A magnetically powered electrically controlled solid propellant combustion performance testing system and method

Abstract

The present invention is a magnetically powered electrically controlled solid propellant combustion performance test system and method. It includes a support frame, an ignition device, a magnetic sheet, an electromagnet, a PD stress control integrated module, a data acquisition subsystem and a PC terminal; a magnetic sheet is connected below the ignition device, and a PD stress control integrated module is arranged below the ignition device, and an electromagnet is arranged thereon. The PD stress control integrated module regulates the current to make the force between the ignition device and the electromagnet constant, thereby pushing the ignition device electrically controlled solid propellant to slide and maintaining dynamic contact between the propellant and the positive and negative electrodes. The present invention is suitable for testing electrically controlled solid propellants of various systems. The parameters of the entire area of ​​the system can be modulated by the PC terminal, and the combustion performance of the electrically controlled solid propellant, such as multi-stage ignition delay time, energy required for ignition, dynamic burning rate, dynamic current, burning rate adjustable ability with electricity, combustion temperature, flame structure morphology and flameout delay time, can be diagnosed simultaneously.

Description

Technical Field

[0001] The invention belongs to the technical field of solid propellant performance testing, and in particular relates to a magnetically powered electrically controlled solid propellant combustion performance testing system and method. Background Art

[0002] Solid propellants have always served the satellite attitude and orbit control systems and tactical missile propulsion systems of high-thrust solutions, but with the diversification of space missions and the complexity of battlefield environments, randomly controlled propulsion systems are obviously very attractive. Electronically controlled solid propellants solve this problem from the source. They achieve active and controllable combustion of propellants through applied voltage, making them a research hotspot in the field of solid propulsion.

[0003] The study of combustion performance is an important foundation for the mature application and theoretical construction of solid propellants. However, unlike traditional solid propellants, electronically controlled solid propellants require external physical fields (including electric fields and force fields) to ensure the continuous input of electrical energy during the test process, which greatly increases the difficulty of testing. On the other hand, electronically controlled solid propellants require more performance parameters to be tested than traditional solid propellants. At present, there is still a lack of scientific and reliable means to test the multi-element combustion performance of electronically controlled solid propellants.

[0004] The existing technical solutions adopt a fixed voltage method, relying on compression springs or electrode suspension to push the propellant into contact with the electrode. This mechanical force may vary with distance or cannot be adjusted, and there is a problem of coil drag, which greatly affects the consistency of the experiment and is not suitable for testing larger grains. The specific test process requires manual operation of electrical equipment, which poses a great safety hazard.

[0005] At present, the combustion test of electronically controlled solid propellant is mainly based on the traditional solid propellant test scheme. The established test device has a simple structure and a single test index. The research is mainly centered on the burning rate, and it is impossible to further study the ignition, flameout, electrical performance, combustion state and secondary combustion. In addition, the test process is mainly static testing, and the average burning rate is used instead of the actual burning rate. However, for electronically controlled solid propellants that can adjust the burning rate in real time with electricity, the static test method obviously can no longer meet its testing needs. Summary of the invention

[0006] The purpose of the present invention is to solve the problem of multi-element combustion performance testing of electronically controlled solid propellants, and to provide a magnetically powered electronically controlled solid propellant combustion performance testing device and system, which can simultaneously diagnose the combustion performance of electronically controlled solid propellants, such as multi-stage ignition delay time, ignition energy required, dynamic burning rate, dynamic current, burning rate adjustable capability with electricity, combustion temperature, flame structure morphology and flameout delay time.

[0007] The technical solution to achieve the purpose of the present invention is: a magnetically powered electrically controlled solid propellant combustion performance test system, including an optical platform, a Z-axis movable ignition device support frame, an open hole horizontal support frame, an inner hole through-through "sandwich" configuration ignition device, a magnetic sheet, an electromagnet, a PD stress control integrated module, a data acquisition subsystem for collecting signals during the process, and a PC terminal;

[0008] The inner hole penetrates the "sandwich" configuration ignition device and is set on the Z-axis movable ignition device support frame through the open hole horizontal support frame. The magnetic sheet is connected below the ignition device. The PD stress control integrated module is set below the ignition device and an electromagnet is set on it. The PD stress control integrated module controls the current to make the force between the ignition device and the electromagnet constant, thereby pushing the electronically controlled solid propellant of the ignition device to slide and maintaining dynamic contact between the propellant and the positive and negative electrodes.

