Impulse type electromagnetic thruster performance detection system and analysis method

Abstract

The invention discloses a pulse type electromagnetic thruster performance detection system and an analysis method. A direct-current power supply, an ignition trigger controller, a pulse current detector, a pulse high-voltage detector, a discharge waveform collector, a pulse type electromagnetic thruster, a polar plate inductance intensity measuring device, a thruster impulse measuring device and a plasma movement speed measuring device are adopted. The polar plate inductance intensity measuring device is used for measuring the inductance gradient of a polar plate discharge channel of the pulse type electromagnetic thruster under different polar plate configurations; the thruster impulse measuring device is positioned below the pulse type electromagnetic thruster and is used for acquiring an output impulse value of the thruster when the pulse type electromagnetic thruster discharges and works; the plasma motion speed measuring device is arranged at the front end of a nozzle of the pulse type electromagnetic thruster and used for measuring the motion speed of plasma plume jetted by the pulse type electromagnetic thruster. According to the invention, measurement of macroscopic performance parameters of the pulse type electromagnetic thruster is realized, and quantitative characterization of microscopic characteristics of the thruster can be realized at the same time.

Description

Technical Field

[0001] The invention relates to the field of aerospace technology, and in particular discloses a pulse electromagnetic thruster performance detection system and analysis method. Background Art

[0002] With the rapid advancement of satellite constellation technology, the demand for electric propulsion technology continues to rise, especially in the field of microsatellites. Pulsed electromagnetic thrusters, due to their excellent performance, not only support the formation flight of constellation satellites, but also provide the satellites with the necessary attitude adjustment, orbit maintenance and transfer power, effectively extending the operating life of satellites in low Earth orbit.

[0003] Although pulsed electromagnetic thrusters are favored for their advantages such as simple structure, high specific impulse and low energy consumption, their insufficient working fluid utilization efficiency and system energy efficiency have become the main obstacles to improving performance and realizing space applications. Studies have shown that about 40% to 90% of the ablated working fluid products in the thruster fail to be effectively ionized, resulting in the inability to be fully accelerated by the electromagnetic field. These insufficiently accelerated materials are discharged under the action of gas power, and the thrust generated is weak, which significantly reduces the utilization efficiency of the working fluid. In addition, the system energy loss is large and the efficiency is less than 10%. Therefore, improving the working fluid utilization efficiency and system efficiency, as well as in-depth exploration of its influencing mechanism, are issues that current researchers urgently need to solve.

[0004] In order to meet these challenges, researchers at home and abroad have used numerical simulation and experimental testing to deeply analyze the impact of thruster parameter changes on performance in order to determine the optimal system parameter configuration. These studies aim to optimize thruster design, improve fluid efficiency, extend service life, and enhance the overall performance of the system. In the experiment, the researchers explored the thruster working mechanism under different system parameter configurations, deeply understood the ablation, ionization and acceleration process of the working fluid, and revealed the key factors affecting system performance. These studies help to increase the proportion of ablated working fluid in electromagnetic acceleration and improve the effective utilization efficiency of the initial energy of the thruster, thereby enhancing the key mechanical properties of the thruster such as impulse, specific impulse and system efficiency.

[0005] In addition, researchers also used electromechanical models and semi-empirical formulas to evaluate the impact of changes in electrical and structural parameters on thruster performance through simulation calculations. However, due to the fixed nature of simulation parameter settings, the actual working state of the thruster cannot be fully reflected. Therefore, these studies are still semi-quantitative and have certain limitations in understanding the mechanism and law of the impact of a single parameter change on thruster performance.

[0006] It is worth noting that the pulsed electromagnetic thruster has a short discharge time of microseconds and involves complex physical mechanisms such as light, electricity, magnetism, and heat. Therefore, there is a complex interaction between the electrical parameters and structural parameters of the system. Changes in a single system parameter will not only affect the microscopic characteristics of the discharge plasma, but also have a significant impact on the discharge characteristics of the system and the macroscopic dynamic performance of the thruster. However, the existing experimental measurement equipment and methods can only quantitatively measure certain macroscopic electrical parameters and mechanical parameters, but cannot obtain the microscopic characteristics of the system discharge circuit, such as equivalent resistance, inductance, discharge energy transfer efficiency, the proportion of Lorentz force accelerated ablation materials, and the proportion of aerodynamic force accelerated ablation materials. It is even more impossible to deeply analyze the internal interactions of the effects of parameter changes on the system discharge characteristics, energy transfer characteristics, and system performance. Therefore, it is difficult for researchers to fully understand and grasp the working process and deep working mechanism of the thruster. Summary of the invention

[0007] The present invention provides a pulse electromagnetic thruster performance detection system and analysis method, aiming to solve at least one defect existing in the above-mentioned prior art.

