Liquid-gas phase change ejection inner trajectory modeling method, simulation method and electronic equipment

Abstract

The invention provides a liquid-gas phase change ejection inner trajectory modeling method, a liquid-gas phase change ejection simulation method and electronic equipment. A liquid-gas phase change ejection system comprises at least one phase change power unit. The liquid-gas phase change ejection inner trajectory modeling method comprises the step of dividing a liquid-gas phase change ejection inner trajectory into a phase change power unit flow model, a primary chamber energy model and a projectile body motion parameter model. According to the method, the liquid-gas phase change ejection inner ballistic model comprising the multiple phase change power units is constructed, the acting time of the phase change device is prolonged, the preset speed can be achieved when the ejection overload control requirement is high and the overload does not exceed the limit value, and the inner ballistic parameter change process in the carbon dioxide phase change ejection expansion acting process can be accurately calculated.

Description

Technical Field

[0001] The present invention belongs to the technical field of phase change launch technology, and particularly relates to a liquid-gas phase change ejection interior ballistic modeling method, a simulation method, and an electronic device. Background Art

[0002] Liquid carbon dioxide absorbs heat in a closed space and undergoes a supercritical phase change to gas, instantly vaporizing to generate high-pressure gas, which can be used as the power of an ejection device. The phase change process can replace or supplement traditional solid gunpowder ejection, providing a more environmentally friendly and controllable energy source. During the carbon dioxide phase change process, due to the drastic phase change and the complexity of gas-liquid-solid multiphase flow, it is difficult to design the interior ballistics. The existing technology establishes the overall scheme of the supercritical phase change ejection device based on the basic principles of high-pressure launch technology and gas guns, and establishes a supercritical phase change gas gun launch model. However, from the release to the final state of the supercritical phase change ejection device, the energy change of the released working medium needs to be combined with the energy utilization rate to obtain the work energy of the supercritical phase change power unit, and then combined with the energy state of the initial volume chamber and the motion equation of the load to obtain the phase change ejection work model. Moreover, the launch device of a single supercritical phase change power unit has a short working time and a drastic energy change, which is not suitable for ejection systems with high requirements for ejection overload. Summary of the Invention

[0003] The purpose of the present invention is to address the deficiencies of the prior art and provide a liquid-gas phase change ejection interior ballistic modeling method, a simulation method, and an electronic device to more accurately calculate the interior ballistic parameters of the liquid-gas phase change ejection system.

[0004] To achieve the above purpose, the technical solution adopted by the present invention is: A liquid-gas phase change ejection interior ballistic modeling method, wherein the liquid-gas phase change ejection system includes a phase change power unit, an initial volume chamber, a launch tube, a projectile, and a tray. There is at least 1 phase change power unit. The projectile is arranged in the launch tube. The initial volume chamber is connected to the launch tube. A heat release source and liquid carbon dioxide are arranged inside the phase change power unit. A pressure release diaphragm is arranged at one end of the phase change power unit connected to the initial volume chamber. A cross groove is arranged at the center of the pressure release diaphragm. The high-pressure carbon dioxide mixture gas in the phase change power unit rushes out through the cross groove to form a nozzle. A tray is arranged at one end of the initial volume chamber connected to the launch tube; The liquid-gas phase change ejection interior ballistic modeling method includes: Dividing the liquid-gas phase change ejection interior ballistic model into a phase change power unit flow model, an initial volume chamber energy model, and a projectile motion parameter model; The expression of the phase change power unit flow model is as follows:

[0005] The expression of the initial volume chamber energy model is as follows:

[0006] The expression of the projectile motion parameter model is as follows:

[0007] Among them, is the mass flow rate of carbon dioxide released by the phase change power unit, is the effective area of the nozzle, is the release pressure of the phase change power unit, is the density of carbon dioxide in the phase change power unit, is the adiabatic coefficient of carbon dioxide; is the energy in the initial volume chamber at time is the initial energy in the initial volume chamber, is the energy released by the i-th phase change power unit into the initial volume chamber at time is the motion acceleration of the projectile at time is the pressure in the initial volume chamber at time is the initial pressure in the initial volume chamber, is the ejection acceleration angle of the projectile, is the friction coefficient of the projectile, is the acceleration due to gravity, is the weight of the projectile, is the radius of the pressure acting surface of the projectile.

