A method for simulating and verifying the ejection property of a micro supercharger

Abstract

The application provides a simulation verification method for the ejection property of a micro supercharging device, which is designed by combining the integrated application principle of gunpowder, a thermodynamic equation and a physical motion equation, obtaining simulated speed and acceleration, and comparing the simulated speed and acceleration with the initial speed and maximum overload measured in the actual test process to complete the simulation verification of the ejection property. The simulation of the application has high authenticity, can efficiently solve the high-overload safety hazard during the ejection of the barrel, and provides a good adjustment basis for the ejection parameters.

Description

Technical Field

[0001] This invention belongs to the field of military power technology, and in particular relates to a simulation verification method for the catapult properties of a micro-pressurization device. Background Technology

[0002] The ejection properties of miniature pressurization devices fall under the field of military propulsion. They combine mathematical simulations and experimental verification using physics and thermodynamics to determine the physical properties of small projectiles during launch and ejection, thereby evaluating the flight characteristics and pressure resistance of small aircraft. This field encompasses multiple aspects, including mathematical simulations combining physical and thermodynamic calculations, gunpowder system application design, and field testing verification.

[0003] Existing pressurization devices mainly involve compressing gas using gas cylinders and controlling gas release via valves. However, these devices are complex, with large gas cylinders and heavy overall weight, making them inconvenient to carry and causing significant inconvenience for field experiments. In contrast, miniature pressurization devices are small, portable, and simple to assemble, offering greater practicality. Therefore, effectively simulating and verifying miniature pressurization devices is a pressing issue that needs to be addressed. Summary of the Invention

[0004] The present invention aims to solve at least one of the technical problems existing in the prior art.

[0005] This invention provides a simulation verification method for the projectile properties of a micro-pressurization device. This method combines the principles of gunpowder integration, thermodynamic equations, and physical equations of motion to obtain the simulated velocity and acceleration. The simulated velocity and acceleration are then compared with the initial velocity and maximum overload measured during actual testing to complete the simulation verification of the projectile properties. Specifically, this method updates and iterates according to the following formula to obtain the simulated velocity and acceleration:

[0006]

[0007] V i+2 =V0+L i+1 S

[0008]

[0009] Q i+1 =c v n i+1 RT′ i+1

[0010]

[0011] F i+1 =(P i+1 -P0)S

[0012]

[0013] v i+1 =v i +a i+1 t

[0014] Among them, L i+1 Let L be the displacement at time i+1. i Let v be the displacement at time i. i Let be the velocity at time i, t be the time interval, and a be the velocity at time i. i and a i+1 V represents the acceleration at times i and i+1, respectively. i+1 and V i+2 V0 represents the volume after time i and i+1, respectively; S represents the area of ​​force application; and P represents the volume after time i and i+1. i+1 Let P be the pressure at time i+1. i ′ +1 Let T be the pressure after the expansion update at time i+1. i+1 and T i+2 Let T be the temperature at times i+1 and i+2. i ′ +1 Let n be the temperature corresponding to the gas expansion at time i+1. i+1 and n i+2 Let be the amounts of gas produced at times i+1 and i+2, respectively, and R be Avogadro's constant. Let Q be the heat generated by the combustion of gunpowder at time i+2. i+1 Let be the heat generated by the gas expansion at time i+1. Let c be the total heat generated at time i+2. v For constant heat capacity, T 燃烧温度 F is the combustion temperature of gunpowder, which is a constant. i+1 Let P0 be the thrust generated at time i+1, P0 be the standard atmospheric pressure, m be the mass of the object being pushed, and v be the thrust generated at time i+1. i+1 and v i Let be the velocities at time i+1 and time i, and λ be the specific heat ratio, which is a constant.

[0015] Furthermore, the amount of substance of the gas produced is obtained according to the following formula:

[0016]

[0017] Where, n i Let m be the amount of gas produced at time i. t (i) represents the mass of gunpowder burning per second at time i, m 总 t represents the total mass of the gunpowder. 反应 (i) represents the reaction time of gunpowder combustion at time i, and M represents the relative molecular mass.

[0018] The present invention provides a simulation verification method for the projectile properties of a micro-pressurization device. This method is designed by combining the principles of gunpowder integration, thermodynamic equations and physical motion equations to obtain the simulated velocity and acceleration. The simulated velocity and acceleration are then compared with the initial velocity and maximum overload measured in the actual test to complete the simulation verification of the projectile properties. Attached Figure Description

[0019] The accompanying drawings, which form part of this specification, are provided to further illustrate embodiments of the invention and, together with the textual description, explain the principles of the invention. It is obvious that the drawings described below are merely some embodiments of the invention, and those skilled in the art can obtain other drawings based on these drawings without any creative effort.