[0008] One aspect of the present invention relates to a pulse electromagnetic thruster performance detection system, comprising a DC power supply, an ignition trigger controller, a pulse current detector, a pulse high voltage detector, a discharge waveform collector, a pulse electromagnetic thruster, a plate inductance intensity measuring device, a thruster impulse measuring device and a plasma motion speed measuring device, wherein: A direct current power supply is electrically connected to the pulse electromagnetic thruster and is used to charge the pulse electromagnetic thruster; A pulse current detector is placed around the pulse electromagnetic thruster discharge loop transmission line and is used to detect the pulse current amplitude data of the discharge loop of the pulse electromagnetic thruster; A pulse high voltage detector is loaded on the pulse electromagnetic thruster and is used to detect the discharge circuit voltage waveform data of the pulse electromagnetic thruster; The discharge waveform collector is connected to the ignition trigger controller, the pulse current detector and the pulse high voltage detector respectively, and is used to collect the discharge circuit pulse current amplitude data detected by the pulse current detector and the discharge circuit voltage waveform data detected by the pulse high voltage detector according to the collection trigger signal provided by the ignition trigger controller; Pulse electromagnetic thruster, installed on the thruster impulse measuring device; The plate inductance intensity measuring device is arranged close to the pulse electromagnetic thruster and is used to measure the inductance gradient of the plate discharge channel of the pulse electromagnetic thruster under different plate configurations; The thruster impulse measuring device is located below the pulse electromagnetic thruster and is used to obtain the thruster output impulse value when the pulse electromagnetic thruster is discharging; The plasma motion velocity measuring device is arranged at the front end of the pulse electromagnetic thruster nozzle and is used to measure the motion velocity of the plasma plume ejected by the pulse electromagnetic thruster.

[0009] Furthermore, the pulse current detector is a Rogowski coil or a current transformer.

[0010] Furthermore, the pulse high voltage detector is a high voltage probe or a capacitive voltage divider.

[0011] Furthermore, the pulsed electromagnetic thruster is a pulsed plasma thruster, a laser electromagnetic induced plasma thruster or a magnetic plasma thruster.

[0012] Furthermore, the plate inductance strength measuring device includes an electric displacement platform, a short-circuited copper bar, a support rod and a copper bar clamp. The support rod is vertically arranged above the electric displacement platform. One end of the copper bar clamp is connected to the support rod, and the other end of the copper bar clamp is used to clamp the short-circuited copper bar.

[0013] Furthermore, the discharge waveform collector is a high-speed oscilloscope or a high-speed data acquisition card.

[0014] Furthermore, the thruster impulse measuring device is a torsion wire type impulse measuring device, a torsion pendulum type impulse measuring device or an inverted pendulum balance type impulse measuring device.

[0015] Furthermore, the plasma movement speed measuring device is a probe array, an ultra-high-speed camera and a narrow-band filter.

