A method for testing dynamic parameters of barreled weapons

Abstract

The present invention discloses a method for testing the dynamic parameters of barreled weapons, comprising: dividing each launch tube of a launch box into a launch unit and multiple test units, wherein the launch unit is located at the center of the test unit; fixing multiple sensors arranged at equal intervals along a circumference using a fixed sensor mechanism, and fixing the sensors inside the test unit. The fixed sensor mechanism also serves as a pressure-bearing unit for the gas jet, which is then transmitted to the sensors; grouping the test units equidistant from the launch unit center; rotating the fixed sensor mechanism to adjust the sensor positions so that the sensors of the test units in the same group are located on concentric circles centered on the launch unit, the number of concentric circles being the same as the number of sensors in the fixed sensor mechanism, each concentric circle forming a test group; and collecting test data from multiple test groups to obtain data at different radial positions. This method solves the problem of impact equal-diameter testing of the gas jet during the launch of a box-type rocket launcher.

Description

Technical Field

[0001] The invention belongs to the technical field of weapon testing equipment and relates to a method for testing dynamic parameters of a barreled weapon. Background Art

[0002] Weapon testing technology is based on engineering testing theory and focuses on the practical application of weapon testing. Quantitatively describing the state changes and characteristics of an object requires testing. Currently, there is a lack of specialized testing equipment for dynamic parameter testing of barreled weapons. This testing is significantly affected by the test system itself, and the lack of a reliable design introduces more interference from adverse environmental factors. Therefore, it is necessary to design an effective barreled weapon testing device to address the current test stability and reliability issues in rocket artillery testing.

[0003] First, regarding the acquisition of tiny signals, signals from the external environment are transmitted through various sensors to a secondary operational amplifier circuit. After undergoing analog-to-digital conversion on an acquisition card, they are transmitted to a host computer. Using the Labview data acquisition program, real-time data acquisition is displayed and stored. Secondly, testing barreled weapons often involves encountering different models and calibers. This sensor mounting mechanism meets the testing requirements of various barreled weapons, offering easy assembly and disassembly and high reliability, resolving a major challenge in testing experiments. The heat source of barreled weapons primarily comes from the high-temperature fluid in the tail flame. Ceramic insulation was installed during the experiment to prevent this high-temperature fluid from eroding and damaging the sensor.

[0004] However, the existing weapon testing system does not have such a widely applicable device. The existing barreled weapon testing device is relatively bulky, not conducive to field testing, the test is single and inflexible, there is no angle adjustment, and it is inconvenient to disassemble and assemble. Summary of the Invention

[0005] The object of the present invention is to provide a method for testing the dynamic parameters of a barreled weapon, which is used to test the dynamic parameters of a box-type barreled weapon.

[0006] The technical solutions for achieving the purpose of the present invention are:

[0007] A method for testing dynamic parameters of a barreled weapon, comprising:

[0008] Divide each launch tube of the launch box into a launch unit and multiple test units, wherein the launch unit is located in the center of the test unit;

[0009] A plurality of sensors arranged at equal intervals along the circumference are fixed by a fixed sensor mechanism, and the sensors are fixed inside the test unit. The fixed sensor mechanism serves as a pressure-bearing unit for the gas jet and transmits the pressure to the sensors.

[0010] Divide the test units that are equidistant from the center of the transmitting unit into a group, rotate the fixed sensor mechanism to adjust the sensor positions so that the sensors of the test units in the same group are located on concentric circles centered on the transmitting unit. The number of concentric circles is the same as the number of sensors in the fixed sensor mechanism, and each concentric circle constitutes a test group.

[0011] After the launch unit completes the launch, it collects test data of multiple test groups to obtain data at different radial positions.

[0012] Compared with the prior art, the present invention has the following significant advantages:

[0013] (1) By dividing the launch tubes with equal center distances into a group, the fixed sensor mechanism is rotated to adjust the sensor position so that the sensor positions of the test units in the same group are located on concentric circles centered on the launch unit. Each concentric circle constitutes a test group, which solves the problem of equal-diameter impact test of the gas jet during the launch process of a box-type rocket launcher.

[0014] (2) The sensor fixing mechanism uses a ceramic ring for thermal insulation, which can simultaneously meet the requirements of isolating the influence of gas flow temperature and preventing gas flow from overflowing from the gap, and can obtain a reliable amplified signal. The board card concentration is high and it is easy to carry. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is a module diagram of a method for testing dynamic parameters of a barreled weapon according to the present invention;

[0016] Figure 2 This is a general diagram of a fixed sensor mechanism for a method of testing dynamic parameters of a barreled weapon according to the present invention;

[0017] Figure 3 This is a schematic diagram of a method for testing dynamic parameters of a barreled weapon according to the present invention;

[0018] Figure 4 This is a diagram of the back structure of a web of a method for dynamic parameter testing of a barreled weapon according to the present invention;

[0019] Figure 5 This is a diagram of the web structure of a method for testing dynamic parameters of a barreled weapon according to the present invention;

