Device for dynamically measuring burning speed of electronic control solid propellant by using target line method

Abstract

The invention discloses a device for dynamically measuring the burning rate of an electronic control solid propellant by using a target line method, an electrode moving module can drive an ignition electrode module to integrally move up and down, and under the action of a spring, an output electrode can realize small-range movement in an electrode clamp; the integral movement of the ignition electrode module and the small-range movement of the output electrode can ensure that the output electrode is in dynamic contact with the burning surface of the solid propellant to be measured, that is, the descending position of the electrode is consistent with the retreating of the burning surface in the process of dynamically measuring the burning speed of the electronic control solid propellant by using a target line method; and the measurement accuracy of the burning speed of the electronic control solid propellant is ensured.

Description

Technical Field

[0001] The invention relates to the technical field of electronically controlled solid propellants, and in particular to a device for dynamically measuring the burning rate of electronically controlled solid propellants using a target line method. Background Art

[0002] As the energy source of solid rocket engines, propellant plays a decisive role in the performance and working performance of solid rocket engines. The burning rate of propellant refers to the burning speed of propellant, which is defined as the distance the propellant moves parallel to the combustion per unit time.

[0003] At present, the target wire method is the most widely used method for testing the burning rate of propellants. Its principle is to drill holes through target wires at a certain distance on the propellant sample. A certain voltage is loaded on the target wire. When the propellant burns, the target wire is burned off, and the voltage in the circuit is detected to drop rapidly. The average burning rate of the propellant is calculated by the time interval between the voltage drop of the two target wires and the distance between the two target wires. The target wire method requires that the propellant has the characteristics of continuous combustion after ignition, that is, self-sustaining combustion.

[0004] Electronically controlled solid propellant is a new type of solid propellant that adds electrolytically combustible fuel to the solid propellant to achieve the effect of burning when powered on and extinguishing when powered off. It does not have the characteristics of self-sustaining combustion and requires continuous application of voltage to maintain the combustion state. The electrode that provides the voltage needs to maintain dynamic contact with the burning surface of the electronically controlled propellant. Therefore, the contact method between the electrode and the electronically controlled propellant greatly affects the burning rate of the electronically controlled solid propellant. The contact between the two should maintain a small force to minimize the impact of external forces on the electronically controlled solid propellant. At the same time, as the electronically controlled solid propellant burns, the spatial position of the burning surface will also change over time. This requires that the position of the external electrode needs to be consistent with the burning surface, such as Figure 1 As shown in (A), the external electrode needs to move downward along with the retreat of the burning surface.

[0005] Since the burning rate of the new electronically controlled solid propellant itself is unknown and the burning rate of the new electronically controlled solid propellant does not remain constant throughout the combustion process, making the electrode drop evenly at a certain speed cannot ensure the normal electrolytic combustion of the new electronically controlled solid propellant, which may lead to inaccurate or impossible measurement of the burning rate of the new electronically controlled solid propellant. Figure 1 As shown in (B), when the electrode moves too slowly, the applied voltage cannot act on the surface of the electronically controlled propellant, causing the electronically controlled solid propellant to extinguish, and its accurate burning rate cannot be tested. Figure 1 As shown in (C), when the electrode descends too quickly, the electronically controlled solid propellant will be subjected to a greater force, which will affect the accuracy of the burning rate and in severe cases will damage the electronically controlled solid propellant sample. Summary of the invention

[0006] Based on this, it is necessary to provide a device for dynamically measuring the burning rate of electronically controlled solid propellant using the target line method to address the above-mentioned technical problems. The device can keep the electrode lowering position consistent with the retreat of the burning surface during the process of dynamically measuring the burning rate of electronically controlled solid propellant using the target line method, thereby ensuring the accuracy of the burning rate measurement of the electronically controlled solid propellant.