[0008] The present invention constructs a liquid-gas phase change ejection interior ballistics model including multiple phase change power units. The increase in the working time of the phase change device can solve the problem of the interior ballistics design with high ejection overload requirements and accurately calculate the change process of the interior ballistics parameters during the carbon dioxide phase change ejection expansion work process.

[0009] Furthermore, the expression of the release pressure of the phase change power unit is as follows:

[0010] Among them, is the material characteristic parameter of the pressure release diaphragm, is the growth multiple of the pressure rise rate, H is the thickness of the cross groove, W is the width of the cross groove, V is the depth of the cross groove, is the effective area of the nozzle.

[0011] Furthermore, the expression of the effective area of the nozzle is as follows:

[0012] Among them, is the diameter of the nozzle, is the opening coefficient of the pressure release diaphragm, usually taking 0.4 - 0.9.

[0013] Further, the expression for the initial energy in the initial volume chamber is as follows:

[0014] Wherein, is the initial enthalpy value of the air in the initial volume chamber, is the molar volume of the air, is the molar mass of the air, is the volume of the initial volume chamber.

[0015] Further, the energy released by the phase change power unit when releasing gas into the initial volume chamber is expressed as follows:

[0016] Wherein, is the energy of carbon dioxide in the i-th phase change power unit, is the energy of air in the i-th phase change power unit, is the energy utilized by the combustion of the chemical agent in the i-th phase change power unit, is the combustion efficiency of the i-th phase change power unit.

[0017] Based on the same inventive concept, the present invention also provides a liquid-gas phase change ejection interior ballistics simulation method, including the following processes: Construct a liquid-gas phase change ejection interior ballistics model according to the liquid-gas phase change ejection interior ballistics modeling method, and the liquid-gas phase change ejection interior ballistics model includes a phase change power unit flow model, an initial volume chamber energy model, and a projectile motion parameter model; Eject the phase change power units in sequence according to a preset excitation timing; Calculate the cumulative energy released by the phase change power units that have been ejected into the initial volume chamber at the current moment; Calculate the energy in the initial volume chamber at the current moment according to the cumulative energy released by the phase change power units that have been ejected into the initial volume chamber at the current moment and the initial energy in the initial volume chamber; Calculate the acceleration, velocity, and travel of the projectile at the current moment; When the projectile exits the launch tube, end the calculation.

[0018] Based on the same inventive concept, the present invention also provides an electronic device, including: One or more processors; A memory, on which one or more programs are stored, and when the one or more programs are executed by the one or more processors, the one or more processors are caused to implement the steps of the liquid-gas phase change ejection interior ballistics modeling method or the liquid-gas phase change ejection interior ballistics simulation method.

[0019] Based on the same inventive concept, the present invention also provides a computer-readable storage medium storing a computer program, and when the computer program is executed by a processor, the steps of the liquid-gas phase change ejection interior ballistic modeling method or the liquid-gas phase change ejection interior ballistic simulation method are implemented.

[0020] Compared with the prior art, the beneficial effects of the present invention are as follows: The present invention constructs a liquid-gas phase change ejection interior ballistic model including multiple phase change power units, and the working time of the phase change device is increased, which can solve the problem of the interior ballistic design of ejection with high ejection overload requirements. When the ejection overload control requirement is high, a predetermined speed can be achieved without exceeding the limit value of the overload, and the change process of the interior ballistic parameters during the expansion work of the carbon dioxide phase change ejection can be accurately calculated. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 is a schematic diagram of the liquid-gas phase change ejection system of the present invention; Figure 2 is a schematic structural diagram of the phase change power unit of the present invention; Figure 3 is a schematic diagram of the pressure relief diaphragm of the present invention; Figure 4 is another schematic diagram of the pressure relief diaphragm of the present invention; Figure 5 is a schematic structural diagram of the nozzle formed after the pressure relief diaphragm of the present invention is impacted by the high-pressure mixed gas; Figure 6 is a schematic diagram of the liquid-gas phase change ejection interior ballistic simulation method of a single phase change power unit of the present invention; Figure 7 is a schematic diagram of the CO2 output mass of the phase change power unit in an embodiment of the present invention; Figure 8 is a schematic diagram of the CO2 output energy of the phase change power unit in an embodiment of the present invention; Figure 9 is a pressure curve graph of the initial volume chamber in an embodiment of the present invention.