[0016] Another aspect of the present invention relates to a pulse electromagnetic thruster performance analysis method, which is applied to the above-mentioned pulse electromagnetic thruster performance detection system. The pulse electromagnetic thruster performance analysis method comprises the following steps: Measuring the inductance gradient of the discharge channel of the pulse electromagnetic thruster: boosting the low-voltage DC power of the DC power supply and supplying it to the energy storage capacitor of the pulse electromagnetic thruster to charge to the rated voltage; using the electric displacement platform to control the short-circuited copper bar to short-circuit the cathode and anode plates of the pulse electromagnetic thruster at the starting position of the thruster discharge channel, the main discharge energy storage capacitor of the pulse electromagnetic thruster is discharged, and a pulse current is generated in the discharge circuit. The pulse current detector detects the pulse current, and the discharge waveform collector collects multiple discharge pulse current amplitude data at the starting position of the thruster discharge channel, and obtains the average value of the current amplitude over time; using the electric displacement platform to control the short-circuited copper bar at different positions X in the discharge channel i Short-circuit and obtain multiple discharge pulse current waveform data at this position; according to the equivalent inductance formula of the LCR discharge circuit, combined with the measured discharge cycle and ignition energy storage capacitance value, obtain the inductance value L at different short-circuit positions. eqxi Data; then according to the different positions X in the discharge channel iAnd the inductance value L at different short-circuit positions eqxi Data, fitting to obtain the discharge channel inductance gradient L'; Obtain the discharge characteristic parameters of the pulsed electromagnetic thruster: the ignition trigger controller controls the discharge of the plasma induction source and induces the main discharge circuit of the pulsed electromagnetic thruster to generate a pulse current. The working fluid of the pulsed electromagnetic thruster is affected by the discharge arc between the cathode and anode plates of the discharge channel, causing ablation and ionization, and is accelerated to be ejected out of the discharge channel; the pulse current detector detects the pulse current waveform data of the discharge circuit, and the high-voltage detector detects the voltage waveform data of the discharge circuit; the impulse generated by the Lorentz force is calculated based on the discharge channel inductance gradient L' obtained by fitting and the pulse current waveform data of the discharge circuit obtained by detection ; Obtain the dynamic performance parameters of the pulsed electromagnetic thruster: Obtain the mass of the working fluid ablated by a single pulse ; Obtain the velocity of the plasma plume ejected by the pulsed electromagnetic thruster measured by the plasma velocity measurement device ; Obtain the pulsed electromagnetic thruster output element impulse I measured by the thruster impulse measuring device bit ; According to the single pulse ablation working fluid quality and the velocity of the plasma plume , and the impulse generated by the Lorentz force is calculated , calculate the ratio of the working fluid accelerated by the Lorentz force and the velocity of the pneumatic accelerator .

[0017] Furthermore, in the step of obtaining the dynamic performance parameters of the pulsed electromagnetic thruster, the impulse value It is expressed as:

[0018] in, is the element impulse value, is the mass of the working fluid for a single pulse ablation, The aerodynamic force accelerates the speed of the working fluid; is the velocity of the plasma plume, is the proportion of the working fluid accelerated by the Lorentz force to ablate.

[0019] The beneficial effects achieved by the present invention are: The present invention provides a pulse electromagnetic thruster performance detection system and analysis method, which adopts a direct current power supply, an ignition trigger controller, a pulse current detector, a pulse high voltage detector, a discharge waveform collector, a pulse electromagnetic thruster, a plate inductance intensity measuring device, a thruster impulse measuring device and a plasma motion speed measuring device, wherein the direct current power supply is electrically connected to the pulse electromagnetic thruster and is used to charge the pulse electromagnetic thruster; the pulse current detector is placed around the pulse electromagnetic thruster discharge loop transmission line and is used to detect the pulse current amplitude data of the pulse electromagnetic thruster discharge loop; the pulse high voltage detector is loaded on the pulse electromagnetic thruster and is used to detect the discharge loop voltage waveform data of the pulse electromagnetic thruster; the discharge waveform collector is respectively connected to the ignition trigger controller, the pulse current detector and the discharge loop voltage waveform data of the pulse electromagnetic thruster. The device is connected to the pulse high voltage detector, and is used to collect the discharge circuit pulse current amplitude data detected by the pulse current detector and the discharge circuit voltage waveform data detected by the pulse high voltage detector according to the collection trigger signal provided by the ignition trigger controller; the pulse electromagnetic thruster is installed on the thruster impulse measurement device; the plate inductance intensity measurement device is arranged close to the pulse electromagnetic thruster, and is used to measure the inductance gradient of the plate discharge channel of the pulse electromagnetic thruster under different plate configurations; the thruster impulse measurement device is located below the pulse electromagnetic thruster, and is used to obtain the thruster output impulse value when the pulse electromagnetic thruster is discharging; the plasma motion speed measurement device is arranged at the front end of the plasma motion speed measurement device, and is used to measure the motion speed of the plasma plume ejected by the pulse electromagnetic thruster. Compared with the prior art, the pulse electromagnetic thruster performance detection system and analysis method provided by the present invention have the following beneficial effects: 1. The present invention provides a pulse electromagnetic thruster working performance detection system and analysis method. The system and method can not only measure the thruster's discharge current, discharge voltage parameters, discharge channel inductance gradient parameters, plasma motion parameters, working fluid ablation mass, thruster impulse, specific impulse, and system efficiency macro-performance parameters in a microsecond time scale, but also obtain the changes in the system parameter settings on the system's discharge circuit equivalent resistance, inductance, discharge energy transmission efficiency, Lorentz force accelerated ablation working fluid ratio, aerodynamic force accelerated ablation working fluid ratio rate and other micro-characteristics, thereby achieving quantitative characterization of micro-characteristics while achieving the measurement of macro-performance parameters.