[0007] The present invention provides a device for dynamically measuring the burning rate of an electrically controlled solid propellant using a target line method, comprising a base;

[0008] The electrode moving module includes two ball screw guide rails both vertically fixed to the top of the base;

[0009] A data acquisition module, the data acquisition module is used to collect the combustion data of the electronically controlled solid propellant to be tested and calculate the burning rate of the electronically controlled solid propellant to be tested;

[0010] An ignition electrode module, the ignition electrode module includes a power supply, an output electrode, an electrode disk and two electrode fixtures. The power supply is electrically connected to the output electrode. The output electrode is fixedly embedded in the center of the electrode disk and is used to maintain dynamic contact with the burning surface of the electronically controlled solid propellant to be tested. The two electrode fixtures are located in the same plane and are respectively fixedly connected to two ball screw guide rails.

[0011] The electrode fixture is a U-shaped fixture, the U-shaped openings of the two electrode fixtures are arranged opposite to each other, the U-shaped side walls of the electrode fixture are parallel to the base, the electrode disk is arranged in the middle of the U-shaped openings of the two electrode fixtures, and the plane where the electrode disk is located is parallel to the plane where the base is located;

[0012] Each electrode fixture is provided with N groups of springs, N is 2 or 3, any group of springs is vertically arranged inside the U-shaped opening of the electrode fixture, each group of springs includes a short spring and a long spring, one end of the short spring is fixedly connected to the upper side wall of the U-shaped opening of the electrode fixture, the other end of the short spring is fixedly connected to the top of the electrode disk, one end of the long spring is fixedly connected to the lower side wall of the U-shaped opening of the electrode fixture, and the other end of the long spring is fixedly connected to the bottom of the electrode disk;

[0013] The moving speed of the electrode fixture driven by the ball screw guide mechanism is the maximum predicted burning speed of the electronically controlled solid propellant to be tested.

[0014] In one embodiment, the elastic constants of the short spring and the long spring are both k, where

[0015] ΔF=2kNΔx

[0016] Δx=(v 1 -v 2 )·t

[0017]

[0018] Where ΔF represents the total weight of the output electrode and electrode disk, v 1 Indicates the moving speed of the ignition electrode module, v 2 represents the minimum predicted burning rate of the electronically controlled solid propellant to be tested, Δx represents the maximum relative displacement between the output electrode and the burning surface of the electronically controlled solid propellant to be tested, t is the maximum predicted burning time of the electronically controlled solid propellant to be tested, and l is the length of the electronically controlled solid propellant to be tested.

[0019] In one of the embodiments, the deformation length of the long spring is greater than the maximum relative displacement between the output electrode and the burning surface of the electronically controlled solid propellant to be tested.

[0020] In one of the embodiments, the base is provided with a through hole and at least three target wire terminals;

[0021] The through hole is coaxially arranged with the electrode disk and is used for installing the electronically controlled solid propellant to be tested when performing a burning rate test;

[0022] The target line terminal is fixedly connected to the top of the base.

[0023] In one embodiment, the data acquisition module includes two target lines, a voltage divider module, an acquisition board and a computer;

[0024] Each target wire is used to pass through the electronically controlled solid propellant to be tested and then be connected to two target wire terminals respectively, and the two target wire terminals serve as a positive electrode and a negative electrode respectively;

[0025] The voltage divider module is used to reduce the voltage signal collected on the target line. The voltage divider module is provided with two resistors, each resistor is connected to the target line terminals of two different electrodes;

[0026] The acquisition board is used to collect the voltage signal after the voltage is stepped down by the voltage divider module at a sampling frequency of 20000 Hz and store it in the computer.

[0027] In one embodiment, the two electrode fixtures are fixedly connected to the slides of the two ball screw guide mechanisms respectively, and the motors of the two ball screw guide mechanisms are synchronized and have the same speed.

[0028] In one embodiment, the long spring or the short spring is threadedly connected to the electrode disk.

[0029] In one embodiment, the target line is connected to an external 24V regulated power supply via a wire.

