Aerostat construction method, device, aerostat, equipment and readable storage medium

Abstract

The present invention provides an aerostat construction method, device, aerostat, equipment and readable storage medium. The aerostat construction method includes: determining a first physical parameter according to a first atmospheric parameter, the first atmospheric parameter being determined based on a first preset level flight altitude; determining a second physical parameter according to a second atmospheric parameter, the second atmospheric parameter being determined based on a second preset level flight altitude; determining the net weight of the aerostat according to the first atmospheric parameter, the first physical parameter and the second physical parameter; and constructing the aerostat according to the first physical parameter, the second physical parameter and the net weight of the aerostat. The aerostat constructed according to the determined first physical parameter, the second physical parameter and the net weight of the aerostat can achieve non-leakage of the buoyancy gas in the zero-pressure balloon within the first preset level flight altitude and the second preset level flight altitude, thereby improving the stability of the aerostat.

Description

Technical Field

[0001] The present invention relates to the technical field of aerostats, and in particular to an aerostat construction method, an apparatus, an aerostat, a device and a readable storage medium. Background Art

[0002] Existing aerostats include zero-pressure balloons. Due to the characteristics of zero-pressure balloons, the zero-pressure balloons in existing aerostats will cause buoyancy gas leakage, making it difficult to achieve stable flight, which greatly limits the development of aerostats. Summary of the invention

[0003] The present invention provides an aerostat construction method, an apparatus, an aerostat, a device and a readable storage medium, which are used to solve the technical problem of poor stability of existing aerostats.

[0004] The present invention provides a method for building an aerostat, the method comprising:

[0005] Determining a first physical parameter according to a first atmospheric parameter, wherein the first atmospheric parameter is determined based on a first preset level flight altitude;

[0006] determining a second physical parameter according to a second atmospheric parameter, wherein the second atmospheric parameter is determined based on a second preset level flight altitude;

[0007] determining a net weight of the aerostat based on the first atmospheric parameter, the first physical parameter, and the second physical parameter;

[0008] The aerostat is constructed according to the first physical parameter, the second physical parameter and the net weight of the aerostat.

[0009] According to a method for building an aerostat provided by the present invention, the first atmospheric parameter includes a first atmospheric pressure, a first atmospheric density and a first atmospheric temperature; the first physical parameter includes a first gas density; and the step of determining the first physical parameter according to the first atmospheric parameter includes:

[0010] The first gas density is calculated according to the preset atmospheric molar mass, the first preset gas molar mass, the first atmospheric pressure, the first atmospheric density and the first atmospheric temperature.

[0011] According to a method for building an aerostat provided by the present invention, the second atmospheric parameter includes a second atmospheric pressure, a second atmospheric density, and a second atmospheric temperature; the second physical parameter includes a second gas density; and the step of determining the second physical parameter according to the second atmospheric parameter includes:

[0012] The second gas density is calculated according to a preset universal gas constant, the preset atmospheric molar mass, the second atmospheric pressure, the second atmospheric density and the second atmospheric temperature.

[0013] According to a method for building an aerostat provided by the present invention, the step of determining the net weight of the aerostat according to the first atmospheric parameter, the first physical parameter and the second physical parameter comprises:

[0014] The net weight of the aerostat is determined according to the first atmospheric density, the first gas density, and the second gas density.

[0015] According to a method for building an aerostat provided by the present invention, the step of building the aerostat according to the first physical parameter, the second physical parameter and the net weight of the aerostat comprises:

[0016] Building an aerostat based on a zero-pressure balloon corresponding to the first gas density and a super-pressure balloon corresponding to the second gas density;

[0017] The net weight of the aerostat includes the net weight of the zero-pressure balloon and the net weight of the super-pressure balloon.

[0018] According to a method for building an aerostat provided by the present invention, after the step of building the aerostat according to the first physical parameter, the second physical parameter and the net weight of the aerostat, the method further comprises:

[0019] Obtaining a maximum overpressure according to the second gas density, the preset universal gas constant, the preset atmospheric molar mass, the preset gas temperature, and the first atmospheric pressure;

[0020] The feasibility of the aerostat is determined according to the maximum overpressure.