[0022] In the figures, 1 - phase change power unit, 2 - initial volume chamber, 3 - launcher tube, 4 - projectile, 5 - tray, 11 - liquid carbon dioxide, 12 - heat release source, 13 - pressure relief diaphragm, 131 - nozzle, 132 - cross groove. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0023] The present invention will be described in detail below with reference to the embodiments. It should be noted that, without conflict, the embodiments in the present invention and the features in the embodiments can be combined with each other. For the convenience of description, words such as "upper", "lower", "left", and "right" in the following text only indicate the same direction as the upper, lower, left, and right directions of the drawings themselves, and do not limit the structure. Embodiment

[0024] As Figures 1-5 , the liquid-gas phase change ejection system of this embodiment includes a phase change power unit 1 (or a phase change tube), an initial volume chamber 2, a launch tube 3, a projectile 4, and a tray 5. There is at least 1 phase change power unit 1. Inside the phase change power unit 1, a heat release source 12 and liquid carbon dioxide 11 are provided. The heat release source 12 can be chemical agent combustion, electric heating, or arc heat release. At one end of the phase change power unit 1 connected to the initial volume chamber 2, a pressure release diaphragm 13 is provided. A cross groove 132 is provided at the center of the pressure release diaphragm 13. The high-pressure carbon dioxide mixture gas in the phase change power unit 1 rushes out through the cross groove 132 to form a nozzle 131. The nozzle 131 is communicated with the initial volume chamber 2. A tray 5 is provided at one end of the initial volume chamber 2 connected to the launch tube. The high-pressure mixture gas enters the initial volume chamber 2 through the nozzle 131 and pushes the tray 5 in the initial volume chamber 2 to move, and the tray 5 pushes the projectile 4 to move at a high speed.

[0025] The liquid-gas phase change ejection interior ballistic physical model includes a phase change power unit flow model, an initial volume chamber energy model, and a projectile motion parameter model; (1) Phase change power unit flow model After the pressure inside the phase change power unit reaches the release pressure, the substances inside the phase change power unit are ejected from the nozzle formed by the pressure release diaphragm at the end. According to the test, the flow rate calculation of this nozzle is carried out according to Equation (1): (1) In the formula, is the mass flow rate of carbon dioxide released by the phase change power unit, is the effective area of the nozzle, is the release pressure of the phase change power unit, is the density inside the phase change power unit, is the adiabatic coefficient of carbon dioxide. For the convenience of calculation, take 1.289. Then there is: (2) 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. The effective area of the nozzle is the effective opening area, and the release pressure of the phase change power unit 1 is measured through experiments or according to Equation (4). The volume of the phase change power unit 1 is known, and the mass of CO2 inside the phase change power unit 1 is known. The density before release inside the phase change power unit 1 can be obtained, then the mass flow rate of carbon dioxide released by the phase change power unit can be obtained through calculation.

[0026] To ensure the effective area of the nozzle , Tests show that the cross groove of the pressure relief diaphragm directly affects the effective area of the nozzle. If the opening degree of the pressure relief diaphragm is too small, the flow rate of the nozzle is too small. If the opening degree of the pressure relief diaphragm is too large, fragments generated by the bursting of the pressure relief diaphragm will enter the initial volume chamber.

[0027] The width W of the cross groove of the pressure relief diaphragm is 0.5 - 2 mm, unit: mm; the effective thickness of the cross groove of the pressure relief diaphragm , unit: mm; the groove depth V of the cross groove of the pressure relief diaphragm is 1.0 - 1.5 mm, and the effective area of the nozzle : (3) (4) Among them, is the nozzle diameter, is the opening coefficient of the pressure relief diaphragm, usually taking 0.4 - 0.9. is the material characteristic parameter of the pressure relief diaphragm, is the growth multiple of the pressure rising rate (value range 200 - 300).