[0030] The beneficial effects of the present invention are as follows: in the device for dynamically measuring the burning rate of an electrically controlled solid propellant using the target line method, the electrode moving module can drive the ignition electrode module to move up and down as a whole, and under the action of the spring, the output electrode can achieve a small range of movement in the electrode fixture, and the overall movement of the ignition electrode module and the small range of movement of the output electrode can ensure that the output electrode and the burning surface of the solid propellant to be measured maintain dynamic contact, that is, in the process of dynamically measuring the burning rate of an electrically controlled solid propellant using the target line method, the electrode descending position can be kept consistent with the retreat of the burning surface, thereby ensuring the accuracy of the burning rate measurement of the electrically controlled solid propellant. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 It is a schematic diagram of the matching between the electrode and the electronically controlled solid propellant;

[0032] Figure 2 A schematic diagram of the structure of a device for dynamically measuring the burning rate of an electrically controlled solid propellant using a target line method provided in an embodiment of the present invention;

[0033] Figure 3 A schematic diagram of the structure of an ignition electrode module in a spring balanced state provided by an embodiment of the present invention;

[0034] Figure 4 This is a voltage change state diagram collected by the data collection module provided in an embodiment of the present invention.

[0035] Wherein: 100, base; 200, ball screw guide mechanism; 300, output electrode; 400, electrode disk; 500, electrode fixture; 600, short spring; 610, long spring; 700, data acquisition module; 800, target line terminal; 900, electronically controlled solid propellant to be tested. DETAILED DESCRIPTION

[0036] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0037] It should be noted that in the description of the present invention, “upper”, “lower”, “top”, “bottom”, orientation or position relationship is based on the attached Figure 2 Regarding the orientation or positional relationship shown, it should be understood that these orientation terms are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0038] In one embodiment, Figure 2 As shown, Figure 2 A schematic diagram of the structure of a device for dynamically measuring the burning rate of an electronically controlled solid propellant using a target line method provided in an embodiment of the present invention. The device of this embodiment includes:

[0039] A base 100; an electrode moving module, the electrode moving module includes two ball screw guide mechanisms 200 both vertically fixed to the top of the base 100; a data acquisition module 700, the data acquisition module 700 is used to collect combustion data of the electronically controlled solid propellant 900 to be tested and calculate the burning rate of the electronically controlled solid propellant 900 to be tested.

[0040] Specifically, the base 100 has insulating properties, is made of insulating materials or has undergone surface insulation treatment, and the two ball screw guide mechanisms 200 are provided on both sides of the top surface of the base 100, with a distance in the middle that allows the ignition electrode module to move up and down. The electronically controlled solid propellant 900 to be tested is cylindrical.

[0041] like Figure 3 As shown, the ignition electrode module includes a power supply, an output electrode 300, an electrode disk 400 and two electrode clamps 500. The power supply is electrically connected to the output electrode 300. The output electrode 300 is fixedly embedded in the center of the electrode disk 400 and is used to maintain dynamic contact with the burning surface of the electronically controlled solid propellant 900 to be tested. The two electrode clamps 500 are located in the same plane and are respectively fixedly connected to two ball screw guide mechanisms 200.

[0042] Specifically, the power source is a high voltage stabilized power source. The electrode disk 400 is annular, and the output electrode 300 is round. The output electrode 300 can be interlocked with the electrode disk 400, and the two are insulated from each other.

[0043] In this embodiment, the high voltage stabilized power supply is connected to the output electrode 300 via a wire to ensure that the output electrode 300 has a high voltage.

[0044] In this embodiment, the electrode fixture 500 is a U-shaped fixture, the U-shaped openings of the two electrode fixtures 500 are arranged opposite to each other, the U-shaped side walls of the electrode fixture 500 are parallel to the base 100, the electrode disk 400 is arranged in the middle of the U-shaped openings of the two electrode fixtures 500, and the plane where the electrode disk 400 is located is parallel to the plane where the base 100 is located;

[0045] Each electrode fixture 500 is provided with N groups of springs, N is 2 or 3, any group of springs is vertically arranged inside the U-shaped opening of the electrode fixture 500, each group of springs includes a short spring 600 and a long spring 610, one end of the short spring 600 is fixedly connected to the upper side wall of the U-shaped opening of the electrode fixture 500, the other end of the short spring 600 is fixedly connected to the top of the electrode disk 400, one end of the long spring 610 is fixedly connected to the lower side wall of the U-shaped opening of the electrode fixture 500, and the other end of the long spring 610 is fixedly connected to the bottom of the electrode disk 400;

[0046] The ball screw guide mechanism 200 drives the electrode fixture 500 to move at a speed that is equal to the maximum predicted burning rate of the electrically-controlled solid propellant 900 to be tested, thereby preventing the electrically-controlled solid propellant from being extinguished due to the external voltage being unable to act on the surface of the electrically-controlled propellant grains because the moving speed of the electrode fixture 500 is too slow.