[0009] Furthermore, it also includes a Z-axis macro adjustment base, the Z-axis macro adjustment base is arranged on the optical platform, and the PD stress control integrated module is arranged on the Z-axis macro adjustment base;

[0010] The hole horizontal support frame is movably arranged on the Z-axis movable ignition device support frame through a slider;

[0011] By adjusting the position of the hole horizontal support frame on the Z-axis movable ignition device support frame, the distance between the ignition device and the electromagnet can be roughly adjusted;

[0012] The Z-axis macro adjustment base can be used to fine-tune the distance between the ignition device and the electromagnet to change the initial magnetic force.

[0013] Furthermore, the inner hole penetrates the "sandwich" configuration ignition device, including a positive electrode clamping plate, an insulating gasket positive electrode grid inserted in the positive electrode clamping plate, a negative electrode plate, an electromagnetic isolation rod and a magnetic sheet connected as one, the negative electrode plate and the electromagnetic isolation rod are connected by an insulating screw, and a solid propellant is placed between the negative electrode plate and the positive electrode grid, and the magnetic force is used to push the electronically controlled solid propellant to slide in the negative electrode track of the bearing, so as to maintain dynamic contact between the propellant and the positive and negative electrodes;

[0014] The two insulating gaskets are respectively located between the positive clamping plate, the negative rail of the bearing, the negative rail of the bearing, and the open hole horizontal support frame.

[0015] Furthermore, the materials of the positive electrode clamping plate, the negative electrode rail of the bearing, the positive electrode grid, and the negative electrode plate are one or two of 304 material and 316 material;

[0016] The insulating gasket is made of one or both of ceramic and PTFE materials;

[0017] The material of the electromagnetic isolation rod is PTFE.

[0018] Furthermore, the data acquisition subsystem includes a laser displacement sensor, a photoelectric sensor, a current probe, a voltage probe, an infrared camera, and a high-speed camera;

[0019] The laser displacement sensor is placed under the magnetic sheet to measure the real-time displacement distance of the magnetic sheet in real time; the photoelectric sensor is horizontally aligned with the upper port of the ignition device to measure the flame intensity when the propellant is burning in real time; the current probe and the voltage probe are placed on the optical platform, and the test line passes through the current probe. When current passes through the test line, the current probe measures the dynamic current in real time, and the positive and negative contacts of the voltage probe are respectively connected to the test line nodes A and B. The two nodes are respectively located on the front and rear test lines at the positive and negative ends of the ignition device. When there is a potential difference between the two nodes, the voltage probe measures the voltage at both ends of the ignition device; the infrared camera and the high-speed camera are horizontally aligned with the upper port of the ignition device to record the infrared image and the combustion flame image during the combustion process.

[0020] Further, an oscilloscope is included;

[0021] The data from the laser displacement sensor, photoelectric sensor, current probe and voltage probe are collected and transmitted to the oscilloscope in real time at a rate of >10kHz;

[0022] The infrared camera and high-speed camera images are transmitted to the PC in real time at a frame rate of >1000fps;

[0023] The oscilloscope and PC are triggered synchronously.

[0024] Furthermore, it also includes a programmable power supply A and a programmable power supply B;

[0025] The negative rail of the bearing is connected to the negative terminal of the programmable power supply A through node B, and the positive clamping plate is connected to the positive terminal of the programmable power supply A through node A;

[0026] The programmable power supply B supplies power to the PD stress control integrated module through the current transmission line.

[0027] Furthermore, it also includes a time delay relay module for controlling opening and closing of the loop.

[0028] Furthermore, the parameter modulation of the programmable power supply A, the programmable power supply B and the delay relay module is controlled via the PC terminal;

[0029] The fixed stress value changes with the composition of the electronically controlled solid propellant formula and is set by the PC to the integrated module through a signal transmission line.

[0030] A method for calculating the combustion performance of a magnetically powered electrically controlled solid propellant using the above system, including a method for calculating the multi-stage ignition delay time, the energy required for ignition, the dynamic burning rate, the dynamic current, the ability of the burning rate to be electrically adjustable, the combustion temperature, the flame structure and the flameout delay time of the electrically controlled solid propellant;

[0031] (1) Electronically controlled solid propellant ignition delay time

[0032] Electronically controlled solid propellant ignition delay time t i,n :

[0033] t i,n =t 1,n -t 0,n (n=1,2,…)

[0034] Among them, t 0,n and t 1,n They are the moment when the voltage is applied across the propellant and the moment when the photoelectric sensor collects the propellant flame signal, and n represents the ignition level.