[0021] The present invention also provides an aerostat construction device, comprising:

[0022] A first physical parameter determination module, configured to determine a first physical parameter according to a first atmospheric parameter, wherein the first atmospheric parameter is determined based on a first preset level flight altitude;

[0023] A second physical parameter determination module, configured to determine a second physical parameter according to a second atmospheric parameter, wherein the second atmospheric parameter is determined based on a second preset level flight altitude;

[0024] an aerostat net weight determination module, configured to determine the aerostat net weight based on the first atmospheric parameter, the first physical parameter, and the second physical parameter;

[0025] The aerostat construction module is used to construct the aerostat according to the first physical parameter, the second physical parameter and the net weight of the aerostat.

[0026] The present invention also provides an aerostat, which comprises a zero-pressure balloon and a super-pressure balloon; the super-pressure balloon is suspended at the bottom of the zero-pressure balloon.

[0027] The present invention also provides an electronic device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the program, any of the above-mentioned methods for constructing an aerostat is implemented.

[0028] The present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon, and when the computer program is executed by a processor, the aerostat building method described in any one of the above is implemented.

[0029] The airship construction method, device, airship, equipment and readable storage medium provided by the present invention respectively determine the first physical parameter and the second physical parameter through the first atmospheric parameter determined by the first preset level flight altitude and the second atmospheric parameter determined by the second preset level flight altitude; further determine the net weight of the airship according to the first atmospheric parameter, the first physical parameter and the second physical parameter; finally, build the airship according to the first physical parameter, the second physical parameter and the net weight of the airship. Since it is assumed that the first preset level flight altitude is the height at which the zero-pressure balloon corresponding to the first physical parameter is just fully inflated, and the floating and sinking balance of the airship is achieved at the first preset level flight altitude by the super-pressure balloon corresponding to the second physical parameter, the airship constructed according to the first physical parameter, the second physical parameter and the net weight of the airship can achieve non-leakage of the buoyancy gas in the zero-pressure balloon, thereby improving the stability of the airship. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the technical solutions in the present invention or 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 creative work.

[0031] Figure 1 This is one of the flow diagrams of the method for building an aerostat provided by the present invention;

[0032] Figure 2 It is a schematic diagram of the structure of the aerostat provided by the present invention;

[0033] Figure 3 This is the second flow chart of the method for building an aerostat provided by the present invention;

[0034] Figure 4 It is a structural schematic diagram of the aerostat construction device provided by the present invention;

[0035] Figure 5It is a structural schematic diagram of the electronic device provided by the present invention. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0037] Combine the following Figure 1-Figure 3 The aerostat construction method of the present invention is described.

[0038] Please refer to Figure 1 The present invention provides a method for building an aerostat, the method comprising:

[0039] Step 100, determining a first physical parameter according to a first atmospheric parameter, wherein the first atmospheric parameter is determined based on a first preset level flight altitude;

[0040] Specifically, the aerostat construction method provided by the present invention is applied to Figure 2 The aerostat shown in the figure is used in a quasi-zero wind layer, wherein the quasi-zero wind layer refers to an east-west wind conversion layer with a relatively low wind speed in the lower part of the stratosphere. Assuming that the wind is easterly at a height h1 above the sea level in the quasi-zero wind layer, h1 is the first preset level flight altitude in this embodiment, and the atmospheric parameters at the first preset level flight altitude are the first atmospheric parameters in this embodiment, and the first atmospheric parameters include the first atmospheric pressure P a1 、First atmospheric density ρ a1 and the first atmospheric temperature T a1 The purpose of obtaining the first atmospheric parameter is to calculate the density ρ of the buoyant gas in the zero-pressure balloon through the first atmospheric parameter. g1 The specific calculation method will be described in detail below.

[0041] Step 200, determining a second physical parameter according to a second atmospheric parameter, wherein the second atmospheric parameter is determined based on a second preset level flight altitude;

[0042] Assume that the wind is westerly at a height h2 above the sea level in the quasi-zero wind layer, and h2 is the second preset level flight altitude in this embodiment, wherein the first preset level flight altitude is greater than the second preset level flight altitude in this embodiment. The atmospheric parameters at the second preset level flight altitude are the second atmospheric parameters in this embodiment, and the second atmospheric parameters include the second atmospheric pressure P a2 、Second atmospheric density ρ a2 and the second atmospheric temperature T a2The purpose of obtaining the second atmospheric parameters is to calculate the density ρ of the buoyant gas in the superpressure balloon through the second atmospheric parameters. as The specific calculation method will be described in detail below.