[0020] 2. The method for analyzing the discharge characteristics and dynamic performance parameters proposed by the method of the present invention has the following advantages over the existing measurement methods: First, it can not only obtain macroscopic characteristics such as discharge current and voltage, but also obtain changes in microscopic parameters such as equivalent resistance and inductance. Since the energy distribution of the LCR discharge loop circuit is related to the ratio of the plasma equivalent resistance in the discharge channel to the external circuit resistance, the internal mechanism of energy distribution caused by a certain parameter change can be obtained, and the influence of a certain parameter change on the energy utilization efficiency of the system can be analyzed, which provides a way for researchers to master the law of improving the initial energy utilization efficiency of the thruster. Second, it can not only measure the macroscopic performance parameters of the thruster, but also analyze the coupling relationship between the discharge characteristics and the mechanical characteristics of the thruster, measure the plasma jet motion characteristics, obtain the magnitude of the impulse generated by the Lorentz force and aerodynamic force in the discharge ablation working fluid, and the ratio of the ablation ionization working fluid and the aerodynamic acceleration working fluid, which provides direct quantitative characterization and change laws for how to improve the ratio of the working fluid accelerated by the Lorentz force and the utilization efficiency of the working fluid.

[0021] 3. The plate inductance gradient measurement technology proposed in the method of the present invention realizes the quantitative measurement and characterization of the thruster discharge plate inductance gradient. The main advantages are as follows: First, the detection method is simple. In practical applications, it is only necessary to use the proposed method to short-circuit the LCR loop and measure the discharge current to obtain the equivalent inductance of the loop at different positions. By qualitatively analyzing the discharge loop inductance at different positions of the plate, the inductance gradient of the discharge plate can be obtained. Furthermore, since the plate inductance gradient is related to the Lorentz force exerted on the plasma in the discharge channel, the law of accelerated change of the electromagnetic force exerted on the ablation and ionization components of the working fluid during the discharge process can also be obtained, and then the proportion of effectively ionized working fluid in the working fluid can be derived; second, compared with the existing empirical formula for the plate inductance gradient, the empirical formula cannot reflect the influence of the change in the plate thickness on the inductance gradient, and the detection and measurement value proposed by the invention is more accurate; third, it meets the measurement of the inductance gradient of plates with different configurations. The empirical formula of the plate inductance gradient cannot estimate the inductance gradient when the plate has special configurations such as different expansion angles and sharp angles. The detection measurement can meet the inductance gradient measurement of plates with different configurations. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a functional block diagram of an embodiment of a pulse electromagnetic thruster performance detection system of the present invention; Figure 2 It is a flow chart of an embodiment of a pulse electromagnetic thruster performance analysis method of the present invention; Figure 3 It is a schematic diagram of the discharge circuit waveform detected by the pulse current detector of the present invention.

[0023] Description of Figure Numbers: 10. DC power supply; 20. Ignition trigger controller; 30. Pulse current detector; 40. High voltage detector; 50. Discharge waveform collector; 60. Pulse electromagnetic thruster; 70. Plate inductance intensity measuring device; 80. Thruster impulse measuring device; 90. Plasma motion speed measuring device. DETAILED DESCRIPTION