[0047] Specifically, the long spring 610 or the short spring 600 is threadedly connected to the electrode disk 400 .

[0048] In one embodiment, the elastic coefficients of the short spring 600 and the long spring 610 are both k, where

[0049] ΔF=2kNΔx

[0050] Δx=(v 1 -v 2 )·t

[0051]

[0052] Wherein, ΔF represents the total weight of the output electrode 300 and the electrode disk 400, v 1 Indicates the moving speed of the ignition electrode module, v 2 represents the minimum predicted burning rate of the electronically controlled solid propellant 900 to be tested, Δx represents the maximum relative displacement between the output electrode 300 and the burning surface of the electronically controlled solid propellant 900 to be tested, t is the maximum predicted burning time of the electronically controlled solid propellant 900 to be tested, and l is the length of the electronically controlled solid propellant 900 to be tested.

[0053] Specifically, the determination and analysis of the elastic coefficients of the long spring 610 and the short spring 600 are as follows:

[0054] In this embodiment, the installed electrode disk 400 and the output electrode 300 are subjected to force analysis as a whole. They are subjected to their own gravity, the tension of the short spring 600 and the support force of the long spring 610. When they come into contact with the electronically controlled solid propellant, they may also be subjected to the upward support force of the electronically controlled solid propellant.

[0055] In order to correctly measure the burning rate of the electronically controlled solid propellant, the upward support force of the electronically controlled solid propellant should be reduced as much as possible. In this embodiment, the upward support force of the electronically controlled solid propellant is replaced by the elastic force of two springs to correspondingly reduce the reaction force of the electrode on the electronically controlled solid propellant.

[0056] In this embodiment, the elastic force of the spring increases with the increase of displacement. Whenever the ignition electrode in a force balance state has a displacement of Δx, its resultant external force kΔx increases. This increased resultant external force will act on the electric-controlled solid propellant, so k needs to be as small as possible to reduce the force on the electric-controlled solid propellant. The displacement in the increase of the resultant external force kΔx is generated by the difference in the burning rate of the electric-controlled solid propellant and the moving speed of the electrode moving device. Therefore, a maximum estimated value of the burning rate needs to be given before the test, and the speed of the electrode moving device is set to the maximum estimated value. The displacement difference caused by the offset between the estimated value and the actual burning rate will be compensated by the expansion and contraction of the special spring, ensuring that the ignition electrode is always in dynamic contact with the burning surface of the electric-controlled solid propellant and the external force acting on the electric-controlled solid propellant is small, thereby minimizing the impact on the burning rate test.

[0057] For example, the electronically controlled solid propellant sample is a cylinder with a diameter of 10 mm and a length of 16 mm, on which two heat-melting target wires are distributed with a spacing of 15 mm, and each electrode fixture 500 is provided with 2 sets of springs. The electrode gravity is 10N, and the natural lengths of the short spring 600 and the long spring 610 in each set of springs are 1cm and 9cm respectively. In the equilibrium state, the electrode is 1cm away from the lower end of the electrode fixture 500, providing a total upward elastic force of 10N to balance the electrode gravity. In this example, the electronically controlled propellant is 16cm, and the estimated burning rate of the electronically controlled propellant is 5±1cm / s, so the maximum test time is 4s. Since the device of this embodiment has the function of automatically adjusting the relative position of the output electrode 300 and the electronically controlled propellant, the moving speed of the electrode fixture 500 is given to be 6 cm / s, the difference between the burning speed and the maximum moving speed of the electrode fixture 500 is 2 cm / s, and under the condition of the longest test time of 4 seconds, the maximum relative displacement of the electrode and the propellant is 8 cm. In this case, the spring returns to the natural length and no longer provides elastic force. The maximum force between the electrode and the electronically controlled propellant is the weight of the electrode itself, 10 N. Then, the calculation formula of the elastic coefficient of the spring is:

[0058] 10=2k×2×8

[0059] 8 = (6-4) 4

[0060]

[0061] The final calculated elastic constant of the spring is 0.3125N / cm.

