Ignition test system comprising ignition simulator of propelling charge and Ignition test method

Abstract

The present invention includes a propellant charge ignition simulation device comprising a frame having a flat upper surface, a combustion chamber mounted on the frame and having a propellant charge loaded into its internal space, a breech portion coupled to one end of the combustion chamber, and a base portion coupled to the other end of the combustion chamber, a propellant charge test system comprising the same, and a test method.

Description

Technology Field

[0001] The present invention relates to an apparatus for simulating the ignition of a propellant charge, a system for testing the ignition including the same, and a test method. Background Technology

[0002] For example, a 155mm propellant charge consists of a propellant, an igniter, and an exhaust cartridge case, and the igniter is ignited by an initial flame generated from a primer applied to the weapon, propagating the flame into the propellant charge to ignite the propellant.

[0003] At this time, a short ignition time from the breech to the base of the weapon must be secured to minimize the differential pressure within the barrel. While these ignition characteristics of the propellant charge can be verified through actual firing tests, unstable ignition can cause damage to the weapon and lead to accidents, and there are disadvantages such as the consumption of significant costs and time.

[0004] The matters described in the background technology above are intended to aid in understanding the background of the invention and may include matters that are not prior art already known to those skilled in the art to which this technology belongs. Prior art literature

[0005] Korean Registered Patent Publication No. 10-0407598 The problem to be solved

[0006] The present invention has been devised to solve the aforementioned problems, and the purpose of the present invention is to provide a propellant charge ignition simulation device capable of more accurately measuring the differential pressure and ignition time of the propellant charge, an ignition test system including the same, and an ignition test method. means of solving the problem

[0007] A propellant charge ignition simulation device according to one aspect of the present invention comprises a frame having a flat upper surface, a combustion chamber mounted on the frame and having a propellant charge loaded into its internal space, a breech portion coupled to one end of the combustion chamber, and a base portion coupled to the other end of the combustion chamber.

[0008] Here, the combustion chamber may be made of a transparent material, and a transparent window may be formed in the propellant charge.

[0009] In addition, the breech portion is characterized in that one end is connected to the combustion chamber and the other end is connected to a breech portion cover, and a primer and a firing device for detonating the primer are mounted on the central axis inside the breech portion cover.

[0010] In addition, the above-mentioned breech portion is characterized by having a sensor mounting portion formed around the detonator, wherein a sensor is mounted thereon.

[0011] In addition, the above-mentioned base is characterized in that one end is connected to the combustion chamber, and the other end is connected to a base cover.

[0012] Additionally, it may further include a spacer coupled to the above-mentioned base cover, and may further include a base support mounted on the frame spaced apart from the above-mentioned base cover.

[0013] In addition, the above-mentioned base is characterized by having a sensor mounting portion formed therein for mounting a sensor.

[0014] Furthermore, it further includes a sensor cable connected to the sensor and a sensor cable protection tube for protecting the sensor cable, and is characterized in that a hole for the sensor cable protection tube is formed in the base cover to extend the sensor cable protection tube to the outside.

[0015] In addition, the propellant charge ignition test system of the present invention includes the propellant charge ignition simulation device, the sensor cable connected to the sensor of the propellant charge ignition simulation device, and the measuring device connected to the sensor cable, which receives the measurement value of the sensor and measures the flame resulting from the combustion of the propellant charge.

[0016] And, it further includes a control device that calculates the differential pressure, defined as the value obtained by subtracting the internal pressure of the base of the projectile from the internal pressure of the breech of the projectile, and the ignition time of the propellant of the propellant charge from the data measured by the measuring device.

[0017] Next, the propellant charge ignition test method of the present invention is a propellant charge ignition test method using the propellant charge ignition test system described above, comprising the steps of: loading the propellant charge into the combustion chamber and preparing the propellant charge ignition simulation device by connecting the sensor cable to the measuring device; igniting the propellant charge by detonating the primer through the detonation device; and measuring the flame resulting from the combustion of the propellant charge by the measuring device and receiving the measured value from the sensor.

[0018] And, it further includes the step of calculating the differential pressure, defined as the value obtained by subtracting the internal pressure of the base of the projectile from the internal pressure of the breech of the projectile, and the ignition time of the propellant of the propellant charge from the data measured by the measuring device. Effects of the invention

[0019] The propellant charge ignition simulation device of the present invention has the effect of being able to more accurately measure the differential pressure and ignition time of the propellant charge.

