Liquid-gas phase change ejection interior ballistics modeling method, simulation method and electronic equipment

Abstract

The present invention provides a liquid-gas phase-change catapult interior ballistics modeling method, simulation method, and electronic equipment. The liquid-gas phase-change catapult system of the present invention includes at least one phase-change power unit. The liquid-gas phase-change catapult interior ballistics modeling method includes dividing the liquid-gas phase-change catapult interior ballistics into a phase-change power unit flow model, an initial volume chamber energy model, and a projectile motion parameter model. The present invention constructs a liquid-gas phase-change catapult interior ballistics model comprising multiple phase-change power units. The phase-change device increases the operating time, which can achieve a predetermined speed without exceeding a limit when catapult overload control requirements are high. The method can also accurately calculate the changes in internal ballistic parameters during the expansion and operating process of a carbon dioxide phase-change catapult.

Description

Technical Field

[0001] The present invention belongs to the technical field of phase change launch, and in particular relates to a liquid-gas phase change catapult interior ballistics modeling method, a simulation method and electronic equipment. Background Art

[0002] Liquid carbon dioxide absorbs heat in a confined space, undergoing a supercritical phase transition to a gaseous state. This instantaneous vaporization produces high-pressure gas that can be used as the power source for catapults. This phase transition process can replace or supplement traditional solid-powder catapults, providing a more environmentally friendly and controllable energy source. The drastic phase changes and complex gas-liquid-solid multiphase flow during the carbon dioxide phase transition process make interior ballistic design challenging. Based on the basic principles of high-pressure launch technology and gas cannons, existing technologies have established an overall design for supercritical phase change launchers and a supercritical phase change gas cannon launch model. However, the energy change of the released working fluid from the supercritical phase change launcher to the final state requires consideration of the energy utilization rate to derive the work energy of the supercritical phase change power unit. This is then combined with the equation of motion of the initial chamber energy state and the load to derive the phase change catapult work model. Furthermore, launchers with a single supercritical phase change power unit have a short operating time and drastic energy changes, making them unsuitable for catapult systems with high requirements for catapult overload. Summary of the Invention

[0003] The purpose of the present invention is to address the deficiencies of the existing technology and provide a liquid-gas phase change catapult interior ballistic modeling method, simulation method and electronic equipment to more accurately calculate the interior ballistic parameters of the liquid-gas phase change catapult system.

[0004] In order to achieve the above object, the technical solution adopted by the present invention is:

[0005] A method for modeling the internal ballistics of a liquid-gas phase-change catapult is disclosed. The liquid-gas phase-change catapult system includes a phase-change power unit, an initial volume chamber, a launch tube, a projectile, and a tray. The phase-change power unit is provided with a plurality of projectiles. The projectile is disposed in the launch tube. The initial volume chamber is connected to the launch tube. A heat release source and liquid carbon dioxide are disposed inside the phase-change power unit. A pressure-releasing diaphragm is disposed at one end of the phase-change power unit connected to the initial volume chamber. A cross groove is disposed at the center of the pressure-releasing diaphragm. The high-pressure carbon dioxide mixture in the phase-change power unit rushes out through the cross groove to form a nozzle. The tray is disposed at one end of the initial volume chamber connected to the launch tube.

[0006] The liquid-gas phase change catapult interior ballistics modeling method comprises:

[0007] The liquid-gas phase change projectile internal ballistic model is divided into the phase change power unit flow model, the initial volume chamber energy model, and the projectile motion parameter model.

[0008] The expression of the phase change power unit flow model is as follows:

[0009]

[0010] The expression of the initial chamber energy model is as follows:

[0011]

[0012] The expression of the projectile motion parameter model is as follows:

[0013]

[0014] in, The mass flow rate of carbon dioxide released by the phase change power unit, is the effective area of ​​the nozzle, Relieve pressure for the phase change power unit, is the carbon dioxide density in the phase change power unit, is the adiabatic coefficient of carbon dioxide; for Always create the energy in the room. is the initial energy in the initial volume room, for At time i+1, the phase change power unit releases the energy of gas into the initial chamber; for The acceleration of the projectile at this moment, for Initial indoor pressure at all times, is the initial pressure in the initial volume chamber, is the acceleration angle of the projectile ejection, is the friction coefficient of the projectile, is the acceleration due to gravity, is the projectile weight, is the radius of the projectile pressure action surface.