[0035] (2) Energy required for electronically controlled solid propellant ignition

[0036] Energy required for electronically controlled solid propellant ignition Q i,n :

[0037]

[0038] Among them, U and I are the voltage and dynamic current of the propellant during electronically controlled combustion, and n represents the ignition level.

[0039] (3) Electronically controlled solid propellant dynamic burning rate

[0040] The burned thickness of the electronically controlled solid propellant grain is equal to the moving distance of the negative plate-electromagnetic isolation rod-magnetic sheet. The dynamic burning rate is (r n ) t :

[0041]

[0042] Among them, Δt is any short period of movement time of the negative plate-electromagnetic isolation rod-magnetic sheet; Δd is the movement distance of the negative plate-electromagnetic isolation rod-magnetic sheet within Δt time, and n represents the ignition level.

[0043] (4) Electronically controlled solid propellant dynamic current

[0044] The current change during the combustion of electronically controlled solid propellant can be obtained from the current change curve recorded by the oscilloscope.

[0045] (5) Electrically adjustable burning rate of electronically controlled solid propellant

[0046] Electrically adjustable burning rate of electronically controlled solid propellant (A r,n ) U :

[0047]

[0048] Among them, ΔU is the voltage change of any small section at both ends of the electronically controlled solid propellant; Δr is the change of the burning rate of the electronically controlled solid propellant within the range of ΔU, and n represents the ignition level.

[0049] (6) Electronically controlled solid propellant combustion temperature

[0050] The combustion temperatures of different regions of the electronically controlled solid propellant flame can be obtained from the calibrated infrared images.

[0051] (7) Electronically controlled solid propellant flame morphology

[0052] The flame morphology of electronically controlled solid propellant can be obtained from high-speed images.

[0053] (8) Electronically controlled solid propellant flameout delay time

[0054] Electronically controlled solid propellant flameout delay time t e,n :

[0055] t e,n =t 3,n -t 2,n (n=1,2,…)

[0056] Among them, t 2,n and t 3,n are the moment when the voltage is removed from both ends of the propellant and the moment when the flame at the positive end disappears, and n represents the ignition order.

[0057] Compared with the prior art, the present invention has the following significant advantages:

[0058] (1) The magnetically powered electrically controlled solid propellant combustion performance test device of the present invention realizes constant stress of electrodes at both ends during the combustion of the propellant by controlling the PD of the electromagnetic force. It is applicable to electrically controlled solid propellants of different systems and can test larger propellant grains. It overcomes the inherent disadvantage of the original technology that the stress cannot be kept constant and the experimental consistency is not strong.

[0059] (2) The "sandwich" configuration ignition device in the magnetic power electric control solid propellant combustion performance test device of the present invention has electrodes located inside, without dragging coils, which ensures that the electrodes are stable and do not drift. The positive electrode grid helps release flames and gas, and does not produce adverse electrode ablation and reaction forces. All components can be quickly mass-produced by 3D printing, and are compact and easy to replace.

[0060] (3) The magnetically powered electrically controlled solid propellant combustion performance test system of the present invention adopts a relay control method to realize ignition and flameout, thereby improving the combustion control accuracy and system safety.

[0061] (4) The magnetically powered electrically controlled solid propellant combustion performance test system of the present invention can simultaneously diagnose the combustion performance of the electrically controlled solid propellant, including multi-stage ignition delay time, ignition energy required, dynamic burning rate, dynamic current, burning rate adjustable capability with electricity, combustion temperature, flame structure morphology and flameout delay time.

[0062] (5) The parameters of the entire area of ​​the magnetically powered electrically controlled solid propellant combustion performance test system of the present invention can be modulated by the PC, which has an excellent human-computer exchange function, simplifies the operation during the experiment, and can greatly improve the experimental efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0063] Figure 1 It is a stereoscopic diagram of the overall structure of the electronically controlled combustion testing device of the present invention.

[0064] Figure 2 It is a three-dimensional diagram of the disassembly and assembly of the "sandwich" configuration ignition device of the electronically controlled combustion test device of the present invention.

[0065] Figure 3 The diagram is a front view and a side view of a positive electrode clamp and a grid of an electric-controlled combustion test device of the present invention.