[0020] In addition, through non-firing tests, it is possible to resolve the disadvantages of the conventional method, which carries the risk of weapon damage and accidents that may occur during the unstable ignition process of the propellant charge during firing. Furthermore, it is designed to enable ignition simulation tests under varying combustion chamber volumes and the overall length of the propellant charge, offering the advantage of easily obtaining data on the ignition characteristics of the propellant charge under various conditions. Brief explanation of the drawing

[0021] FIG. 1 schematically illustrates the propellant charge ignition simulation device of the present invention and an ignition test system including the same. Figure 2 is a cross-sectional shape of the breech portion of the propellant charge ignition simulation device of the present invention. FIG. 3 is a side cross-sectional shape of the base of the propellant charge ignition simulation device of the present invention, and FIG. 4 is the AA cross-sectional shape of FIG. 3. FIG. 5 is a side cross-sectional shape of the base cover of the propellant charge ignition simulation device of the present invention, and FIG. 6 is a cross-sectional shape of the BB of FIG. 5. FIG. 7 is an example of a propellant charge of the propellant charge ignition simulation device of the present invention. Specific details for implementing the invention

[0022] In order to fully understand the present invention, the operational advantages of the present invention, and the objectives achieved by the implementation of the present invention, reference must be made to the accompanying drawings illustrating preferred embodiments of the present invention and the contents described in the accompanying drawings.

[0023] In describing preferred embodiments of the present invention, known technologies or repetitive descriptions that may unnecessarily obscure the essence of the invention will be shortened or omitted.

[0024] FIG. 1 schematically illustrates the propellant charge ignition simulation device of the present invention and an ignition test system including the same.

[0025] Hereinafter, with reference to FIG. 1, a propellant charge ignition simulation device according to one embodiment of the present invention, an ignition test system including the same, and an ignition test method will be described.

[0026] The present invention relates to a device for simulating the ignition of a propellant charge, for example, a 155mm propellant charge, and a test system and a test method. As referenced in FIG. 1, the test system of the present invention has a combustion chamber (10) mounted on a flat surface on a frame (70), a breech portion (20) coupled to one end corresponding to the rear of the combustion chamber (10), and a base portion (30) mounted to the other end corresponding to the front.

[0027] Therefore, the propellant charge (40) loaded inside the combustion chamber (10) is combusted by the firing energy from the breech section (20), and the flame is propagated to the base section (30). A measuring device (80) measures this firing test and calculates the differential pressure and ignition time at the time of ignition through the measured data.

[0028] More specifically, the combustion chamber (10) is composed of a tube made of a transparent material such as acrylic resin, polycarbonate, or polystyrene, allowing the flame propagation phenomenon to be observed without obstruction during the initial ignition of the propellant charge (40). Additionally, as shown in FIG. 7, a transparent window (41) is formed in the propellant charge (40), thereby enabling the measurement of the flame propagation time through a high-speed camera.

[0029] The combustion chamber (10) can be manufactured to a suitable size according to the chamber volume of the gun system or the length of the propellant charge (40), and the base portion (30) and the spacer (50) additionally coupled to the base portion (30) to compensate for the length are designed to be positioned along the longitudinal axis according to the length of the combustion chamber (10).

[0030] A base support (60) is mounted on a frame (70) to support the base of the projectile (30), and the base support (60), which is a screw-type support, is designed to ensure the structural robustness of the base of the projectile (30) against the pressure generated after the ignition of the propellant charge (40).

[0031] Since the length of the propellant charge (40) varies depending on the amount of propellant grain filling, the ignition simulation device is able to obtain data on ignition characteristics according to the length of the propellant charge during the development process of the propellant charge.

[0032] The measuring device (80) may include a PC, a data collection device, and a high-speed camera, and can calculate differential pressure and ignition time through the measured data and can calculate them through a separate control device.

[0033] The differential pressure is defined as the value obtained by subtracting the internal pressure of the base (30) from the internal pressure of the breech (20), and the ignition time is determined by determining the ignition time of the propellant confirmed through high-speed camera images.

[0034] FIG. 2 is a cross-sectional shape of the breech portion of the propellant charge ignition simulation device of the present invention, wherein the breech portion (20) is formed with an open center, one end of the breech portion (20) is connected to the combustion chamber (10), and the other end is closed by the breech portion cover (22).

[0035] And, a firing device (23) and a primer (24) are provided on the central axis inside the breech cover (22), and the primer (24) ignites the propellant charge (40) inside the combustion chamber (10).

[0036] In addition, a sensor mounting portion (21) is formed in the shape of a hole or groove around the detonator (24) in the breech portion (20), allowing a sensor to be mounted in the sensor mounting portion (21).

[0037] Depending on the data to be measured, pressure sensors, thermocouples, etc., may be applied, and the size of the hole may vary depending on the size of the sensor.

[0038] FIG. 3 is a side cross-sectional shape of the base of the propellant charge ignition simulation device of the present invention, and FIG. 4 is the AA cross-sectional shape of FIG. 3. FIG. 5 is a side cross-sectional shape of the base cover of the propellant charge ignition simulation device of the present invention, and FIG. 6 is the BB cross-sectional shape of FIG. 5.

[0039] One end of the bullet base (30) is connected to the combustion chamber (10), and the other end is connected to the bullet base cover (32) using a fixing pin (33).

[0040] And, a sensor mounting portion (31) is formed in the shape of a hole or groove in the base portion (30), allowing a sensor to be mounted in the sensor mounting portion (31).