[0015] The present invention constructs a liquid-gas phase change catapult interior ballistic model including multiple phase change power units. The working time of the phase change device is increased, which can solve the catapult interior ballistic design problem with high catapult overload requirements and accurately calculate the change process of interior ballistic parameters during the expansion working process of carbon dioxide phase change catapult.

[0016] Furthermore, the expression for the release pressure of the phase change power unit is as follows:

[0017]

[0018] in, is the characteristic parameter of the pressure relief diaphragm material, is the growth multiple of the boost rate, H is the cross groove thickness, W is the cross groove width, V is the cross groove depth, is the effective area of ​​the nozzle.

[0019] Furthermore, the expression of the nozzle effective area is as follows:

[0020]

[0021] in, is the nozzle diameter, is the opening coefficient of the pressure relief diaphragm, usually taken as 0.4~0.9.

[0022] Furthermore, the expression of the initial energy in the initial volume chamber is as follows:

[0023]

[0024] in, is the initial enthalpy of the initial indoor air, is the molar volume of air, is the molar mass of air, is the volume of the initial chamber.

[0025] Furthermore, the energy of the gas released by the phase change power unit into the initial volume chamber is expressed as follows:

[0026]

[0027] in, is the carbon dioxide energy in the i+1th phase change power unit, is the air energy in the i+1th phase change power unit, is the energy used by the combustion of chemicals in the i+1th phase change power unit, is the combustion efficiency of the i+1th phase change power unit.

[0028] Based on the same inventive concept, the present invention also provides a liquid-gas phase change catapult interior ballistics simulation method, which includes the following process:

[0029] Constructing a liquid-gas phase change catapult internal ballistics model according to the liquid-gas phase change catapult internal ballistics modeling method, wherein the liquid-gas phase change catapult internal ballistics model includes a phase change power unit flow model, an initial volume chamber energy model, and a projectile motion parameter model;

[0030] The phase change power units are sequentially excited according to a preset excitation sequence;

[0031] Calculate the cumulative energy of the gas released into the initial volume chamber by the phase change power unit that has been excited at the current moment;

[0032] Calculate the energy in the initial volume chamber at the current moment based on the cumulative energy of the gas released into the initial volume chamber by the excited phase change power unit at the current moment and the initial energy in the initial volume chamber;

[0033] Calculate the acceleration, velocity and stroke of the projectile at the current moment;

[0034] The calculation ends when the projectile leaves the launch tube.

[0035] Based on the same inventive concept, the present invention further provides an electronic device, comprising:

[0036] one or more processors;

[0037] A memory having one or more programs stored thereon, which, when executed by the one or more processors, enables the one or more processors to implement the steps of a liquid-gas phase change catapult interior ballistics modeling method or a liquid-gas phase change catapult interior ballistics simulation method.

[0038] Based on the same inventive concept, the present invention also provides a computer-readable storage medium storing a computer program, which, when executed by a processor, implements the steps of a liquid-gas phase change catapult interior ballistics modeling method or a liquid-gas phase change catapult interior ballistics simulation method.