[0024] In order to better understand the above technical solution, the above technical solution will be described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0025] like Figure 1 and Figure 2 As shown, the first embodiment of the present invention proposes a pulse electromagnetic thruster performance detection system, including a DC power supply 10, an ignition trigger controller 20, a pulse current detector 30, a pulse high voltage detector 40, a discharge waveform collector 50, a pulse electromagnetic thruster 60, a plate inductance intensity measuring device 70, a thruster impulse measuring device 80 and a plasma motion speed measuring device 90, wherein the DC power supply 10 is electrically connected to the pulse electromagnetic thruster 60 and is used to charge the pulse electromagnetic thruster 60; the pulse current detector 30 is placed around the pulse electromagnetic thruster 60 and is used to detect the pulse current amplitude data of the discharge circuit of the pulse electromagnetic thruster 60; the pulse high voltage detector 40 is loaded on the pulse electromagnetic thruster 60 and is used to detect the discharge circuit voltage waveform data of the pulse electromagnetic thruster 60; the discharge waveform collector 50 is respectively connected to the ignition trigger controller 20, the pulse current detector 30, and the pulse high voltage detector 40. The current detector 30 is connected to the pulse high voltage detector 40, and is used to collect the discharge circuit pulse current amplitude data detected by the pulse current detector 30 and the discharge circuit voltage waveform data detected by the pulse high voltage detector 40 according to the collection trigger signal provided by the ignition trigger controller 20; the pulse electromagnetic thruster 60 is installed on the thruster impulse measuring device 80; the plate inductance intensity measuring device 70 is arranged close to the pulse electromagnetic thruster 60, and is used to measure the inductance gradient of the plate discharge channel of the pulse electromagnetic thruster 60 under different plate configurations; the thruster impulse measuring device 80 is located below the pulse electromagnetic thruster 60, and is used to obtain the thruster output impulse value when the pulse electromagnetic thruster 60 is discharging; the plasma movement speed measuring device 90 is arranged at the front end of the nozzle of the pulse electromagnetic thruster 60, and is used to measure the movement speed of the plasma plume ejected by the pulse electromagnetic thruster 60.

[0026] In the above structure, see Figure 1In the pulse electromagnetic thruster performance detection system provided in this embodiment, the pulse current detector 30 adopts a Rogowski coil or a current transformer. The pulse high voltage detector 40 adopts a high voltage probe or a capacitive voltage divider. The pulse electromagnetic thruster 60 adopts a pulse plasma thruster, a laser electromagnetic induced plasma thruster or a magnetic plasma thruster. The plate inductance intensity measuring device 70 includes an electric displacement platform, a short-circuited copper bar, a support rod and a copper bar clamp, the support rod is vertically arranged above the electric displacement platform, one end of the copper bar clamp is connected to the support rod, and the other end of the copper bar clamp is used to clamp the short-circuited copper bar. The discharge waveform collector 50 adopts a high-speed oscilloscope or a high-speed data acquisition card. The thruster impulse measuring device 80 adopts a torsion wire impulse measuring device, a torsion pendulum impulse measuring device or an inverted pendulum balance impulse measuring device. The plasma motion speed measuring device 90 adopts a probe array, an ultra-high-speed camera and a narrow-band filter. Specifically, in this embodiment, the positive and negative outputs of the DC power supply 10 are connected to the two poles of the energy storage capacitor of the pulse electromagnetic thruster 60 through a transmission line, and the energy storage capacitor is charged; the Rogowski coil is placed around the transmission line between the energy storage capacitor of the pulse electromagnetic thruster 60 and the anode plate of the pulse electromagnetic thruster 60, and is used to detect the pulse current of the thruster discharge circuit; the high-voltage probe is loaded on the positive and negative poles of the energy storage capacitor of the pulse electromagnetic thruster 60, respectively, and is used to detect the voltage waveform of the discharge circuit; the high-speed oscilloscope (or high-speed data acquisition card) is connected to the Rogowski coil and the high-voltage probe, respectively, and is used to collect the discharge current and the high-voltage waveform data of the discharge circuit when the pulse electromagnetic thruster 60 is in discharge operation; the pulse electromagnetic thruster 60 is installed on the thruster impulse measuring device 80, and the thruster impulse measuring device 80 is used to obtain the thruster output impulse value when the pulse electromagnetic thruster 60 is in discharge operation. The short-circuited copper bar adopts a cylindrical or strip-shaped copper bar with a cross-sectional width of about 1mm, and its length is longer than the distance between the positive and negative plates of the thrust discharge channel. The copper bar clamp clamps the short-circuited copper bar and is fixedly connected to the electric displacement platform through a support rod. The plasma motion velocity measuring device 90 can be a probe array, an ultra-high-speed camera and a narrow-band filter, which is used to measure the motion velocity of the plasma plume ejected by the thruster. The double probe adopts a white tungsten wire with a diameter of Ф0.05 ​​to Ф0.6mm, and a ceramic tube is used to provide support and electrical insulation for the probe. The length of the exposed ceramic tube of the tungsten wire is 6mm to 12mm, and the distance between the two tungsten wire probes is 1mm to 3mm. A bias DC voltage of 12V to 24V is applied between the probes, and a sampling resistor of 20Ω to 50Ω is connected in series on the tungsten wire probe circuit. A filter capacitor with a capacity of 10nF is connected in parallel at both ends of the sampling resistor, and an oscilloscope probe is used to obtain the voltage change waveform at both ends of the sampling resistor. The dual probe array includes 4 dual probes, each dual probe is equally spaced, and each dual probe is placed on the central axis of the thruster nozzle. When the dual probe array is used, the voltage waveform collected by the dual probe is output to a high-speed oscilloscope or a high-speed data acquisition card.The ignition trigger controller is connected to a high-speed oscilloscope (or a high-speed data acquisition card) to provide an acquisition trigger signal for oscilloscope signal acquisition.