[0020] Figure 1 A schematic diagram comparing acceleration simulation results with measured results provided by a specific embodiment of the present invention is shown;

[0021] Figure 2 The theoretical velocity curve provided by a specific embodiment of the present invention is shown. Detailed Implementation

[0022] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0023] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0024] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps described in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the accompanying drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values.

[0025] According to a specific embodiment of the present invention, a method for simulating and verifying the projectile properties of a micro-pressurization device is provided. This method is designed by combining the principles of gunpowder integration, thermodynamic equations, and physical equations of motion to obtain the simulated velocity and acceleration. The simulated velocity and acceleration are then compared with the initial velocity and maximum overload measured during actual testing to complete the simulation verification of the projectile properties. Specifically, this method updates and iterates according to the following formula to obtain the simulated velocity and acceleration:

[0026]

[0027] V i+2 =V0+L i+1 S

[0028]

[0029] Q i+1 =c v n i+1 RT′ i+1

[0030]

[0031] F i+1 =(P i+1 -P0)S

[0032]

[0033] v i+1 =v i +a i+1 t

[0034] Among them, L i+1 Let L be the displacement at time i+1. i Let v be the displacement at time i. i Let be the velocity at time i, t be the time interval, and a be the velocity at time i. i and a i+1 V represents the acceleration at times i and i+1, respectively. i+1and V i+2 V0 represents the volume after time i and i+1, respectively; S represents the area of ​​force application; and P represents the volume after time i and i+1. i+1 Let P' be the pressure at time i+1. i+1 Let T be the pressure after the expansion update at time i+1. i+1 and T i+2 Let T' be the temperature at times i+1 and i+2. i+1 Let n be the temperature corresponding to the gas expansion at time i+1. i+1 and n i+2 Let be the amounts of gas produced at times i+1 and i+2, respectively, and R be Avogadro's constant. Let Q be the heat generated by the combustion of gunpowder at time i+2. i+1 Let be the heat generated by the gas expansion at time i+1. Let c be the total heat generated at time i+2. v For constant heat capacity, T 燃烧温度 F is the combustion temperature of gunpowder, which is a constant. i+1 Let P0 be the thrust generated at time i+1, P0 be the standard atmospheric pressure, m be the mass of the object being pushed, and v be the thrust generated at time i+1. i+1 and v i Let be the velocities at time i+1 and time i, and λ be the specific heat ratio, which is a constant.

[0035] In this invention, the time interval t can be set to 0.0001s, and the gunpowder combustion temperature T 燃烧温度 It can be set to a constant of 1400, and the specific heat ratio λ can be set to a constant of 1.4.

[0036] The calculation formulas obtained by utilizing the integrated application principles of gunpowder, thermodynamic equations, and physical motion equations require accurate connection of the application sequence to achieve complete updates and iterations. This invention correlates heat and motion to obtain the change law from heat to motion, which is beneficial for subsequent analysis of the authenticity of experimental data and for necessary structural reinforcement.

[0037] The following sections provide a theoretical analysis of the integrated application principles of gunpowder, its thermodynamic equations, and its physical equations of motion.

[0038] 1. Principles of Integrated Application of Gunpowder

[0039] The miniature pressurization device essentially utilizes the immense pressure generated by the ignition of gunpowder. The combustion process of gunpowder is calculated based on factors such as the mass of the gunpowder, the combustion temperature, and the initial pressure. This allows for the calculation of the amount of gaseous substance (n) produced by the miniature pressurization device, and consequently, the heat generated during the gunpowder's operation. Its combustion process follows these rules:

[0040]

[0041] Where, m t (i) represents the mass of gunpowder burning per second at time i, m 总 t represents the total mass of the gunpowder. 反应 (i) represents the reaction time of gunpowder combustion at time i, and n i Let M be the amount of gas produced at time i, and M be the relative molecular mass, which is a constant value of 29. Let be the heat generated by the combustion of gunpowder at time i.

[0042] 2. Thermodynamic equations

[0043] The heat generated during the combustion of gunpowder is used to iterate through thermodynamic equations to calculate the corresponding physical parameters such as temperature, pressure, and volume. This allows us to calculate the pressure and volume of the small aircraft at various moments during the real-time ejection process. Then, we can use the formulas for pressure, force, and area of ​​force application to calculate the force, thereby relating it to the kinematic equations.

[0044]

[0045] F i =(P i -P0)S

[0046] Among them, T i Let i be the temperature at time i. Let P be the total heat generated at time i. i Let V be the pressure at time i. i F represents the volume after time i-1 ends. i Let i be the thrust generated at time i.