[0039] Compared with the prior art, the present invention has the following beneficial effects:

[0040] The present invention constructs a liquid-gas phase change catapult interior ballistic model including multiple phase change power units. The working time of the phase change device is increased, which can solve the problem of catapult interior ballistic design with high catapult overload requirements, and solve the problem of achieving a predetermined speed when the overload does not exceed the limit value when the catapult overload control requirements are high, and accurately calculate the change process of interior ballistic parameters during the expansion and working process of carbon dioxide phase change catapult. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Figure 1 is a schematic diagram of the liquid-gas phase change ejection system of the present invention;

[0042] Figure 2 Schematic diagram of the structure of the phase change power unit of the present invention;

[0043] Figure 3 is a schematic diagram of a pressure-releasing membrane of the present invention;

[0044] Figure 4 is another schematic diagram of the pressure-releasing membrane of the present invention;

[0045] Figure 5 This is a schematic diagram of the structure of the nozzle formed by the pressure-releasing diaphragm of the present invention after the high-pressure mixed gas impacts;

[0046] Figure 6 Schematic diagram of the interior ballistics simulation method of liquid-gas phase change catapult for a single phase change power unit of the present invention;

[0047] Figure 7 Schematic diagram of CO2 output quality of a phase change power unit according to an embodiment of the present invention;

[0048] Figure 8Schematic diagram of CO2 energy output from a phase change power unit according to an embodiment of the present invention;

[0049] Figure 9 1 is a pressure curve diagram of the initial volume chamber according to an embodiment of the present invention.

[0050] In the figure, 1-phase change power unit, 2-initial volume chamber, 3-launching tube, 4-projectile body, 5-tray, 11-liquid carbon dioxide, 12-heat release source, 13-pressure release diaphragm, 131-nozzle, 132-cross groove. DETAILED DESCRIPTION

[0051] The present invention will be described in detail below with reference to the following embodiments. It should be noted that the embodiments and features of the embodiments may be combined unless they conflict. For ease of description, the words "upper," "lower," "left," and "right" appearing below merely indicate the directions of upper, lower, left, and right relative to the accompanying drawings and do not limit the structure. Example

[0052] like Figure 1-Figure 5 The liquid-gas phase change ejection system of this embodiment includes a phase change power unit 1 (or phase change tube), an initial volume chamber 2, a launch tube 3, a projectile 4 and a tray 5. There is at least one phase change power unit 1. A heat release source 12 and liquid carbon dioxide 11 are arranged inside the phase change power unit 1. The heat release source 12 can be chemical combustion, electric heating or arc heat release. A pressure relief diaphragm 13 is provided at the end of the phase change power unit 1 connected to the initial volume chamber 2. A cross groove 132 is provided at the center of the pressure relief diaphragm 13. The high-pressure carbon dioxide mixture in the phase change power unit 1 rushes out through the cross groove 132 to form a nozzle 131. The nozzle 131 is connected to the initial volume chamber 2. A tray 5 is provided at the end of the initial volume chamber 2 connected to the launch tube. The high-pressure mixture enters the initial volume chamber 2 through the nozzle 131 and pushes the tray 5 in the initial volume chamber 2 to run. The tray 5 pushes the projectile 4 to move at high speed.

[0053] The liquid-gas phase change catapult internal ballistic physical model includes the phase change power unit flow model, the initial volume chamber energy model, and the projectile motion parameter model;

[0054] (1) Phase change power unit flow model

[0055] After the pressure in the phase change power unit reaches the release pressure, the material in the phase change power unit is ejected from the nozzle formed by the pressure release diaphragm at the end. The flow rate of the nozzle is calculated according to formula (1) based on the test:

[0056] (1)

[0057] Where, The mass flow rate of carbon dioxide released by the phase change power unit, is the effective area of ​​the nozzle, Relieve pressure for the phase change power unit, is the density in the phase change power unit, is the adiabatic coefficient of carbon dioxide. For the convenience of calculation, Take 1.289. Then we have:

[0058] (2)

[0059] The mass flow rate of carbon dioxide released by the phase change power unit is determined by the nozzle area, the pressure inside the phase change power unit 1 and the density inside the phase change power unit 1. is the effective opening area, the phase change power unit 1 releases the pressure Through experimental measurement or according to formula (4), the volume of the phase change power unit 1 is known, the mass of CO2 in the phase change power unit 1 is known, and the density before release in the phase change power unit 1 can be obtained. , then the mass flow rate of carbon dioxide released by the phase change power unit is It can be obtained by calculation.