[0043] Step 300, determining the net weight of the aerostat according to the first atmospheric parameter, the first physical parameter and the second physical parameter;

[0044] Specifically, this embodiment also needs to include the air molar mass M a and the preset constant of the universal gas constant R, where M a =28.96g / mol, R = 8.314J / (mol.K), from the ideal gas state equation we know:

[0045] P a1 M a =ρ a1 RT a1 (1)

[0046] The first physical parameters in this embodiment include the first superheat, the first gas pressure, the first gas density, the first gas temperature, the first volume, the first sphere mass, the first gas mass and the first gas molar mass. For the buoyant gas in the zero-pressure balloon at h1:

[0047] P g1 M g =ρ g1 RT g1 (2)

[0048] P g1 is the first gas pressure, that is, the pressure of the buoyant gas in the zero-pressure balloon; M g is the molar mass of the first gas, that is, the molar mass of the buoyant gas in the zero-pressure balloon; ρ g1 is the first gas density, that is, the density of the buoyant gas in the zero-pressure balloon, T g1 is the first gas temperature, that is, the temperature of the floating gas in the zero-pressure balloon. According to the properties of the zero-pressure balloon, the first atmospheric pressure is equal to the first gas pressure, and the first gas temperature is equal to the first atmospheric temperature and the first superheat ΔT. z The density of the buoyant gas in the zero-pressure balloon can be obtained by combining the above formula (1) with the above formula (2) g1 .

[0049]

[0050] V z is the first volume mentioned above, that is, the volume of the zero-pressure balloon, m g is the mass of the first gas mentioned above, that is, the mass of the buoyant gas in the zero-pressure balloon.

[0051]

[0052] When the first gas density is calculated, the relationship between the first gas mass and the first volume can be determined according to the above formula (4).

[0053] The second physical parameters in this embodiment include the target overpressure, the second gas pressure, the second gas density, the second gas temperature, the second sphere mass, the second volume, and the second gas mass. Assume that the overpressure of the superpressure balloon to maintain its shape (i.e., the above target overpressure) is ΔP s , determine that the gas temperatures inside and outside the zero-pressure balloon and the super-pressure balloon are the same, and the second gas temperature is the gas temperature inside the super-pressure balloon. Then the air pressure inside the super-pressure balloon (i.e. the second gas pressure) is P as , the second gas pressure is equal to the sum of the second atmospheric pressure and the target overpressure. The air density ρ in the overpressure balloon can be obtained from the ideal gas state equation as , that is, the second gas density mentioned above:

[0054]

[0055] The volume of the superpressure balloon (i.e. the second volume mentioned above) is V s , the mass of air that needs to be filled into the superpressure balloon (i.e. the mass of the second gas mentioned above) is m a :

[0056]

[0057] According to the above formula (5), the relationship between the second gas mass and the second volume can be determined.

[0058] The mass of the zero-pressure balloon (i.e. the mass of the first sphere mentioned above) is m z , the mass of the superpressure balloon (i.e. the mass of the second sphere mentioned above) is m s , the mass of the ballast is m. From the floating and sinking balance of the aerostat during the day, we can get:

[0059] (V z +V s )ρ a1 -m g -m a -m z -m s -m=0 (6)

[0060] According to the above formula (6), when ρ is known a1 , m g With V z The relationship between a With V sBased on the relationship between z , m s The relationship between and m, the net weight of the aerostat in this embodiment includes m z , m s and m, because m z The first physical parameter corresponding to the zero-pressure balloon, m s The second physical parameter corresponding to the superpressure balloon, ρ a1 It belongs to the first atmospheric parameter, so the net weight of the aerostat can be calculated according to the above formula (6).

[0061] Step 400: construct an aerostat according to the first physical parameter, the second physical parameter and the net weight of the aerostat.