[0066] Figure 4 It is a schematic diagram of the electromagnet and PD stress control integrated module of the electronically controlled combustion test device of the present invention.

[0067] Figure 5 It is a three-dimensional schematic diagram of the overall structure of the electronically controlled combustion test system of the present invention.

[0068] Figure 6 It is a typical oscilloscope signal diagram in a specific embodiment of the present invention.

[0069] Figure 7 It is a typical infrared temperature diagram in a specific embodiment of the present invention.

[0070] Figure 8 It is a typical high-speed flame morphology diagram in a specific embodiment of the present invention.

[0071] Description of reference numerals:

[0072] 1-Z-axis movable ignition device support frame, 2-opening horizontal support frame, 3-"sandwich" configuration ignition device, 4-magnetic sheet, 5-electromagnet, 6-PD stress control integrated module, 7-Z-axis macro adjustment base, 8-laser displacement sensor, 9-photoelectric sensor, 10-current probe, 11-voltage probe, 12-infrared camera, 13-high-speed camera, 14-optical platform, 15-positive clamping plate, 16-insulating gasket, 17-bearing negative rail, 18-positive grid, 19-negative plate, 20-electromagnetic isolation rod, 21-current transmission line, 22-signal transmission line, 23-1-test node A, 23-2-test line node B, 24-1-programmable power supply A, 24-2-programmable power supply B, 25-delay relay switch module, 26-oscilloscope, 27-PC terminal. DETAILED DESCRIPTION

[0073] The present invention is further described in detail below in conjunction with the accompanying drawings.

[0074] like Figure 1-8 As shown, the present invention relates to a magnetically powered electrically controlled solid propellant combustion performance test device, comprising: a Z-axis movable ignition device support frame 1, a side wing slider of the support frame 1 is connected to an open hole horizontal support frame 2 through a 12.9-level screw, the inner hole of the horizontal support frame 2 passes through a "sandwich" configuration ignition device 3, a magnetic sheet 4 is connected below the ignition device 3 through a 316 screw, and a Z-axis micro-pitch adjustment base 7 is arranged directly below the ignition device; a PD stress control integrated module 6 is connected above the base 7 through a 316 screw, a current transmission line 21 and a signal transmission line 22 are above the integrated module 6, and an electromagnet 5 is arranged directly above the integrated module 6, the electromagnet 5 is powered by the integrated module 6, and the response frequency is greater than 10kHz; by adjusting the magnetic sheet 4 and the electromagnet 5 The distance between the magnetic sheet 4 and the electromagnet 5 changes the initial magnetic force. The distance between the magnetic sheet 4 and the electromagnet 5 can be roughly adjusted by the side slider of the sliding support frame 1, and the slider stroke is 260mm. The distance between the magnetic sheet 4 and the electromagnet 5 can be fine-tuned by the Z-axis macro adjustment base 7, and the longitudinal stroke of the base is 10mm; the laser displacement sensor 8 is placed under the magnetic sheet 4 to measure the real-time displacement distance of the magnetic sheet 4 in real time. The photoelectric sensor 9 is horizontally aligned with the upper port of the ignition device 3 to measure the flame intensity when the propellant is burning in real time. The current probe 10 and the voltage probe 11 are placed on the optical platform 14. The test line passes through the current probe 10. When current passes through the test line, the current probe 10 measures the dynamic current in real time. The positive and negative contacts of the voltage probe 11 are respectively connected to the test line node A A 23-1 and B 23-2 are connected, and the two nodes are respectively located on the front and rear test lines at the positive and negative ends of the ignition device 3. When there is a potential difference between the two nodes, the voltage probe 11 measures the voltage at both ends of the ignition device; the infrared camera 12 and the high-speed camera 13 are horizontally aligned with the upper port of the ignition device 3 to record the infrared image and the combustion flame image during the combustion process.