[0062] It should be noted that in actual tests, the situation that the central axis of the electronically controlled propellant and the center of gravity of the electrode do not coincide with each other often occurs due to the uneven combustion of the electronically controlled propellant, which will cause the electrode to deflect under the action of torque, and the spring on one side may be stretched and the spring on the other side may be compressed. In this embodiment, the combination of the upper spring and the lower spring can better balance the torque when the torque on both sides is uneven, ensure the horizontal state of the electrode, and better provide an external electric field for the burning surface of the electronically controlled solid propellant for electrolytic combustion.

[0063] In one of the embodiments, the deformation length of the long spring 610 is greater than the maximum relative displacement between the output electrode 300 and the burning surface of the electrically-controlled solid propellant 900 to be tested, which can ensure that the spring can support the output electrode 300 to move within a small range and can compensate for all displacement deviations between the output electrode 300 and the burning surface of the electrically-controlled solid propellant 900 to be tested, thereby achieving dynamic contact between the output electrode 300 and the burning surface of the electrically-controlled solid propellant 900 to be tested.

[0064] In one embodiment, the base 100 is provided with a through hole and at least three target wire terminals 800; the through hole is coaxially arranged with the electrode disk 400 for installing the electronically controlled solid propellant 900 to be tested when performing a burning rate test; the target wire terminals 800 are fixedly connected to the top of the base 100.

[0065] In this embodiment, the target wire terminal 800 is made of copper. The entire target wire terminal 800 penetrates and is fixed to the base 100 . Nuts such as fixing nuts for fixing the connecting wire are provided at both ends of the target wire terminal 800 .

[0066] In one embodiment, the data acquisition module 700 includes two target lines, a voltage divider module, an acquisition board and a computer; each target line is used to pass through the electronically controlled solid propellant 900 to be tested and then connected to two target line terminals 800, respectively, and the two target line terminals 800 serve as a positive electrode and a negative electrode, respectively; the voltage divider module is used to reduce the voltage signal on the target line collected, and the voltage divider module is provided with two resistors, each resistor is connected to two target line terminals 800 with different electrodes; the acquisition board is used to collect the voltage signal after the voltage is reduced by the voltage divider module at a sampling frequency of 20000 Hz and store it in the computer.

[0067] The voltage divider module is a resistor series module, and the two resistors of the voltage divider module may have the same or different resistance values. In this embodiment, two resistors with a large resistance value and a small resistance value are connected in series and then connected to the positive and negative ends of a target line, that is, two electrodes connected to a target line with different electrodes, and the voltage on the large and small resistors distributes the total voltage on the target line to each resistor according to the resistance ratio. Reasonable design of the ratio of the two resistors can reduce the total voltage on the target line and prevent the voltage from being too large and exceeding the range of the acquisition device.

[0068] In this embodiment, the target wire is connected to an external 24V stabilized power supply through a wire. Specifically, the target wire is a 0.3mm heat-melting wire, and the two target wires pass through the upper and lower sides of the electronically controlled solid propellant 900 to be tested, respectively, and the distances between the two target wires and the propellant are known.

[0069] In one embodiment, the two electrode fixtures 500 are respectively fixedly connected to the slides of the two ball screw guide mechanisms 200, and the motors of the two ball screw guide mechanisms 200 are synchronized and have the same speed. The motors of the ball screw guide mechanisms 200 can synchronously drive the electrode fixtures 500 to move up and down with adjustable speed and adjustable stroke.

[0070] The working process of the device for dynamically measuring the burning rate of electronically controlled solid propellant using the target line method of the present invention is as follows:

[0071] First, connect and tighten each module, ensure that the target line terminal 800 and the electrode moving module are firmly connected to the base 100, and check whether each component is completely insulated.

[0072] Next, the spring is connected to the electrode disk 400, the insulation state of the output electrode 300 and the spring is checked, and the freedom of the ignition electrode module to move up and down is checked. Then, it is checked whether the electrode moving module can synchronously drive the electrode fixture 500 to move up and down according to the set speed and stroke.