[0060] To ensure the effective area of ​​the nozzle The test shows that the cross groove of the pressure relief diaphragm directly affects the effective area of ​​the nozzle. If the opening of the pressure relief diaphragm is too small, the flow rate of the nozzle is too small. If the opening of the pressure relief diaphragm is too large, the pressure relief diaphragm will burst and generate fragments that enter the initial volume chamber.

[0061] The width W of the cross groove of the pressure relief diaphragm is 0.5-2mm, in mm; the effective thickness of the cross groove of the pressure relief diaphragm is , unit: mm; the cross groove depth V of the pressure relief diaphragm is 1.0-1.5mm, the effective area of ​​the nozzle :

[0062] (3)

[0063] (4)

[0064] in, is the nozzle diameter, is the opening coefficient of the pressure relief diaphragm, usually taken as 0.4~0.9. is the characteristic parameter of the pressure relief diaphragm material, It is the growth multiple of the boost rate (range 200-300).

[0065] As one embodiment, the volume of the phase change power unit is 2.4L, the mass of CO2 is 1.7Kg, and the output mass and output energy of the phase change power unit at 20°C are calculated as follows: Figure 7 、 Figure 8 shown.

[0066] (2) Energy model of the initial volume chamber

[0067] Assume the radius of the launch tube is The weight of the projectile is , the radius of the projectile pressure action surface is , the initial volume of the chamber is , the effective stroke of the projectile is The friction coefficient of the projectile is , the ejection acceleration angle of the projectile is .

[0068] 1) Single phase change power unit

[0069] The sum of the work done by a single phase change power unit and the initial energy in the initial volume chamber is equal to the sum of the energy of the liquid carbon dioxide in the phase change power unit, the kinetic energy of the projectile, and the gravitational potential energy of the projectile:

[0070] (5)

[0071] Where, is the energy increment of CO2 and air in the initial volume chamber (energy in the initial volume chamber), J; is the projectile velocity, m / s; is the acceleration due to gravity, m / s²; h is the height of the projectile, m; is the initial energy in the initial volume chamber, J; is the energy of the phase change power unit releasing gas into the initial chamber (output energy of the phase change power unit), J.

[0072] An initial chamber is located between the phase-change power unit and the projectile. This chamber ensures a stable and uniform flow of the high-pressure, high-velocity carbon dioxide mixture ejected from the phase-change power unit, which then acts on the projectile to propel it. The initial chamber typically contains a certain amount of air. When calculating the trajectory of the projectile, in addition to the CO2 ejected from the phase-change power unit, it also takes into account the original air in the initial chamber and the air ejected along with the CO2 from the phase-change power unit.

[0073] Work energy of a single phase change power unit ,have:

[0074] (6)

[0075] That is, the work done by a single phase change power unit is equal to the CO2 energy in the phase change power unit. , air energy in the phase change power unit and the energy used in chemical combustion the sum of For combustion efficiency.

[0076] (7)

[0077] Where, is the initial indoor air quality, kg; is the initial enthalpy of the initial indoor air, is the molar volume of air, equal to 22.414 L / mol, is the molar mass of air, which is equal to 28.97 g / mol.

[0078] Initial indoor air density at all times :

[0079] (8)

[0080] Where, is the amount of initial indoor air, for The amount of material entering the initial chamber from the phase change power unit at any moment, for The movement distance of the projectile at the moment, m.

[0081] The density of carbon dioxide entering the initial chamber of the phase change power unit at the moment :

[0082] (9)

[0083] Where, for The mass of liquid carbon dioxide entering the primary chamber from the phase change power unit at any moment.

[0084] (10)

[0085] (11)

[0086] The substance entering the initial chamber from the phase change power unit is CO2, then

[0087] (12)

[0088] Where, is the molar mass of CO2, which is equal to 44 g / mol.