[0028] As one of the implementation modes, the volume of the phase change power unit is 2.4 L, and the mass of CO2 is 1.7 Kg. When calculated at 20 °C, the output mass and output energy results of the phase change power unit are as Figure 7 、 Figure 8 shown.

[0029] (2)Initial volume chamber energy model Let the radius of the launch tube be , the weight of the projectile be , the radius of the pressure acting surface of the projectile be , the volume of the initial volume chamber be , the effective stroke of the projectile be , the friction coefficient of the projectile be , the ejection acceleration angle of the projectile be .

[0030] 1)Single phase change power unit 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: (5) In the formula, is the energy increment of CO2 and air in the initial volume chamber (energy in the initial volume chamber), J; is the moving speed of the projectile, m / s; is the gravitational acceleration, m / s²; h is the moving height of the projectile, m; is the initial energy in the initial volume chamber, J; The energy for the phase change power unit to release gas into the initial volume chamber (the output energy of the phase change power unit), J.

[0031] An initial volume chamber is provided between the phase change power unit and the projectile body. The function of the initial volume chamber is to make the high-pressure and high-speed carbon dioxide mixture ejected from the phase change power unit flow stably and uniformly, and then act on the projectile body to push it to move. There is generally a certain amount of air in the initial volume chamber. When calculating the interior ballistics of the initial volume chamber, in addition to considering the CO2 ejected from the phase change power unit, it is also necessary to consider the original air in the initial volume chamber and the air ejected together with the CO2 from the phase change power unit.

[0032] The working energy of a single phase change power unit , is: (6) That is, the working energy of a single phase change power unit is equal to the energy of CO2 in the phase change power unit , the energy of air in the phase change power unit and the energy utilized by the combustion of chemical agents sum, is the combustion efficiency.

[0033] (7) In the formula, is the mass of air in the initial volume chamber, kg; is the initial enthalpy value of air in the initial volume chamber, is the molar volume of air, equal to 22.414 L / mol, is the molar mass of air, equal to 28.97 g / mol.

[0034] The density of air in the initial volume chamber at time : (8) In the formula, is the amount of air in the initial volume chamber, is The amount of substance entering the initial volume chamber from the phase change power unit at time is The moving stroke of the projectile body at time, m.

[0035] The density of carbon dioxide entering the initial volume chamber from the phase change power unit at time : (9) In the formula, is The mass of liquid carbon dioxide entering the initial volume chamber from the phase change power unit at time.

[0036] (10) (11) The substance entering the initial chamber from the phase change power unit is CO2, then (12) In the formula, is the molar mass of CO2, equal to 44 g / mol.

[0037] 2) Multiple phase change power units Multiple phase change power units release carbon dioxide into the initial volume chamber in sequence at a certain interval. 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 at one time, but the carbon dioxide energy released by n phase change power units is accumulated at a certain time interval. The energy in the initial volume chamber is: (13)

[0038] In the formula, for The work done by the i-th phase change power unit entering the initial chamber at a certain moment; is the carbon dioxide energy in the i-th phase change power unit, is the air energy in the i-th phase change power unit, is the energy used by the combustion of chemicals in the i-th phase change power unit, is the combustion efficiency of the i-th phase change power unit.

[0039] The carbon dioxide energy released by a single phase change power unit can be regarded as a Time series: (14) In the formula, 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.

[0040] 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: (15) The mass of carbon dioxide released by a single phase change power unit is regarded as a time series: (16) where is the mass of carbon dioxide released by a single phase change power unit, is the time when a single phase change power unit releases energy, is the mass of carbon dioxide released at time is the mass of carbon dioxide released at time is the time step of the carbon dioxide mass sequence, is the mass of carbon dioxide released at time. Assume that there are i phase change power units releasing carbon dioxide into the initial volume chamber in sequence with the time sequence. The time series of the total carbon dioxide mass is: (17) where is the mass of carbon dioxide of the phase change power unit entering the initial volume chamber at time is the mass of carbon dioxide of the phase change power unit entering the initial volume chamber at time is the mass of carbon dioxide of the phase change power unit entering the initial volume chamber at time.