[0073] Next, place the electronically controlled solid propellant 900 to be tested with a target line at a certain distance in the through hole, connect the target line to the target line terminal 800, connect the target line terminal and the data acquisition module 700 with a wire, power the target line, and check whether the data acquisition module 700 monitors and records normally.

[0074] As the test begins, the electrode moving device drives the electrode fixture 500 to move downward close to the electrically-controlled solid propellant 900 to be tested. When the output electrode 300 contacts the electrically-controlled solid propellant 900 to be tested, the electrically-controlled solid propellant 900 to be tested begins to burn, and the burning surface begins to retreat downward. The electrode moving module continues to move downward. Since the output electrode 300 has a certain difference in burning rate from the electrically-controlled solid propellant 900 to be tested, it undergoes a certain displacement relative to the electrode fixture 500. At the same time, the spring begins to deform, continuously compensating for the force exerted on the electrically-controlled solid propellant 900 by the total gravity of the output electrode 300 and the electrode disk 400.

[0075] Finally, when the burning surface retreats to the target line position, the target line is burned out and the voltage loaded on it decreases rapidly. This process is monitored and recorded by the data acquisition module 700. The electronically controlled combustion rate of the electronically controlled solid propellant 900 to be tested is calculated based on the target line spacing and the time interval for the voltage on the target line to decrease.

[0076] In a specific embodiment, how the present invention calculates the burning rate of electronically controlled combustion is described.

[0077] In this embodiment, the target line spacing on the electric-controlled solid propellant 900 to be tested is 20mm, the estimated burning rate is 5mm / s, the electrode moving device is set at a speed of 6mm / s, the Hooke coefficient of a single spring is 0.1N / cm, the electrode's own weight is 10N, the initial deformation is 10mm, the allowable compensation deformation is 10mm, and when the relative displacement between the ignition electrode and the electrode clamp is within 10mm, the force on the electric-controlled solid propellant is always less than the ignition electrode's own weight. The data acquisition module 700 has a sampling rate of 200000Hz, the voltage on the target line is about 3.3V, the voltage reduction process of the target line being burned by the propellant does not exceed 3ms, and the voltage change collected by the data acquisition module 700 is as follows: Figure 4 shown.

[0078] Depend on Figure 4 It can be seen that the data acquisition module 700 accurately monitors the process of voltage reduction on the two target lines with an error of 0.003s. According to the spacing of 20mm between the target lines, the burning rate of the electronically controlled solid propellant is calculated to be 5.24mm / s.

[0079] The device for dynamically measuring the burning rate of an electronically controlled solid propellant using the target line method of the present invention can measure the burning rate of the electronically controlled propellant by cooperating with an electrode moving module and a spring. During the process, it is ensured that the output electrode 300 follows the retreat of the burning surface and the force of the output electrode 300 on the electronically controlled propellant to be measured is reduced to the greatest extent, so that the burning rate of the electronically controlled solid propellant can be accurately measured.

[0080] The above-mentioned embodiments only express several implementation methods of the present invention, and the description thereof is relatively specific and detailed, but it cannot be understood as limiting the scope of the present invention. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present invention, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the attached claims.