[0089] 2) Multiple phase change power units

[0090] Multiple phase change power units release carbon dioxide into the initial volume chamber in sequence at certain intervals. The motion equation of the projectile is the same as that of a single phase change power unit. The difference is that the working fluid entering the initial volume chamber from the phase change power unit is not completed all at once. Instead, the carbon dioxide energy released by n phase change power units is accumulated at certain time intervals. The energy in the initial volume chamber is:

[0091] (13)

[0092]

[0093] Where, for The work done by the i+1th phase change power unit entering the primary chamber at a certain moment; is the carbon dioxide energy in the i+1th phase change power unit, is the air energy in the i+1th phase change power unit, is the energy used by the combustion of chemicals in the i+1th phase change power unit, is the combustion efficiency of the i+1th phase change power unit.

[0094] The carbon dioxide energy released by a single phase change power unit can be regarded as a Time series:

[0095] (14)

[0096] Where, is the time it takes for a single phase change power unit to release energy, for The energy released at all times, for The energy released at all times, is the time step of the energy sequence, for Energy released at all times.

[0097] Assume that there are i phase change power units with The working fluid is released into the initial volume chamber in sequence, and the time series of the total work energy is:

[0098] (15)

[0099] The mass of carbon dioxide released by a single phase change power unit is considered as a Time series:

[0100] (16)

[0101] Where, is the mass of carbon dioxide released by a single phase change power unit, is the time it takes for a single phase change power unit to release energy, for The mass of carbon dioxide released at any moment, for The mass of carbon dioxide released at any moment, is the time step of the CO2 mass series, for The mass of carbon dioxide released at the moment. Assume that there are i phase change power units with The carbon dioxide is released into the initial chamber in sequence, and the time series of the total carbon dioxide mass is:

[0102] (17)

[0103] Where, yes The mass of carbon dioxide in the phase change power unit entering the primary chamber at any moment, yes The mass of carbon dioxide in the phase change power unit entering the primary chamber at any moment, yes The mass of carbon dioxide of the phase change power unit entering the primary chamber at any moment.

[0104] Substituting into formula (5) to formula (13) we can get The density of the air in the room at the time of initial concentration and The density of carbon dioxide entering the primary chamber from the phase change power unit at any moment.

[0105] (3) Projectile motion parameter model

[0106] Ignoring air resistance, the acceleration of projectile 4 is:

[0107] (18)

[0108] in, for The acceleration of the projectile at this moment, for Initial indoor pressure at all times, is the initial pressure in the initial volume chamber, is the acceleration angle of the projectile ejection, is the friction coefficient of the projectile, is the acceleration due to gravity, is the weight of the projectile, is the radius of the projectile pressure action surface.

[0109] Projectile speed :

[0110] (19)

[0111] Movement stroke of the projectile :

[0112] (20)

[0113] Initially, the air and carbon dioxide gas in the room are at the same temperature and pressure. The density of the indoor air at the beginning of each time The pressure in the initial chamber can be calculated by combining the density of the carbon dioxide entering the initial chamber from the phase change power unit at any moment and the energy released into the initial chamber by the phase change power unit with the equation of motion of the projectile.

[0114] The calculation process of interior ballistics of liquid-gas phase change ejection is as follows Figure 6 As shown, first calculate the amount, mass and energy of the air in the initial volume chamber, then import the output mass and energy of a single phase change power unit, and combine the air state in the initial volume chamber to calculate the CO2 density and air density. First give an assumed pressure and substitute it into Refprop to calculate the energy increment of CO2 and air. After adding the energy increment of CO2 and air to the kinetic energy of the projectile, compare it with the output energy of the phase change power unit. When the two are equal, the pressure at this time is the pressure in the initial volume chamber. Combined with the projectile motion equation, the acceleration, velocity and stroke of the projectile at this time are obtained, and the volume of the initial volume chamber is updated. When the projectile leaves the launch tube, the calculation is terminated, and finally the ballistic parameters in the initial volume chamber are obtained, including the initial volume chamber pressure, projectile motion acceleration, projectile motion velocity, etc.