[0027] The present invention relates to a pulse electromagnetic thruster performance analysis method, which is applied to the above-mentioned pulse electromagnetic thruster performance detection system. The pulse electromagnetic thruster performance analysis method comprises the following steps: Step S100, measuring the inductance gradient of the discharge channel of the pulse electromagnetic thruster: boosting the low voltage DC power of the DC power supply and supplying the energy storage capacitor of the pulse electromagnetic thruster to charge to the rated voltage; using the electric displacement platform to control the short-circuited copper bar to short-circuit the cathode and anode plates of the pulse electromagnetic thruster at the starting position of the thruster discharge channel, the main discharge energy storage capacitor of the pulse electromagnetic thruster is discharged, and a pulse current is generated in the discharge circuit, the pulse current detector detects the pulse current, and the discharge waveform collector collects multiple discharge pulse current amplitude data at the starting position of the thruster discharge channel, and obtains the average value of the current amplitude over time; using the electric displacement platform to control the short-circuited copper bar at different positions X of the discharge channel i Short-circuit and obtain multiple discharge pulse current waveform data at this position; according to the equivalent inductance formula of the LCR discharge circuit, combined with the measured discharge cycle and ignition energy storage capacitance value, obtain the inductance value L at different short-circuit positions. eqxi Data; then according to the different positions X in the discharge channel i And the inductance value L at different short-circuit positions eqxi The data is fitted to obtain the discharge channel inductance gradient L'.

[0028] Step S200, obtaining the discharge characteristic parameters of the pulsed electromagnetic thruster: the ignition trigger controller controls the discharge operation of the plasma induction source, and induces the main discharge circuit of the pulsed electromagnetic thruster to generate a pulse current. The working fluid of the pulsed electromagnetic thruster is acted upon by the discharge arc between the cathode and anode plates of the discharge channel, and is ablated and ionized, and is accelerated to be ejected out of the discharge channel; the pulse current detector detects the pulse current waveform data of the discharge circuit, and the high-voltage detector detects the voltage waveform data of the discharge circuit; the impulse generated by the Lorentz force is calculated based on the discharge channel inductance gradient L' obtained by fitting and the pulse current waveform data of the discharge circuit obtained by detection .

[0029] Step S300, obtaining the dynamic performance parameters of the pulsed electromagnetic thruster: obtaining the mass of the working fluid ablated by a single pulse ; Obtain the velocity of the plasma plume ejected by the pulsed electromagnetic thruster measured by the plasma velocity measurement device ; Obtain the pulsed electromagnetic thruster output element impulse I measured by the thruster impulse measuring device bit ; According to the single pulse ablation working fluid quality and the velocity of the plasma plume , and the impulse generated by the Lorentz force is calculated , calculate the ratio of the working fluid accelerated by the Lorentz force and the velocity of the pneumatic accelerator .

[0030] Furthermore, the pulse electromagnetic thruster performance analysis method provided in this embodiment, step S100 specifically includes: Step S110: The low-voltage DC power provided by the low-voltage DC power supply is boosted and then charged to the pulse electromagnetic thruster energy storage capacitor to a rated voltage via the high-voltage DC power supply.

[0031] Step S120, using the two-dimensional displacement platform to control the short-circuited copper bar to short-circuit the thruster cathode and anode plates at the starting position of the thruster discharge channel, so that the thruster main discharge energy storage capacitor is discharged and a pulse current is generated in the discharge circuit.

[0032] Step S130: The Rogowski coil or current transformer detects the pulse current, and the high-speed oscilloscope (or high-speed data acquisition card) collects the discharge current amplitude data.

[0033] Step S140, repeat the above process 10 to 20 times, obtain multiple discharge current data, and obtain the average value of the current amplitude changing with time.