[0075] Furthermore, the ignition device 3 includes: a positive electrode clamp 15, an insulating gasket 16, a bearing negative electrode track 17 with an inner diameter of 20 mm, a positive electrode grid 18, a negative electrode plate 19 with a diameter of 20 mm, and an electromagnetic isolation rod 20 with a diameter of 20 mm; the positive electrode grid 18 is inserted into the internal groove of the positive electrode clamp 15 to facilitate the replacement of the grid, and there is a ceramic insulating gasket 16 between the bearing negative electrode track 17 and the clamp 15 and the open hole horizontal support frame 2 to ensure insulation between the positive and negative electrodes, the ignition device and the electronically controlled combustion system; the negative electrode plate 19 is connected to the electromagnetic isolation rod 20 through a nylon screw, the negative electrode plate 19, the isolation rod 20 and the magnetic sheet 4 are connected as a whole, and the positive electrode grid, the electronically controlled solid propellant and the negative electrode plate are in a "sandwich" structure; the bearing negative electrode track 17 is a linear ball bearing, and the negative electrode plate 19 is fitted with the linear ball, and the magnetic force acts on the negative electrode track of the bearing to push the electronically controlled solid propellant on the negative electrode plate to slide, thereby maintaining dynamic contact between the propellant and the positive and negative electrodes.

[0076] The invention relates to a magnetic power electrically controlled solid propellant combustion performance test system, comprising: a programmable power supply, a time delay relay switch module, the above-mentioned electrically controlled combustion test device, an oscilloscope, and a PC terminal.

[0077] The positive and negative electrodes of the programmable power supply A 24-1 are respectively connected to the positive electrode clamping plate 15 and the negative electrode track 17 of the bearing in the electric control combustion test device through the test line, the delay relay module 25 is used to control the open circuit and the closed circuit in the loop, and the parameter modulation of the programmable power supply A24-1, the programmable power supply B 24-2 and the delay relay module 25 is controlled by the PC terminal 27; the programmable power supply B supplies power to the PD stress control integrated module 6 through the current transmission line 21, and the PC terminal 27 sets a fixed stress value for the integrated module 6 through the signal transmission line 22; the signals of the laser displacement sensor 8, the photoelectric sensor 9, the current probe 10 and the voltage probe 11 in the electric control combustion test device are transmitted to the oscilloscope 26 in real time, the acquisition frequency of the oscilloscope 26 is greater than 10kHz, and the rising edge is less than 500ps. The infrared image and high-speed image of the infrared camera 12 and the high-speed camera 13 in the electric control combustion test device are transmitted to the PC terminal 27 at a frame rate of greater than 1000fps; the oscilloscope 26 and the PC terminal 27 are synchronously triggered and recorded.

[0078] The present invention adopts 3D printing technology to manufacture the required parts and accessories.

[0079] The present invention relates to a method for calculating the combustion performance of a magnetically powered electrically controlled solid propellant:

[0080] (1) Electronically controlled solid propellant ignition delay time

[0081] Electronically controlled solid propellant ignition delay time t i,n :

[0082] t i,n =t1,n -t 0,n (n=1,2,…)

[0083] Among them, t 0,n and t 1,n They are the moment when the voltage is applied across the propellant and the moment when the photoelectric sensor collects the propellant flame signal, and n represents the ignition level.

[0084] (2) Energy required for electronically controlled solid propellant ignition

[0085] Energy required for electronically controlled solid propellant ignition Q i,n :

[0086]

[0087] Among them, U and I are the voltage and dynamic current of the propellant during electronically controlled combustion, and n represents the ignition level.

[0088] (3) Electronically controlled solid propellant dynamic burning rate

[0089] The burned thickness of the electronically controlled solid propellant grain is equal to the moving distance of the negative plate-electromagnetic isolation rod-magnetic sheet. The dynamic burning rate is (r n ) t :

[0090]

[0091] Among them, Δt is any short period of movement time of the negative plate-electromagnetic isolation rod-magnetic sheet; Δd is the movement distance of the negative plate-electromagnetic isolation rod-magnetic sheet within Δt time, and n represents the ignition level.

[0092] (4) Electronically controlled solid propellant dynamic current

[0093] The current change during the combustion of electronically controlled solid propellant can be obtained from the current change curve recorded by the oscilloscope.

[0094] (5) Electrically adjustable burning rate of electronically controlled solid propellant

[0095] Electrically adjustable burning rate of electronically controlled solid propellant (A r,n ) U :

[0096]

[0097] Among them, ΔU is the voltage change of any small section at both ends of the electronically controlled solid propellant; Δr is the change of the burning rate of the electronically controlled solid propellant within the range of ΔU, and n represents the ignition level.

[0098] (6) Electronically controlled solid propellant combustion temperature

[0099] The combustion temperatures of different regions of the electronically controlled solid propellant flame can be obtained from the calibrated infrared images.