[0041] Substituting into formulas (5) to (13), the density of the air in the initial volume chamber at time and the density of the carbon dioxide entering the initial volume chamber from the phase change power unit at time can be obtained.

[0042] (3) Projectile motion parameter model Without considering air resistance, the acceleration of the projectile 4 in motion: (18) where is the acceleration of the projectile in motion at time is the pressure in the initial volume chamber at time is the initial pressure in the initial volume chamber, is the projectile ejection acceleration angle, is the projectile friction coefficient, is the gravitational acceleration, is the projectile weight, is the radius of the pressure acting surface of the projectile.

[0043] The velocity of the projectile : (19) The moving stroke of the projectile : (20) The air and carbon dioxide gas in the initial volume chamber are at the same temperature and pressure. Given the density of the air in the initial volume chamber at time the density of the carbon dioxide entering the initial volume chamber from the phase change power unit at time

[0044] The calculation process of the internal ballistics of liquid-gas phase change ejection is as Figure 6 shown. First, calculate the air quantity, mass, and energy in the initial volume chamber, then import the output mass and energy of a single phase change power unit, and combine with the air state in the initial volume chamber to calculate the CO2 density and air density. First, assume a pressure, substitute them into Refprop together, calculate the energy increments of CO2 and air, add the energy increments of CO2 and air to the kinetic energy of the projectile, and compare 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. Combine with the projectile motion equation to obtain the projectile motion acceleration, velocity, and stroke at this time, and update the volume of the initial volume chamber. When the projectile leaves the launcher, stop the calculation. Finally, obtain the internal ballistics parameters in the initial volume chamber, including the pressure in the initial volume chamber, the projectile motion acceleration, the projectile motion velocity, etc.

[0045] The simulation method includes the following processes: 1) Determine the output mass of the phase change power unit using Equation (11), determine the air quantity, mass, and initial energy in the initial volume chamber, and calculate the output energy of the phase change power unit; 2) Calculate the CO2 density using Equation (9) and the air density using Equation (8) according to the output mass of the phase change power unit in step 1), as well as the air quantity, mass, and initial energy; 3) Assume a pressure in the initial volume chamber, combine with step 2), and use Refprop_Example_main.VI (the physical properties of CO2 and air refer to the Refprop database of the National Institute of Standards and Technology (NIST) of the United States. The Refprop software includes support for dynamic link libraries, allowing other applications to utilize the functions of Refprop) to calculate the energy increments of CO2 and air in the initial volume chamber; 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 energy increment of the output of the phase change power unit; 5) Compare the output energy of the phase change power unit with the increment of the output energy of the phase change power unit obtained in step (4). When they are equal, this pressure is the pressure in the initial volume chamber; 6) Accumulate 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; 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 volume chamber. When the projectile leaves the launcher tube, stop the calculation.

[0046] Experimental verification: A certain simulated projectile weighs 1.2 t and uses 5 phase change power units, with 1.7 kg of carbon dioxide installed in each phase change power unit. The pressure test and calculation curves of the initial volume chamber are as Figure 9 shown. The pressure test and calculation curves of the initial volume chamber are in good agreement, verifying the accuracy of the calculation model.

[0047] Another embodiment of the present invention provides an electronic device, including: One or more processors; A memory, on which one or more programs are stored. When the one or more programs are executed by the one or more processors, the one or more processors implement the steps of the liquid-gas phase change ejection interior ballistic modeling method or the liquid-gas phase change ejection interior ballistic simulation method.

[0048] In some implementations, the memory may be a high-speed random access memory (RAM: Random Access Memory), and may also include non-volatile memory, such as at least one disk memory.

[0049] In other implementations, the processor may be a general-purpose processor of various types such as a central processing unit (CPU) and a digital signal processor (DSP), which are not limited here.

[0050] Another embodiment of the present invention provides a computer-readable storage medium, which stores a computer program. When the computer program is executed by a processor, the steps of the liquid-gas phase change ejection interior ballistic modeling method or the liquid-gas phase change ejection interior ballistic simulation method are implemented.