[0047] 3. Equations of Motion in Physics

[0048] By using thermodynamic equations to calculate the corresponding pressure, and then using the physical relationship between pressure and force, the real-time force law of the small aircraft can be calculated. Force, acceleration, velocity, displacement, etc. can then be updated and iterated through kinematic equations. The calculated real-time velocity and acceleration are then theoretically analyzed and finally compared with the data from actual field tests.

[0049]

[0050] v i+1 =v i +a i+1 t

[0051]

[0052] V i+2 =V0+L i+1 S

[0053] Among them, F iLet i be the thrust generated at time i.

[0054] The mathematical simulation is verified by using experimentally measured data such as speed and overload to ensure that the simulation results match the actual situation, thus providing the true validity of the mathematical simulation.

[0055] This invention, through theoretical calculations in physics and thermodynamics, combined with the actual properties of integrated gunpowder applications, more realistically simulates the characteristics of the ejection process of a small aircraft, helping to understand the system's characteristics in advance and improving the reliability of subsequent experiments. Simultaneously, experimental verification based on the theoretical foundation of mathematical simulation helps ensure the compatibility of the small aircraft with the micro-pressurization device in terms of strength and overload resistance.

[0056] To gain a further understanding of the present invention, the simulation verification method for the ejection properties of the micro-pressurization device of the present invention will be described in detail below with reference to specific embodiments.

[0057] In this embodiment, the real-time motion laws of physical variables such as velocity, acceleration, and force are iteratively derived according to the simulation verification method for the launch properties of the aforementioned micro-pressurization device. These laws are then compared with data from actual field tests, primarily focusing on whether the overload, peak velocity, and variation patterns are consistent. Figure 1 and Figure 2 As shown. Theoretical simulation analysis was performed on the velocity and acceleration. The theoretical velocity at the exit of the tube was 46.09 m / s, while the actual exit velocity of the aircraft in the test was between 44 m / s and 48 m / s. Therefore, the experimental results are roughly consistent with the simulation results, and the peak acceleration reached 354g.

[0058] By comparing the variation patterns of the designed physical parameters with experimentally measured data such as speed and overload, the simulation has high realism and effectively solves the safety hazard of high overload during tube firing, while also providing a good basis for adjusting the firing parameters.

[0059] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A simulation verification method for the projectile properties of a micro-intensification device, characterized in that, The method is designed by combining the principles of gunpowder integration, thermodynamic equations and physical motion equations to obtain the simulated velocity and acceleration. The simulated velocity and acceleration are then compared with the initial velocity and maximum overload measured in the actual test to complete the simulation verification of the projectile properties. The method updates and iterates according to the following formula to obtain the simulated velocity and acceleration: V i+2 =V0+L i+1 S Q i+1 =c v n i+1 RT′ i+1 F i+1 =(P i+1 -P0)S v i+1 =v i +a i+1 t Among them, L i+1 Let L be the displacement at time i+1. i Let v be the displacement at time i. i Let be the velocity at time i, t be the time interval, and a be the velocity at time i. i and a i+1 V represents the acceleration at times i and i+1, respectively. i+1 and V i+2 V0 represents the volume after time i and i+1, respectively; S represents the area of ​​force application; and P represents the volume after time i and i+1. i+1 Let P' be the pressure at time i+1. i+1 Let T be the pressure after the expansion update at time i+1. i+1 and T i+2 Let T' be the temperature at times i+1 and i+2. i+1 Let n be the temperature corresponding to the gas expansion at time i+1. i+1 and n i+2 Let be the amounts of gas produced at times i+1 and i+2, respectively, and R be Avogadro's constant. Let Q be the heat generated by the combustion of gunpowder at time i+2. i+1 Let be the heat generated by the gas expansion at time i+1. Let c be the total heat generated at time i+2. v For constant heat capacity, T 燃烧温度 F is the combustion temperature of gunpowder, which is a constant. i+1 Let P0 be the thrust generated at time i+1, P0 be the standard atmospheric pressure, m be the mass of the object being pushed, and v be the thrust generated at time i+1. i+1 and v i Let be the velocities at time i+1 and time i, and λ be the specific heat ratio, which is a constant.

2. The simulation verification method for the ejection properties of the micro-intensification device according to claim 1, characterized in that, The amount of gas produced is obtained using the following formula: Where, m t (i) represents the mass of gunpowder burning per second at time i, m 总 t represents the total mass of the gunpowder. 反应 (i) represents the reaction time of gunpowder combustion at time i, and n i Let M be the amount of gas produced at time i, and M be the relative molecular mass.

Images