Claims

1. A device for dynamically measuring the burning rate of an electronically controlled solid propellant using a target line method, characterized in that: comprising a base (100); An electrode moving module, the electrode moving module comprising two ball screw guide rail mechanisms (200) both vertically fixed to the top of the base (100); A data acquisition module (700), the data acquisition module (700) being used to acquire combustion data of the electronically controlled solid propellant (900) to be tested and to calculate the burning rate of the electronically controlled solid propellant (900) to be tested; An ignition electrode module, the ignition electrode module comprising a power supply, an output electrode (300), an electrode disk (400) and two electrode fixtures (500), the power supply being electrically connected to the output electrode (300), the output electrode (300) being fixedly embedded in the center of the electrode disk (400) and being used to maintain dynamic contact with the burning surface of the electrically controlled solid propellant (900) to be tested, the two electrode fixtures (500) being located in the same plane and being fixedly connected to two ball screw guide mechanisms (200) respectively; The electrode fixture (500) is a U-shaped fixture, the U-shaped openings of the two electrode fixtures (500) are arranged opposite to each other, the U-shaped side walls of the electrode fixture (500) are parallel to the base (100), the electrode disk (400) is arranged in the middle of the U-shaped openings of the two electrode fixtures (500), and the plane where the electrode disk (400) is located is parallel to the plane where the base (100) is located; Each of the electrode clamps (500) is provided with N groups of springs, N is 2 or 3, any group of springs is vertically arranged inside the U-shaped opening of the electrode clamp (500), and each group of springs comprises a short spring (600) and a long spring (610), one end of the short spring (600) is fixedly connected to the upper side wall of the U-shaped opening of the electrode clamp (500), and the other end of the short spring (600) is fixedly connected to the top of the electrode disk (400), one end of the long spring (610) is fixedly connected to the lower side wall of the U-shaped opening of the electrode clamp (500), and the other end of the long spring (610) is fixedly connected to the bottom of the electrode disk (400); The ball screw guide mechanism (200) drives the electrode fixture (500) to move at a speed that is equal to the maximum predicted burning rate of the electrically controlled solid propellant (900) to be tested.

2. The device for dynamically measuring the burning rate of electronically controlled solid propellant using the target line method according to claim 1, characterized in that: The elastic coefficients of the short spring (600) and the long spring (610) are both k, where ΔF=2kNΔx Δx=(v1-v2)·t In the formula, ΔF represents the total weight of the output electrode (300) and the electrode disk (400), v1 represents the moving speed of the ignition electrode module, v2 represents the minimum predicted burning rate of the electronically controlled solid propellant (900) to be tested, Δx represents the maximum relative displacement between the output electrode (300) and the burning surface of the electronically controlled solid propellant (900) to be tested, t is the maximum predicted burning time of the electronically controlled solid propellant (900) to be tested, and l is the length of the electronically controlled solid propellant (900) to be tested.

3. The device for dynamically measuring the burning rate of electronically controlled solid propellant using the target line method according to claim 2, characterized in that: The deformation length of the long spring (610) is greater than the maximum relative displacement between the output electrode (300) and the combustion surface of the electrically controlled solid propellant (900) to be tested.

4. The device for dynamically measuring the burning rate of electronically controlled solid propellant using the target line method according to claim 3, characterized in that: The base (100) is provided with a through hole and at least three target line terminals (800); The through hole is coaxially arranged with the electrode disk (400) and is used for installing the electronically controlled solid propellant (900) to be tested when performing a burning rate test; The target line terminal (800) is fixedly connected to the top of the base (100).

5. The device for dynamically measuring the burning rate of electronically controlled solid propellant using the target line method according to claim 4, characterized in that: The data acquisition module (700) comprises two target lines, a voltage divider module, an acquisition board and a computer; Each target wire is used to pass through the electronically controlled solid propellant (900) to be tested and then be connected to two target wire terminals (800), the two target wire terminals (800) serving as a positive electrode and a negative electrode respectively; The voltage divider module is used to reduce the voltage signal collected on the target line, and the voltage divider module is provided with two resistors, each resistor is connected to two target line terminals (800) with different electrodes; The acquisition board is used to acquire the voltage signal after the voltage is stepped down by the voltage divider module at a sampling frequency of 20000 Hz and store the signal in the computer.

6. The device for dynamically measuring the burning rate of electronically controlled solid propellant using the target line method according to claim 5, characterized in that: The two electrode fixtures (500) are respectively fixedly connected to the slides of the two ball screw guide mechanisms (200), and the slides of the two ball screw guide mechanisms (200) are synchronized and have the same speed.

7. The device for dynamically measuring the burning rate of electronically controlled solid propellant using the target line method according to claim 6, characterized in that: The long spring (610) or the short spring (600) is threadedly connected to the electrode disk (400).

8. The device for dynamically measuring the burning rate of electronically controlled solid propellant using the target line method according to claim 7, characterized in that: The target line is connected to an external 24V voltage-stabilized power supply through a wire.

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