[0100] (7) Electronically controlled solid propellant flame morphology

[0101] The flame morphology of electronically controlled solid propellant can be obtained from high-speed images.

[0102] (8) Electronically controlled solid propellant flameout delay time

[0103] Electronically controlled solid propellant flameout delay time t e,n :

[0104] t e,n =t 3,n -t 2,n (n=1,2,…)

[0105] Among them, t 2,n and t 3,n are the moment when the voltage is removed from both ends of the propellant and the moment when the flame at the positive end disappears, and n represents the ignition order.

Claims

1. A magnetically powered electrically controlled solid propellant combustion performance test system, characterized in that: It comprises an optical platform (14), a Z-axis movable ignition device support frame (1), an open hole horizontal support frame (2), an inner hole penetrating a "sandwich" configuration ignition device (3), a magnetic sheet (4), an electromagnet (5), a PD stress control integrated module (6), a data acquisition subsystem for acquiring signals during the process, and a PC terminal; The inner hole penetrates the "sandwich" configuration ignition device (3) and is arranged on a Z-axis movable ignition device support frame (1) through an open hole horizontal support frame (2); a magnetic sheet (4) is connected below the ignition device (3); a PD stress control integrated module (6) is arranged below the ignition device (3) and an electromagnet (5) is arranged thereon; the PD stress control integrated module (6) controls the current so that the force between the ignition device (3) and the electromagnet (5) remains constant, thereby pushing the electric control solid propellant of the ignition device (3) to slide and maintaining dynamic contact between the propellant and the positive and negative electrodes; The inner hole penetrating "sandwich" configuration ignition device (3) comprises a positive electrode clamping plate (15), an insulating gasket (16), a bearing negative electrode track (17), a positive electrode grid (18), a negative electrode plate (19) and an electromagnetic isolation rod (20); The positive electrode grid (18) is inserted into the positive electrode clamping plate (15), the negative electrode plate (19), the electromagnetic isolation rod (20) and the magnetic sheet (4) are connected as one, the negative electrode plate (19) and the electromagnetic isolation rod (20) are connected by an insulating screw, and the solid propellant is placed between the negative electrode plate (19) and the positive electrode grid (18). The magnetic force acts on the negative electrode track (17) of the bearing to push the electrically controlled solid propellant to slide, thereby maintaining dynamic contact between the propellant and the positive and negative electrodes; The two insulating gaskets (16) are respectively located between the positive electrode clamping plate (15), the bearing negative electrode rail (17), the bearing negative electrode rail (17), and the open hole horizontal support frame (2).

2. The system according to claim 1, characterized in that It also includes a Z-axis macro adjustment base (7), the Z-axis macro adjustment base (7) is arranged on the optical platform (14), and the PD stress control integrated module (6) is arranged on the Z-axis macro adjustment base (7); The open hole horizontal support frame (2) is movably arranged on the Z-axis movable ignition device support frame (1) via a slider; By adjusting the position of the open hole horizontal support frame (2) on the Z-axis movable ignition device support frame (1), the distance between the ignition device (3) and the electromagnet (5) can be roughly adjusted; The distance between the ignition device (3) and the electromagnet (5) can be finely adjusted through the Z-axis micro-adjustment base (7) to change the initial magnetic force.

3. The system according to claim 2, characterized in that The materials of the positive electrode clamping plate (15), the bearing negative electrode track (17), the positive electrode grid (18), and the negative electrode plate (19) are one or two of 304 material and 316 material; The material of the insulating gasket (16) is one or both of a ceramic material and a PTFE material; The electromagnetic isolation rod (20) is made of PTFE material.

4. The system according to claim 3, characterized in that The data acquisition subsystem includes a laser displacement sensor (8), a photoelectric sensor (9), a current probe (10), a voltage probe (11), an infrared camera (12) and a high-speed camera (13); The laser displacement sensor (8) is placed below the magnetic sheet (4) to measure the real-time displacement distance of the magnetic sheet (4) in real time; the photoelectric sensor (9) is horizontally aligned with the upper port of the ignition device (3) to measure the flame light intensity when the propellant is burning in real time; the current probe (10) and the voltage probe (11) are placed on the optical platform (14), the test line passes through the current probe (10), when current passes through the test line, the current probe (10) measures the dynamic current in real time, the positive and negative contacts of the voltage probe (11) are respectively connected to the test line nodes A and B, the two nodes are respectively located on the front and rear test lines at the positive and negative ends of the ignition device (3), when there is a potential difference between the two nodes, the voltage probe (11) measures the voltage at the two ends of the ignition device; the infrared camera (12) and the high-speed camera (13) are horizontally aligned with the upper port of the ignition device (3) to record the infrared image and the combustion flame image during the combustion process.

