, it should be clear that the functions of any of the above embodiments can be achieved not only by executing the program code read by the computer, but also by enabling the operating system operating on the computer to complete part or all of the actual operations based on the instructions of the program code.

[0145] In addition, it can be understood that the program code read from the storage medium is written into a memory provided in an expansion board inserted into the computer or into a memory provided in an expansion module connected to the computer, and then based on the instructions of the program code, a CPU installed on the expansion board or expansion module is enabled to perform part or all of the actual operations, thereby realizing the functions of any of the above embodiments.

[0146] It should be noted that, in this article, relational terms such as first and second are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply the existence of any such actual relationship or order between these entities or operations. Moreover, the terms "comprises", "comprising" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprising a ..." do not exclude the presence of other identical factors in the process, method, article or device comprising the elements.

[0147] Those skilled in the art will understand that all or part of the steps of implementing the above-mentioned method embodiment can be completed by hardware related to program instructions, and the aforementioned program can be stored in a computer-readable storage medium. When the program is executed, it executes the steps of the above-mentioned method embodiment; and the aforementioned storage medium includes: ROM, RAM, disk or optical disk, etc. Various media that can store program codes.

[0148] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A method for calculating the temperature characteristics of a spherical-nosed cone vehicle during reentry, characterized in that: include: Obtain the target model of the target ball-nosed cone aircraft; Calculating the head stagnation temperature of the target bulbous-nosed cone vehicle at various flight altitudes during the reentry process according to the target model; Determine a temperature estimation model of the target spherical nose cone aircraft according to the target model; Determining the surface temperature distribution of the target spherical nose-cone vehicle at each flight altitude during the reentry process according to the head stagnation point temperature of the target spherical nose-cone vehicle at each flight altitude and the temperature estimation model of the target spherical nose-cone vehicle; The step of calculating the head stagnation temperature of the target bulbous-nosed cone vehicle at various flight altitudes during the reentry process according to the target model includes: For each flight altitude of the target ball-nosed cone vehicle during the reentry process, the following operations are performed: Determining the flight speed of the target spherical nose cone aircraft at the current flight altitude; Determining a stagnation point heat flux at the head of the target spherical nose-conical aircraft at the current flight altitude according to the target model, the current flight altitude, and the flight speed of the target spherical nose-conical aircraft at the current flight altitude; determining a stagnation point temperature of the head of the target spherical nose-conical aircraft at the current flight altitude according to a stagnation point heat flux of the head of the target spherical nose-conical aircraft at the current flight altitude; The head stagnation temperature of the target spherical nose cone aircraft at the current flight altitude is calculated by the following formula: Where, is the shell thickness, is the position variable in the shell thickness direction, ; is the temperature at each shell thickness position of the head stagnation point, is the initial shell temperature, is the time it takes for the target ball-nosed cone vehicle to enter the reentry process at the current flight altitude, is the shell thermal conductivity of the target spherical nose cone aircraft, is the shell density, is the shell specific heat, The heat flux at the head stagnation point of the target spherical nose cone aircraft at the current flight altitude; The surface temperature distribution of the target spherical nose cone vehicle at each flight altitude during the reentry process is calculated by the following formula: Where, is the surface temperature distribution of the target spherical nose cone vehicle at the current flight altitude during the reentry process, is the distance between each position on the surface of the target spherical nose cone aircraft and the head stationary point, is the head stagnation temperature of the target spherical nose cone aircraft at the current flight altitude, 、 、 、 、 is the constant of the temperature estimation model of the target spherical nose cone aircraft.

2. The method according to claim 1, characterized in that The head stagnation point heat flux of the target spherical nose cone aircraft at the current flight altitude is calculated by the following formula: Where, is the head stagnation heat flow, is the spherical head radius of the target spherical nose cone aircraft, and are the preset reference speed and reference density, is the flight speed of the target spherical nose cone aircraft at the current flight altitude, is the atmospheric density corresponding to the current flight altitude.

3. The method according to claim 1, characterized in that Determining the stagnation point temperature of the head of the target spherical nose-conical aircraft at the current flight altitude according to the stagnation point heat flux of the head of the target spherical nose-conical aircraft at the current flight altitude includes: Determining an initial shell temperature of the target bulbous-nosed cone vehicle; the initial shell temperature is the shell temperature of the target bulbous-nosed cone vehicle before the reentry process begins; Determining the shell thickness of the target spherical nose cone aircraft according to the target model; Determining the duration of the target bulbous-nosed cone vehicle entering a reentry process at a current flight altitude; The stagnation point temperature of the head of the target spherical nose-cone aircraft at the current flight altitude is determined based on the stagnation point heat flux at the head of the target spherical nose-cone aircraft at the current flight altitude, the initial shell temperature, the shell thickness and the duration of the target spherical nose-cone aircraft entering the re-entry process at the current flight altitude.

4. The method according to claim 1, wherein Determining a target ball-nosed cone aircraft temperature estimation model according to the target model includes: According to the numerical simulation results of different types of spherical nose cone aircraft, a temperature estimation model library of spherical nose cone aircraft is constructed; A target spherical nose cone aircraft temperature estimation model is determined according to the target model and the spherical nose cone aircraft temperature estimation model library.

5. A device for calculating the temperature characteristics of a bulbous-nosed cone vehicle during reentry, for implementing the method according to any one of claims 1 to 4, characterized in that: include: An acquisition unit, used for acquiring a target model of a target spherical nose cone aircraft; a calculation unit, configured to calculate, according to the target model, the head stagnation point temperature of the target bulbous-nosed cone vehicle at various flight altitudes during the reentry process; A determination unit, configured to determine a temperature estimation model of a target spherical nose cone aircraft according to the target model; The estimation unit is used to determine the surface temperature distribution of the target spherical nose cone aircraft at each flight altitude during the re-entry process according to the head stagnation point temperature of the target spherical nose cone aircraft at each flight altitude and the temperature estimation model of the target spherical nose cone aircraft.

6. A computing device comprising a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, the method according to any one of claims 1 to 4 is implemented.

7. A computer-readable storage medium having a computer program stored thereon, which, when executed in a computer, causes the computer to execute the method according to any one of claims 1 to 4.

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