[0115] The simulation method includes the following processes:

[0116] 1) Use formula (11) to determine the output mass of the phase change power unit, determine the air volume, mass and initial energy of the initial volume chamber, and calculate the output energy of the phase change power unit;

[0117] 2) Based on the output mass of the phase change power unit in step 1), as well as the air volume, mass and initial energy, use equation (9) to calculate the CO2 density and equation (8) to calculate the air density;

[0118] 3) Assuming a constant initial chamber pressure, combined with step 2), use Refprop_Example_main.VI (the physical properties of CO2 and air are referenced from the Refprop database of the National Institute of Standards and Technology (NIST). Refprop software includes support for dynamic link libraries, allowing other applications to utilize Refprop's functionality) to calculate the energy increments of CO2 and air in the initial chamber.

[0119] 4) Combine the energy increments of CO2 and air in the initial volume chamber, the kinetic energy of the projectile, and the gravitational potential energy of the projectile to obtain the output energy increment of the phase change power unit;

[0120] 5) Compare the output energy of the phase change power unit with the output energy increment of the phase change power unit obtained in step (4). When they are equal, this pressure is the pressure in the initial volume chamber;

[0121] 6) Accumulating the output mass and energy of the phase change power unit according to the ignition time sequence to obtain the output mass and energy of multiple phase change power units;

[0122] 7) Substitute the output mass and energy of multiple phase change power units into the projectile motion equation to obtain the projectile motion acceleration, velocity, and displacement at this time, and update the volume of the initial chamber. When the projectile exits the launch tube, terminate the calculation.

[0123] Experimental verification:

[0124] A simulated bomb weighs 1.2 tons and uses five phase change power units, each containing 1.7 kg of carbon dioxide. The initial chamber pressure test and calculation curves are shown in Figure 2. Figure 9 As shown in the figure, the initial chamber pressure test is in good agreement with the calculated curve, which verifies the accuracy of the calculation model.

[0125] Another embodiment of the present invention provides an electronic device, including:

[0126] one or more processors;

[0127] A memory having one or more programs stored thereon, which, when executed by one or more processors, enables the one or more processors to implement the steps of a liquid-gas phase change catapult interior ballistics modeling method or a liquid-gas phase change catapult interior ballistics simulation method.

[0128] In some implementations, the memory may be a high-speed random access memory (RAM), and may also include a non-volatile memory, such as at least one disk storage.

[0129] In other implementations, the processor may be a central processing unit (CPU), a digital signal processor (DSP), or other general-purpose processors, which are not limited herein.

[0130] Another embodiment of the present invention provides a computer-readable storage medium storing a computer program. When the computer program is executed by a processor, the steps of a liquid-gas phase change catapult interior ballistics modeling method or a liquid-gas phase change catapult interior ballistics simulation method are implemented.

[0131] The contents illustrated in the above embodiments should be understood as these embodiments are only used to more clearly illustrate the present invention, and are not used to limit the scope of the present invention. After reading the present invention, various equivalent modifications of the present invention by those skilled in the art shall fall within the scope defined by the claims attached to this application.