[0020] Figure 6 This is a star frame structure diagram of a method for testing dynamic parameters of barreled weapons according to the present invention;

[0021] Figure 7 This is a structural diagram of a hinge bracket for a method for testing dynamic parameters of a barreled weapon according to the present invention. DETAILED DESCRIPTION

[0022] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0023] The present invention provides a method for testing dynamic parameters of barreled weapons. According to the impact characteristics of the gas jet during the launch process of a box-type rocket launcher, each launch tube of the launch box is divided into a launch unit and multiple test units, wherein the launch unit is located at the center of the test unit. Figure 3 In the figure, tube A is used as the transmitting unit. In theory, the measured pressure tends to decrease gradually along the radial direction with the transmitting unit A as the center. Therefore, the actual sensor measuring points are arranged on concentric circles of different radii with the transmitting unit A as the center. Since the transmitting tubes are usually arranged in a square array, the center distances between other test units and the transmitting unit are not equal. The test units and the transmitting unit do not form a circular array, resulting in the inability to form a circular test center. Therefore, the test method of the present invention is developed based on the following device to achieve equal diameter testing with the transmitting unit A as the center.

[0024] like Figure 1 As shown in FIG, the device consists of a host computer, an STM32F103ADC module, a secondary operational amplifier circuit, a fixed sensor mechanism, a sensor and an SD card; the physical quantity measured by the sensor is converted into a changing voltage, and this tiny (mV level) voltage is amplified to the voltage range to be measured (0~5V) through the operational amplifier circuit, and then the analog signal is transmitted to the STM32ADC module to be converted into a digital signal, which reaches the host computer through the USB bus, and the Labview software is used to collect the continuously changing physical quantity from the sensor; Figure 2-Figure 7 As shown, the fixed sensor mechanism includes an air-facing surface base plate 1 (serving as a pressure-bearing surface for the gas jet) which cooperates with the barrel and is located at the mouth of the barrel. Engraved lines and reused screw holes are provided on the air-facing surface base plate 1. The engraved lines have a calibration function for adjusting the circumferential angle. The reused screw holes are used as mounting holes. The air-facing surface base plate 1 is connected to the web through the reused screw holes to realize the detachable replacement of the web. Threaded holes 8 are provided on the web for connection with the reused screw holes of the air-facing surface base plate 1. Matching screw holes for installing three sensors 5 are designed in the web. The screw holes are arranged at equal intervals along the circumference (coaxial with the sensor drainage holes 10 on the screw hole air-facing surface base plate 1). Insulating ceramic rings 7 and O-rings 6 (green fluorine) are provided in the screw holes to provide thermal insulation and meet the sealing requirements. Figure 4 As shown, three fixed hinge supports are evenly distributed along the circumferential direction inside the web, which are used to hinge the hinge bracket 2. One end of the hinged hinge bracket 2 is hinged to the fixed hinge support, and the other end is provided with a convex circle, which is connected to the inner wall of the barrel through the convex circle of the hinge bracket 2; the central bolt countersunk hole 9 of the web is used to connect the fastening bolt 4, and the fastening bolt 4 is connected to a star frame 3, and the star frame 3 is provided with three sliding arms, which respectively slide with the sliding grooves of the hinge bracket 2; by rotating the fastening bolt 4, the star frame 3 is displaced relative to the air-facing surface base plate 1, so that the three hinge brackets 2 can be extended and retracted at the same time, completing the fixation or separation of the entire fixed sensor mechanism and the inner wall of the barrel.

[0025] When using the device to test the dynamic parameters of a barreled weapon, first connect the sensor 5 (which can be a temperature sensor, pressure sensor, etc. as needed) to the fixed sensor mechanism, then connect it to the secondary operational amplifier circuit, then connect it to the STM32F103ADC module, and finally connect it to the host computer through the USB bus; the assembly of the fixed sensor mechanism is as follows: assemble the three groups of ceramic rings 7 with O-rings 6 respectively, and gently place them into the three assembly threads on the air-facing base cover 1 in turn, adjust the position of the center hole of the ceramic ring 7 and the center hole of the thread, keep them concentric with the drainage hole, and then slowly screw the sensor 5 into the assembly thread. At this time, ensure that the air-facing base cover 1 is placed horizontally. With continuous spinning, the end face of the sensor 5 is contacted and compacted with the end face of the ceramic ring 7, ensuring that the structure is stable. The stability of the components and the sealing of the structure; screw the three sensors 5 into the threaded holes of the base cover 1 in turn; after the installation is completed, slowly put the mechanism with the assembled sensors 5 into the barrel, adjust the appropriate circumferential angle, and adjust the radial positions of the three sensors relative to the center of the launching unit A according to the engraved lines on the airborne base cover 1. The three sensors 5 are respectively located on different concentric circles (centered on the center of the launching unit A); at this time, pass the fastening bolt 4 through the fastening bolt countersunk hole 9 and cooperate with the threaded hole on the star frame 3. As the thread is continuously screwed in, the distance between the airborne base cover 1 and the star frame 3 gradually decreases, and the hinge bracket 2 will be pulled up by the star frame 3. The three-point posture formed increases, and finally the convex circle of the hinge bracket 2 is in close contact with the inner wall of the barrel, achieving the function of reliable fastening.