[0062] Specifically, after the first preset level flight altitude and the second preset level flight altitude are determined, a zero-pressure balloon of a certain volume and weight is selected, that is, a first volume V z and the mass of the first sphere m z Determine, at the first gas density ρ g1 and the first volume V z If the first gas mass m is known, the first gas mass m can be determined according to the above formula (4) g , that is, to determine the mass of the buoyant gas filled in the zero-pressure balloon. z and the mass of the first sphere m z In this case, the volume V of the superpressure balloon can be determined s and the deadweight of the superpressure balloon m s That is, first determine the volume V of the superpressure balloon s In this case, you can use m a With V s The relationship between the second gas mass m is calculated. a Substituting all the determined parameters into the above formula (6) we can get the superpressure balloon weight m s , a zero-pressure balloon that meets the above-mentioned first physical parameter, a super-pressure balloon that meets the above-mentioned second physical parameter, and a zero-pressure balloon, a super-pressure balloon, and ballast that meet the net weight of the airship are built, and an airship that can float stably in the quasi-zero wind layer can be obtained. Since the first preset level flight altitude is the altitude at which the zero-pressure balloon is completely inflated, and the floating and sinking balance of the airship is achieved by the super-pressure balloon at the first preset level flight altitude, the airship built according to the above parameters can achieve non-leakage of the buoyancy gas in the zero-pressure balloon, thereby improving the stability of the airship.

[0063] In this embodiment, the first physical parameter and the second physical parameter are determined respectively by the first atmospheric parameter determined by the first preset level flight altitude and the second atmospheric parameter determined by the second preset level flight altitude; the net weight of the airship is further determined according to the first atmospheric parameter, the first physical parameter and the second physical parameter; finally, the airship is built according to the first physical parameter, the second physical parameter and the net weight of the airship. Since it is assumed that the first preset level flight altitude is the height at which the zero-pressure balloon corresponding to the first physical parameter is just fully inflated, and the floating and sinking balance of the airship is achieved at the first preset level flight altitude by the super-pressure balloon corresponding to the second physical parameter, the airship built according to the first physical parameter, the second physical parameter and the net weight of the airship can achieve no leakage of the buoyancy gas in the zero-pressure balloon, improve the stability of the airship, have better height stability, and can achieve longer flight time. In combination with the wind field environment at the first preset level flight altitude and the wind field environment at the second preset level flight altitude, it can achieve residence in a specific area.

[0064] In one embodiment, the aerostat construction method provided in the embodiment of the present application may further include:

[0065] Step 110, calculating the first gas density according to a preset atmospheric molar mass, a first preset gas molar mass, the first atmospheric pressure, the first atmospheric density and the first atmospheric temperature.

[0066] Specifically, the first physical parameter in this embodiment includes a first superheat, a first gas pressure, a first gas density, a first gas temperature, a first volume, a first sphere mass, a first gas mass, and a first gas molar mass. According to the properties of the zero-pressure balloon, the first atmospheric pressure is equal to the first gas pressure, and the first gas temperature is equal to the first atmospheric temperature and the first superheat ΔT. z The density of the buoyant gas in the zero-pressure balloon can be obtained by combining the above formula (1) with the above formula (2) g1 According to the above formula (3), the first gas density can be obtained.

[0067] In this embodiment, the first gas density in the first physical parameter is determined by the first atmospheric parameter, which lays a foundation for subsequently building a stable aerostat according to the obtained first physical parameter and other parameters.

[0068] In one embodiment, the aerostat construction method provided in the embodiment of the present application may further include:

[0069] Step 210, calculating the second gas density according to a preset universal gas constant, the preset atmospheric molar mass, the second atmospheric pressure, the second atmospheric density and the second atmospheric temperature.

[0070] The second physical parameters in this embodiment include the target overpressure, the second gas pressure, the second gas density, the second gas temperature, the second sphere mass, the second volume, and the second gas mass. Assume that the overpressure of the superpressure balloon to maintain its shape (i.e., the above target overpressure) is ΔP s , determine that the gas temperatures inside and outside the zero-pressure balloon and the super-pressure balloon are the same, and the second gas temperature is the gas temperature inside the super-pressure balloon. Then the air pressure inside the super-pressure balloon (i.e. the second gas pressure) is P as , the second gas pressure is equal to the sum of the second atmospheric pressure and the target overpressure. The air density ρ in the overpressure balloon can be obtained from the ideal gas state equation as .

[0071] In this embodiment, the second gas density in the second physical parameter is determined by the second atmospheric parameter, which lays a foundation for subsequently building a stable aerostat according to the obtained second physical parameter and other parameters.

[0072] In one embodiment, the aerostat construction method provided in the embodiment of the present application may further include:

[0073] Step 310: Determine the net weight of the aerostat according to the first atmospheric density, the first gas density, and the second gas density.