[0051] The content clarified in the above embodiments should be understood that these embodiments are only used to more clearly illustrate the present invention, rather than to limit the scope of the present invention. After reading the present invention, various equivalent forms of modification of the present invention by those skilled in the art all fall within the scope defined by the appended claims of this application.

Claims

1. A liquid-gas phase change ejection interior ballistics modeling method. The liquid-gas phase change ejection system includes a phase change power unit, an initial volume chamber, a launch tube, a projectile, and a tray. There is at least one phase change power unit. The projectile is arranged in the launch tube. The initial volume chamber is connected to the launch tube. A heat release source and liquid carbon dioxide are arranged inside the phase change power unit. A pressure relief diaphragm is arranged at one end of the phase change power unit connected to the initial volume chamber. A cross groove is arranged at the center of the pressure relief diaphragm. The high-pressure carbon dioxide mixture gas in the phase change power unit rushes out through the cross groove to form a nozzle. A tray is arranged at one end of the initial volume chamber connected to the launch tube; It is characterized in that The liquid-gas phase change ejection interior ballistics modeling method includes: Dividing the liquid-gas phase change ejection interior ballistics model into a phase change power unit flow model, an initial volume chamber energy model, and a projectile motion parameter model; The expression of the phase change power unit flow model is as follows: ； The expression of the initial volume chamber energy model is as follows: ； The expression of the projectile motion parameter model is as follows: ； Among them, is the mass flow rate of carbon dioxide released by the phase change power unit, is the effective area of the nozzle, is the release pressure of the phase change power unit, is the density of carbon dioxide in the phase change power unit, is the adiabatic coefficient of carbon dioxide; is the energy in the initial volume chamber at time is the initial energy in the initial volume chamber, is the energy released by the i-th phase change power unit into the initial volume chamber at time is the moving acceleration of the projectile at time is the pressure in the initial volume chamber at time is the initial pressure in the initial volume chamber, is the ejection acceleration angle of the projectile, is the friction coefficient of the projectile, is the acceleration due to gravity, is the weight of the projectile, is the radius of the pressure acting surface of the projectile.

2. The liquid-gas phase change ejection interior ballistic modeling method according to claim 1, wherein The expression of the pressure released by the phase change power unit is as follows: ； Among them, is the characteristic parameter of the pressure relief diaphragm material, is the growth multiple of the pressure increase rate, H is the thickness of the cross groove, W is the width of the cross groove, V is the depth of the cross groove, is the effective area of the nozzle.

3. The liquid-gas phase change ejection interior ballistic 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 ejection 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: ； Among them, is the initial enthalpy value of the air in the initial volume chamber, is the molar volume of the air, is the molar mass of the air, is the volume of the initial volume chamber.

5. The liquid-gas phase change ejection interior ballistics modeling method according to claim 1, characterized in that The energy of the gas released by the phase change power unit entering the initial volume chamber is expressed as follows: ； Among them, is the carbon dioxide energy in the i-th phase change power unit, is the air energy in the i-th phase change power unit, is the energy utilized by the combustion of chemical agents in the i-th phase change power unit, is the combustion efficiency of the i-th phase change power unit.

6. A liquid-gas phase change ejection interior ballistics simulation method, characterized in that Including the following processes: Construct a liquid-gas phase change ejection interior ballistics model according to the liquid-gas phase change ejection interior ballistics modeling method described in any one of claims 1-5. The liquid-gas phase change ejection interior ballistics model includes a phase change power unit flow model, an initial volume chamber energy model, and a projectile motion parameter model; Sequentially activate the phase change power units according to a preset activation timing; Calculate the cumulative energy of the gas released by the phase change power units that have been activated at the current moment and entering the initial volume chamber; Calculate the energy in the initial volume chamber at the current moment according to the cumulative energy of the gas released by the phase change power units that have been activated at the current moment and entering the initial volume chamber, and the initial energy in the initial volume chamber; Calculate the acceleration, velocity, and travel of the projectile at the current moment; When the projectile exits the launch tube, end the calculation.

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

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

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