[0041] A hole is formed in the base cover (32) through which a sensor cable is drawn out to electrically connect the sensor mounted on the sensor mounting part (31).

[0042] That is, the sensor cable is protected by being wrapped in a sensor cable protection tube so as to be protected from fire, and the sensor cable protection tube is drawn out through a hole (34) for the sensor cable protection tube formed in the base cover (32) and connected to a measuring device (80).

[0043] As described above, the propellant charge ignition simulation device of the present invention has the effect of being able to more accurately measure the differential pressure and ignition time of the propellant charge.

[0044] That is, by setting the ignition test system described above, a propellant charge (40) is loaded into the combustion chamber (10), and the propellant charge (40) is ignited by detonating the primer (24) through the detonation device (23).

[0045] The flame generated by the ignition of the propellant charge (40) is measured by a high-speed camera of the measuring device (80), and the measuring device (80) receives the measurement values ​​from the sensors mounted on the breech (20) and the base (30), and the control device calculates the differential pressure and ignition time to test the ignition of the propellant charge.

[0046] Although the present invention has been described above with reference to the illustrated drawings, it is obvious to those skilled in the art that it is not limited to the described embodiments and can be modified and varied in various ways without departing from the spirit and scope of the invention. Accordingly, such modifications or variations should be deemed to fall within the scope of the claims of the present invention, and the scope of rights of the present invention should be interpreted based on the appended claims. Explanation of the symbols

[0047] 10: Combustion chamber 20 : Fomibu 21: Sensor mounting section 22 : Formiboo Cover 23: Firing device 24: Detonator 30: Anthrax 31: Sensor mounting section 32 : Anthrax cover 33 : Fixing pin 34: Hole for sensor cable protection tube 35 : Support groove 40 : Propellant charge 41 : Transparent window 50 : Spacer 60 : Anthracnose base support 70 : Frame 80: Measuring device

Claims

Claim 1 A propellant charge ignition test system comprising: a frame having a flat upper surface; a combustion chamber made of a transparent material mounted on the frame and having a propellant charge loaded into its internal space; a breech section coupled to one end of the combustion chamber, having a sensor mounting section formed therein with a primer and a firing device on a central axis and a sensor mounted around the primer; a base section coupled to the other end of the combustion chamber and having a sensor mounting section formed therein with a sensor mounted thereon; and a measuring device comprising a high-speed camera positioned outside the transparent combustion chamber and capturing the initial flame propagation phenomenon of the propellant through a transparent window formed in the propellant charge, and a control device that receives sensor measurement values ​​of the breech section and base section and images from the high-speed camera to calculate the differential pressure (subtracting the internal pressure of the base section from the internal pressure of the breech section) and the ignition time of the propellant, and measuring ignition characteristic data according to the change in the overall length of the propellant charge through a non-firing test. Claim 2 delete Claim 3 delete Claim 4 A propellant charge ignition test system according to claim 1, wherein one end of the breech portion is coupled to the combustion chamber and the other end is coupled to a breech portion cover, and a primer and a firing device for detonating the primer are mounted on a central axis inside the breech portion cover. Claim 5 A propellant charge ignition test system according to claim 4, characterized in that the breech portion has a sensor mounting portion formed therein for mounting a sensor around the primer. Claim 6 A propellant charge ignition test system according to claim 4, wherein one end of the base portion is coupled to the combustion chamber and the other end is coupled to a base portion cover. Claim 7 A propellant charge ignition test system according to claim 6, further comprising a spacer coupled to the base cover. Claim 8 A propellant charge ignition test system according to claim 6, further comprising a base support mounted on the frame and spaced apart from the base cover. Claim 9 A propellant charge ignition test system according to claim 8, characterized in that a sensor mounting portion for mounting a sensor is formed in the base portion thereof. Claim 10 A propellant charge ignition test system according to claim 9, further comprising: a sensor cable connected to the sensor; and a sensor cable protection tube for protecting the sensor cable, wherein a hole for the sensor cable protection tube is formed in the base cover for drawing the sensor cable protection tube outward. Claim 11 A propellant charge ignition test system according to claim 9, further comprising a sensor cable connected to the sensor of the propellant charge ignition test system, wherein the measuring device is connected to the sensor cable to receive the measured value of the sensor and measure the flame caused by the combustion of the propellant charge. Claim 12 delete Claim 13 A method for testing the ignition of a propellant charge using the propellant charge ignition test system of claim 11, comprising the steps of: preparing the propellant charge ignition test system by loading the propellant charge into the combustion chamber and connecting the sensor cable to the measuring device; igniting the propellant charge by detonating the primer through the detonation device; and measuring the flame resulting from the combustion of the propellant charge by the measuring device and receiving the measured value by the sensor. Claim 14 A propellant charge ignition test method according to claim 13, further comprising the step of calculating a differential pressure defined as the value obtained by subtracting the internal pressure of the base portion from the internal pressure of the breech portion from the internal pressure of the breech portion and the ignition time of the propellant of the propellant charge from the data measured by the measuring device.

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