[0074] The volume of the superpressure balloon (i.e. the second volume mentioned above) is V s , the mass of air that needs to be filled into the superpressure balloon (i.e. the mass of the second gas mentioned above) is m a According to the above formula (5), the relationship between the second gas mass and the second volume can be determined. The mass of the zero-pressure balloon (i.e., the mass of the first sphere) is m z , the mass of the superpressure balloon (i.e. the mass of the second sphere mentioned above) is m s , the mass of the ballast is m. According to the above formula (6), when ρ is known a1 , m g With V z The relationship between a With V s Based on the relationship between z , m s The relationship between and m, the net weight of the aerostat in this embodiment includes m z , m s and m, because m z The first physical parameter corresponding to the zero-pressure balloon, m s The second physical parameter corresponding to the superpressure balloon, ρ a1 It belongs to the first atmospheric parameter, so the net weight of the aerostat can be calculated according to the above formula (6).

[0075] This embodiment determines the net weight of the aerostat through the first atmospheric parameter, the first physical parameter and the second physical parameter, which lays a foundation for subsequently building a stable aerostat according to these relationships.

[0076] In one embodiment, the aerostat construction method provided in the embodiment of the present application may further include:

[0077] Step 410: construct an airship based on the zero-pressure balloon corresponding to the first gas density and the super-pressure balloon corresponding to the second gas density; the net weight of the airship includes the net weight of the zero-pressure balloon and the net weight of the super-pressure balloon.

[0078] Specifically, after the first preset level flight altitude and the second preset level flight altitude are determined, a zero-pressure balloon that meets the first physical parameter, a super-pressure balloon that meets the second physical parameter, and a zero-pressure balloon, a super-pressure balloon, and ballast that meet the net weight of the airship are selected for construction, and an airship that can stably float in the quasi-zero wind layer can be obtained. Since the first preset level flight altitude is the height at which the zero-pressure balloon is just fully inflated, and the floating and sinking balance of the airship is achieved by the super-pressure balloon at the first preset level flight altitude, the airship constructed according to the above parameters can achieve non-leakage of the buoyancy gas in the zero-pressure balloon, thereby improving the stability of the airship.

[0079] In this embodiment, when the first physical parameter, the second physical parameter and the net weight of the aerostat are determined, the aerostat that can stably float in the quasi-zero wind layer can be obtained by building a zero-pressure balloon that meets the first physical parameter, a super-pressure balloon that meets the second physical parameter, and a zero-pressure balloon, a super-pressure balloon and ballast that meet the net weight of the aerostat. Since the first preset level flight altitude is the altitude at which the zero-pressure balloon is completely inflated, and the floating and sinking balance of the aerostat is achieved by the super-pressure balloon at the first preset level flight altitude, the aerostat built according to the above parameters can achieve non-leakage of the buoyancy gas in the zero-pressure balloon, thereby improving the stability of the aerostat.

[0080] Please refer to Figure 4 In one embodiment, the method for constructing an aerostat provided in the embodiment of the present application may further include:

[0081] Step 500, obtaining a maximum overpressure according to the second gas density, the preset universal gas constant, the preset atmospheric molar mass, the preset gas temperature and the first atmospheric pressure;

[0082] Step 600: Determine the feasibility of the aerostat according to the maximum overpressure.

[0083] Specifically, the superheat of the superpressure balloon is ΔT s The maximum overpressure of the superpressure balloon (i.e., the maximum overpressure in this embodiment) is ΔP max :

[0084]

[0085] According to the second gas density ρ in the above formula (7) as , universal gas constant R, atmospheric molar mass M a , the second superheat ΔT s , the first atmospheric temperature T a1 And the first atmospheric pressure P a1 , the maximum overpressure ΔP is calculated max . According to the obtained maximum superpressure of the superpressure balloon, the feasibility of the aerostat (medium superpressure balloon) is determined.

[0086] This embodiment calculates the maximum overpressure of the superpressure balloon during the day through the second gas density, the universal gas constant, the atmospheric molar mass, the second superheat, the first atmospheric temperature and the first atmospheric pressure, providing data verification for the feasibility of selecting the superpressure balloon.

[0087] The aerostat construction device provided by the present invention is described below. The aerostat construction device described below and the aerostat construction method described above can be referred to each other.