[0026] When the inner diameter of the barrel is different, different sizes of double plates can be used to connect with the air-facing surface substrate 1, and assembled and fixed through the double plate threaded holes 8 to meet the test needs; the air-facing surface substrate 1 is made of high-quality carbon steel, has good rigidity, can resist the impact of the jet, and has a long service life; the jet passes through the sensor drainage hole 10 on the air-facing surface substrate 1, and the airflow is transferred to the test end of the sensor 5; there is a ceramic ring 7 between the sensor 5 and the substrate 1, which isolates the influence of the jet height on the sensor 5; at the same time, it is equipped with an O-ring 6, which plays a sealing role to ensure that the airflow will not overflow from the thread gap, thereby realizing effective collection of dynamic parameters.

[0027] like Figure 3 As shown, this embodiment takes the transmitting unit A as the center and there are 8 test units around it as an example. The 8 test units are ①②③④⑤⑥⑦⑧, among which the center distances of ①②③④ transmitting tubes and the transmitting tube A are equal (located above, below, left and right of A in the figure), and the center distances of ⑤⑥⑦⑧ transmitting tubes and the transmitting tube A are equal (located at 45 degrees to the four corners in the figure). Each test unit contains 3 sensors, namely x, y, and z, among which x, y, and z are arranged in a counterclockwise direction to form an equilateral triangle with x, y, and z as vertices. According to the test requirements, ensure that the three sensors x, y, and z are located on three concentric circles with different radii, and adjust the positions of x, y, and z to achieve the following. Figure 3 The test positions shown form 6 concentric circles (shown by dotted lines in the figure). Each circle of equal radius has 4 x (y or z) sensors evenly distributed on it, serving as a test group. Among them, the 4 x, 4 y, and 4 z sensors in the 1, 2, 3, and 4 test units, 4 x, 4 y, and 4 z, 4 x constitute the smallest concentric circle in the group, 4 y constitute the largest concentric circle in the group, and 4 z are located in the middle concentric circle, totaling three concentric circles. Similarly, the 4 x, 4 y, and 4 z sensors in the 5, 6, 7, and 8 test units form a total of 6 concentric circle test groups. Each test group measures 4 test data, and the average measurement value is taken to obtain the test data on that radius. Similarly, the measured values ​​of the 6 test groups are averaged to obtain more reliable test data.

Claims

1. A method for testing dynamic parameters of a barreled weapon, characterized in that: include: Divide each launch tube of the launch box into a launch unit and multiple test units, wherein the launch unit is located in the center of the test unit; By arranging a plurality of sensors at equal intervals along the circumference of the fixed sensor mechanism and fixing the sensors inside the test unit, the fixed sensor mechanism serves as a pressure-bearing unit for the gas jet and transmits it to the sensors; Divide the test units that are equidistant from the center of the transmitting unit into a group, rotate the fixed sensor mechanism to adjust the sensor positions so that the sensors of the test units in the same group are located on concentric circles centered on the transmitting unit. The number of concentric circles formed by the sensors of each group of test units is the same as the number of sensors of the grouped test units, and each concentric circle constitutes a test group. After the launch unit completes the launch, it collects test data of multiple test groups to obtain data at different radial positions.

2. The method for dynamic parameter testing of a barreled weapon according to claim 1, wherein: The fixed sensor mechanism includes: The gas-facing base plate is located at the mouth of the barrel when in use and serves as the pressure-bearing surface for the gas jet, and is provided with multiple drainage holes; The telescopic mechanism is capable of expanding and contracting relative to the inner wall of the barrel, and when expanded, it conforms to the inner wall of the barrel to fix the entire fixed sensor mechanism within the inner wall of the barrel; A plurality of sensors are arranged at equal intervals along the circumference and fixed to the air-facing surface substrate.

3. The method for dynamic parameter testing of a barreled weapon according to claim 2, wherein: The telescopic mechanism comprises: The fastening bolts can rotate relative to the air-facing substrate to drive the movement of the star frame relative to the air-facing substrate; a star frame connected with the fastening bolts and sliding with the hinge bracket; A plurality of hinge brackets are arranged at equal intervals along the circumference and can realize opening and / or contraction actions during the movement of the star frame.

4. The method for dynamic parameter testing of a barreled weapon according to claim 3, wherein: The end of the hinge bracket is provided with a convex structure.

5. The method for dynamic parameter testing of a barreled weapon according to claim 2, wherein: The air-facing surface base plate is provided with a replaceable belly plate to adapt to barrels of different calibers.

6. The method for dynamic parameter testing of a barreled weapon according to claim 1, wherein: Each test unit is equipped with three sensors, forming an equilateral triangle. The three sensors are located on three concentric circles with different radii centered on the center of the transmitting unit. The same group of test units forms three test groups.

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