5. The system according to claim 4, characterized in that Also included is an oscilloscope (26); The data of the laser displacement sensor (8), the photoelectric sensor (9), the current probe (10) and the voltage probe (11) are transmitted and collected in real time at a rate of >10 kHz to an oscilloscope (26); The images of the infrared camera (12) and the high-speed camera (13) are transmitted to the PC (27) in real time at a frame rate of >1000fps; The oscilloscope (26) and the PC terminal (27) are triggered synchronously.

6. The system according to claim 5, characterized in that Also includes a programmable power supply A (24-1) and a programmable power supply B (24-2); The negative rail of the bearing is connected to the negative terminal of the programmable power supply A (24-1) via a node B (23-2), and the positive clamping plate (15) is connected to the positive terminal of the programmable power supply A (24-1) via a node A (23-1); The programmable power source B (24-2) supplies power to the PD stress control integrated module (6) through the current transmission line (21).

7. The system according to claim 6, characterized in that It also includes a time delay relay module (25) for controlling opening and closing of the loop.

8. The system according to claim 7, characterized in that The parameter modulation of the programmable power supply A (24-1), the programmable power supply B (24-2) and the delay relay module (25) is controlled via the PC terminal (27); The fixed stress value changes with the composition of the electronically controlled solid propellant formula and is set by the PC terminal (27) to the integrated module (6) through the signal transmission line (22).

9. A method for calculating the combustion performance test of a magnetically powered electrically controlled solid propellant based on the magnetically powered electrically controlled solid propellant combustion performance test system according to any one of claims 1 to 8, characterized in that: Including calculation methods for multi-stage ignition delay time of electronically controlled solid propellant, ignition energy required, dynamic burning rate, dynamic current, burning rate adjustable capability with electricity, combustion temperature, flame structure morphology and flameout delay time; (1) Electronically controlled solid propellant ignition delay time Electronically controlled solid propellant ignition delay time t i,n : t i,n =t 1,n -t 0,n (n=1,2,…) Among them, t 0,n and t 1,n They are the moments when the voltage is applied across the propellant and the moment when the photoelectric sensor collects the propellant flame signal, and n represents the ignition level; (2) Energy required for electronically controlled solid propellant ignition Energy required for electronically controlled solid propellant ignition Q i,n : Among them, U and I are the voltage and dynamic current of the propellant during electronically controlled combustion, respectively, and n represents the ignition level; (3) Electronically controlled solid propellant dynamic burning rate The burned thickness of the electronically controlled solid propellant grain is equal to the moving distance of the negative plate-electromagnetic isolation rod-magnetic sheet. The dynamic burning rate is (r n ) t : Among them, Δt is any short period of movement time of the negative plate-electromagnetic isolation rod-magnetic sheet; Δd is the movement distance of the negative plate-electromagnetic isolation rod-magnetic sheet within Δt time, and n represents the ignition level; (4) Electronically controlled solid propellant dynamic current The current change during the combustion of electronically controlled solid propellant can be obtained from the current change curve recorded by the oscilloscope; (5) Electrically adjustable burning rate of electronically controlled solid propellant Electrically adjustable burning rate of electronically controlled solid propellant (A r,n ) U : Among them, ΔU is the voltage change of any small section at both ends of the electronically controlled solid propellant; Δr is the change of the burning rate of the electronically controlled solid propellant within the range of ΔU, and n represents the ignition level; (6) Electronically controlled solid propellant combustion temperature The combustion temperatures of different regions of the electronically controlled solid propellant flame can be obtained from the calibrated infrared images; (7) Electronically controlled solid propellant flame morphology The flame morphology of electronically controlled solid propellant can be obtained from high-speed images; (8) Electronically controlled solid propellant flameout delay time Electronically controlled solid propellant flameout delay time t e,n : t e,n =t 3,n -t 2,n (n=1,2,…) Among them, t 2,n and t 3,n are the moment when the voltage is removed from both ends of the propellant and the moment when the flame at the positive end disappears, and n represents the ignition order.

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