[0088] Please refer to Figure 4 The present invention also provides an aerostat construction device, comprising:

[0089] A first physical parameter determination module 401, configured to determine a first physical parameter according to a first atmospheric parameter, wherein the first atmospheric parameter is determined based on a first preset level flight altitude;

[0090] A second physical parameter determination module 402, configured to determine a second physical parameter according to a second atmospheric parameter, wherein the second atmospheric parameter is determined based on a second preset level flight altitude;

[0091] an aerostat net weight determination module 403, configured to determine the aerostat net weight according to the first atmospheric parameter, the first physical parameter and the second physical parameter;

[0092] The aerostat construction module 404 is used to construct the aerostat according to the first physical parameter, the second physical parameter and the net weight of the aerostat.

[0093] Optionally, the first atmospheric parameter includes a first atmospheric pressure, a first atmospheric density and a first atmospheric temperature; the first physical parameter includes a first gas density; and the first physical parameter determination module includes:

[0094] The first gas density calculation unit is used to calculate the first gas density according to the preset atmospheric molar mass, the first preset gas molar mass, the first atmospheric pressure, the first atmospheric density and the first atmospheric temperature.

[0095] Optionally, the second atmospheric parameter includes a second atmospheric pressure, a second atmospheric density and a second atmospheric temperature; the second physical parameter includes a second gas density; and the second physical parameter determination module includes:

[0096] The second gas density calculation unit is used to calculate the second gas density according to a preset universal gas constant, the preset atmospheric molar mass, the second atmospheric pressure, the second atmospheric density and the second atmospheric temperature.

[0097] Optionally, the aerostat net weight determination module comprises:

[0098] The aerostat net weight determination unit is used to determine the aerostat net weight according to the first atmospheric density, the first gas density and the second gas density.

[0099] Optionally, the aerostat construction module comprises:

[0100] The aerostat construction unit is used to construct the aerostat according to the zero-pressure balloon corresponding to the first gas density and the super-pressure balloon corresponding to the second gas density; the net weight of the aerostat includes the net weight of the zero-pressure balloon and the net weight of the super-pressure balloon.

[0101] Optionally, after the step of building the aerostat according to the first physical parameter, the second physical parameter and the net weight of the aerostat, the method further comprises:

[0102] a maximum overpressure determination module, configured to obtain a maximum overpressure according to the second gas density, the preset universal gas constant, the preset atmospheric molar mass, the preset gas temperature and the first atmospheric pressure;

[0103] The aerostat feasibility determination module is used to determine the feasibility of the aerostat according to the maximum overpressure.

[0104] Figure 5 An example of a physical structure diagram of an electronic device is shown in FIG. Figure 5 As shown, the electronic device may include: a processor (proceor) 510, a communication interface (Communication Interface) 520, a memory (memory) 530 and a communication bus 540, wherein the processor 510, the communication interface 520, and the memory 530 communicate with each other through the communication bus 540. The processor 510 may call the logic instructions in the memory 530 to execute the method for building an aerostat.

[0105] In addition, the logic instructions in the above-mentioned memory 530 can be implemented in the form of a software functional unit and can be stored in a computer-readable storage medium when it is sold or used as an independent product. Based on such an understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art or the part of the technical solution, can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Acce Memory), disk or optical disk and other media that can store program codes.

[0106] On the other hand, the present invention also provides an aerostat, which includes a zero-pressure balloon, a super-pressure balloon and ballast; wherein: the super-pressure balloon is suspended at the bottom of the zero-pressure balloon, and the ballast is suspended at the bottom of the super-pressure balloon.

[0107] On the other hand, the present invention further provides a non-transitory computer-readable storage medium having a computer program stored thereon, which is implemented when the computer program is executed by a processor to execute the aerostat building method provided by the above methods.

[0108] The device embodiments described above are merely illustrative, wherein the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. Ordinary technicians in this field can understand and implement it without paying creative labor.

[0109] Through the description of the above implementation methods, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus a necessary general hardware platform, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solution is essentially or the part that contributes to the prior art can be embodied in the form of a software product, and the computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a disk, an optical disk, etc., including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0110] 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 embodiments of the present invention.