Claims

1. A method for modeling the interior ballistics of a liquid-gas phase-change catapult. The liquid-gas phase-change catapult system includes a phase-change power unit, an initial volume chamber, a launch tube, a projectile, and a tray. The phase-change power unit is provided with multiple phase-change power units. The projectile is disposed within the launch tube. The initial volume chamber is connected to the launch tube. A heat release source and liquid carbon dioxide are disposed within the phase-change power unit. A pressure-releasing diaphragm is disposed at the end of the phase-change power unit connected to the initial volume chamber. A cross-shaped groove is disposed in the center of the pressure-releasing diaphragm. The high-pressure carbon dioxide mixture in the phase-change power unit is ejected through the cross-shaped groove to form a nozzle. A tray is disposed at the end of the initial volume chamber connected to the launch tube. It is characterized in that The liquid-gas phase change catapult interior ballistics modeling method comprises: The liquid-gas phase change projectile internal ballistic model is divided into the phase change power unit flow model, the initial volume chamber energy model, and the projectile motion parameter model. The expression of the phase change power unit flow model is as follows: ； The expression of the initial chamber energy model is as follows: ； The expression of the projectile motion parameter model is as follows: ； in, The mass flow rate of carbon dioxide released by the phase change power unit, is the effective area of ​​the nozzle, Relieve pressure for the phase change power unit, is the carbon dioxide density in the phase change power unit, is the adiabatic coefficient of carbon dioxide; for Always create the energy in the room. is the initial energy in the initial volume room, for At time i+1, the phase change power unit releases the energy of gas into the initial chamber; for The acceleration of the projectile at this moment, for Initial indoor pressure at all times, is the initial pressure in the initial volume chamber, is the acceleration angle of the projectile ejection, is the friction coefficient of the projectile, is the acceleration due to gravity, is the weight of the projectile, is the radius of the projectile pressure action surface.

2. The liquid-gas phase change catapult interior ballistics modeling method according to claim 1, characterized in that: The expression of the release pressure of the phase change power unit is as follows: ； in, is the characteristic parameter of the pressure relief diaphragm material, is the growth multiple of the boost rate, H is the cross groove thickness, W is the cross groove width, V is the cross groove depth, is the effective area of ​​the nozzle.

3. The liquid-gas phase change catapult interior ballistics modeling method according to claim 1 or 2, characterized in that: The expression of the effective area of ​​the nozzle is as follows: ； Where D1 is the nozzle diameter, is the opening coefficient of the pressure relief diaphragm.

4. The liquid-gas phase change catapult interior ballistics modeling method according to claim 1, characterized in that: The expression of the initial energy in the initial volume chamber is as follows: ； in, is the initial enthalpy of the initial indoor air, is the molar volume of air, is the molar mass of air, is the volume of the initial chamber.

5. The liquid-gas phase change catapult interior ballistics modeling method according to claim 1, characterized in that: The energy of the gas released by the phase change power unit into the initial chamber is expressed as follows: ； in, is the carbon dioxide energy in the i+1th phase change power unit, is the air energy in the i+1th phase change power unit, is the energy used by the combustion of chemicals in the i+1th phase change power unit, is the combustion efficiency of the i+1th phase change power unit.

6. A liquid-gas phase change projectile interior ballistics simulation method, characterized in that: The following processes are included: A liquid-gas phase change catapult internal ballistics model is constructed according to the liquid-gas phase change catapult internal ballistics modeling method according to any one of claims 1 to 5, wherein the liquid-gas phase change catapult internal ballistics model includes a phase change power unit flow model, an initial volume chamber energy model, and a projectile motion parameter model; The phase change power units are sequentially excited according to a preset excitation sequence; Calculate the cumulative energy of the gas released into the initial volume chamber by the phase change power unit that has been excited at the current moment; Calculate the energy in the initial volume chamber at the current moment based on the cumulative energy of the gas released into the initial volume chamber by the excited phase change power unit at the current moment and the initial energy in the initial volume chamber; Calculate the acceleration, velocity and stroke of the projectile at the current moment; The calculation ends when the projectile leaves the launch tube.

7. An electronic device, characterized in that: include: one or more processors; A memory having one or more programs stored thereon, which, when executed by the one or more processors, enables the one or more processors to implement the steps of the liquid-gas phase change catapult interior ballistics modeling method described in any one of claims 1 to 5 or the liquid-gas phase change catapult interior ballistics simulation method described in claim 6.

8. A computer-readable storage medium, characterized in that It stores a computer program, which, when executed by a processor, implements the steps of the liquid-gas phase change catapult interior ballistics modeling method described in any one of claims 1 to 5 or the liquid-gas phase change catapult interior ballistics simulation method described in claim 6.

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