Claims

1. A method for building an aerostat, characterized in that: include: Determining a first physical parameter according to a first atmospheric parameter, wherein the first atmospheric parameter is determined based on a first preset level flight altitude; the first atmospheric parameter includes a first atmospheric pressure, a first atmospheric density, and a first atmospheric temperature; and the first physical parameter includes a first gas density; determining a second physical parameter according to a second atmospheric parameter, wherein the second atmospheric parameter is determined based on a second preset level flight altitude; the second atmospheric parameter includes a second atmospheric pressure, a second atmospheric density, and a second atmospheric temperature; and the second physical parameter includes a second gas density; determining a net weight of the aerostat based on the first atmospheric parameter, the first physical parameter, and the second physical parameter; constructing an aerostat according to the first physical parameter, the second physical parameter, and the net weight of the aerostat; The step of determining the first physical parameter according to the first atmospheric parameter comprises: Calculating the first gas density according to a preset atmospheric molar mass, a first preset gas molar mass, the first atmospheric pressure, the first atmospheric density, and the first atmospheric temperature; The step of determining the second physical parameter according to the second atmospheric parameter comprises: Calculating the second gas density according to a preset universal gas constant, the preset atmospheric molar mass, the second atmospheric pressure, the second atmospheric density, and the second atmospheric temperature; The step of determining the net weight of the aerostat according to the first atmospheric parameter, the first physical parameter and the second physical parameter comprises: determining a net weight of the aerostat based on the first atmospheric density, the first gas density, and the second gas density; The step of building the aerostat according to the first physical parameter, the second physical parameter and the net weight of the aerostat comprises: Building an aerostat based on a zero-pressure balloon corresponding to the first gas density and a super-pressure balloon corresponding to the second gas density; The net weight of the aerostat includes the net weight of the zero-pressure balloon and the net weight of the super-pressure balloon; After the step of building the aerostat according to the first physical parameter, the second physical parameter and the net weight of the aerostat, the method further includes: Obtaining a maximum overpressure according to the second gas density, the preset universal gas constant, the preset atmospheric molar mass, the preset gas temperature, and the first atmospheric pressure; The feasibility of the aerostat is determined according to the maximum overpressure.

2. An aerostat construction device, characterized in that: include: A first physical parameter determination module, configured to determine a first physical parameter according to a first atmospheric parameter, wherein the first atmospheric parameter is determined based on a first preset level flight altitude; the first atmospheric parameter includes a first atmospheric pressure, a first atmospheric density, and a first atmospheric temperature; and the first physical parameter includes a first gas density; A second physical parameter determination module, configured to determine a second physical parameter according to a second atmospheric parameter, wherein the second atmospheric parameter is determined based on a second preset level flight altitude; the second atmospheric parameter comprises a second atmospheric pressure, a second atmospheric density, and a second atmospheric temperature; the second physical parameter comprises a second gas density; an aerostat net weight determination module, configured to determine the aerostat net weight based on the first atmospheric parameter, the first physical parameter, and the second physical parameter; an aerostat construction module, configured to construct an aerostat according to the first physical parameter, the second physical parameter and the net weight of the aerostat; The first physical parameter determination module comprises: a first gas density calculation unit, configured to calculate the first gas density according to a preset atmospheric molar mass, a first preset gas molar mass, the first atmospheric pressure, the first atmospheric density, and the first atmospheric temperature; The second physical parameter determination module includes: a second gas density calculation unit, configured to calculate the second gas density according to a preset universal gas constant, the preset atmospheric molar mass, a second atmospheric pressure, the second atmospheric density, and the second atmospheric temperature; The aerostat net weight determination module comprises: an aerostat net weight determination unit, configured to determine the aerostat net weight according to the first atmospheric density, the first gas density, and the second gas density; The aerostat building module comprises: an aerostat construction unit, configured to construct an aerostat according to a zero-pressure balloon corresponding to the first gas density and a super-pressure balloon corresponding to the second gas density; the net weight of the aerostat includes the net weight of the zero-pressure balloon and the net weight of the super-pressure balloon; The aerostat construction device further comprises: a maximum overpressure determination module, configured to obtain a maximum overpressure according to the second gas density, the preset universal gas constant, the preset atmospheric molar mass, the preset gas temperature and the first atmospheric pressure; The aerostat feasibility determination module is used to determine the feasibility of the aerostat according to the maximum overpressure.

3. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the program, the aerostat building method as claimed in claim 1 is implemented.

4. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the aerostat construction method as claimed in claim 1 is implemented.

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