[0034] Step S150, using a two-dimensional displacement platform, controlling the short-circuited copper bar to short-circuit at different positions Xi of the discharge channel, and obtaining multiple discharge current data at the position (the discharge current waveform is a typical LCR discharge circuit waveform).

[0035] Step S160: According to the LCR discharge circuit equivalent inductance formula , combined with the measured discharge cycle and ignition energy storage capacitance value, the inductance value at different short-circuit positions can be obtained , and then according to the location and The data can be fitted to obtain the discharge channel inductance gradient L'.

[0036] Preferably, the pulsed electromagnetic thruster performance analysis method provided in this embodiment, step S200 specifically includes: Step S210, the pulse electromagnetic thruster is installed at the thruster installation position of the impulse measuring device, the low-voltage DC power provided by the low-voltage DC power supply is boosted and then outputted as a high-voltage voltage through the high-voltage DC power supply, the thruster main discharge energy storage capacitor and the plasma induction source ignition circuit energy storage capacitor are charged to a set voltage, the controller is triggered to make the plasma induction source discharge and work, and a pulse current is induced in the main discharge circuit of the pulse electromagnetic thruster, under the ablation and ionization action of the discharge arc between the cathode and anode plates of the thruster discharge channel, the thruster working fluid is ablated and gasified, wherein part of the ablation products are ionized to form plasma, and the working fluid ablation products are accelerated in the discharge channel under the combined action of the Lorentz force and the thermodynamic force, and ejected out of the discharge channel.

[0037] Step S220: The pulse current detector detects the pulse current waveform of the discharge circuit, and the high-voltage probe detects the discharge voltage waveform of the discharge circuit.

[0038] like Figure 3 As shown, a pulse current detector is installed on the energy storage capacitor to plasma induction source circuit to collect the discharge during the plasma induction source discharge process. Since the discharge circuit is equivalent to an LCR circuit, its typical discharge current waveform is a sinusoidal oscillation discharge. The discharge current waveform collected by its current transformer is transmitted to the control chip in the control circuit, and the control program performs fitting processing on the current data in the following manner.

[0039] The equivalent inductance of the discharge circuit is And equivalent resistance , as shown in formulas (1) and (2).

[0040] (1) (2)

[0041] In formulas (1) and (2), is the equivalent inductance of the discharge circuit, is the equivalent resistance of the discharge circuit, is the discharge cycle, is the main capacitor value, is the maximum forward discharge current, is the peak value of reverse discharge current.

[0042] Furthermore, we have: (3) In formula (3), is the equivalent inductance of the discharge circuit, is the equivalent resistance of the discharge circuit, , are the inductance and resistance of the external circuit respectively, , are the equivalent inductance and resistance in the discharge channel of the plasma induction source. Since the resistance of the external circuit remains unchanged, The change in the value represents the change in the equivalent resistance in the discharge channel of the plasma induced source.

[0043] The initial energy of the main capacitor of the pulsed electromagnetic thruster is: (4) In formula (4), is the initial energy of the main capacitor of the pulsed electromagnetic thruster, is the main capacitor value, The charging voltage value of the main capacitor.

[0044] The energy input into the thruster discharge channel can be calculated from the measured discharge voltage and current. and the efficiency of converting system energy into discharge energy : (5) (6) In formulas (5) and (6), is the energy of the thruster discharge channel, is the efficiency of converting system energy into discharge energy, is the discharge time, is the variation of discharge voltage over time, is the variation of discharge current over time, is the initial energy of the main capacitor of the pulsed electromagnetic thruster.

[0045] Through the above method, the change value of the plasma equivalent inductance and resistance in the discharge channel, the energy and proportion of the initial energy effectively transferred to the discharge channel for ablating ionized working fluid and accelerating ablation products can be obtained through the measured discharge current and discharge voltage data. The energy distribution of the LCR circuit is related to the ratio of the plasma equivalent resistance in the discharge channel to the external circuit resistance, so the internal mechanism of energy distribution caused by a certain parameter change can be obtained.

[0046] Furthermore, the pulsed electromagnetic thruster performance analysis method provided in this embodiment, step S300 specifically includes: Step S310: The impulse measuring device measures the impulse value output by the pulse electromagnetic thruster at the initial energy. .

[0047] Step S320: Since the mass of a single pulse ablation of a single pulse electromagnetic thruster is very small, in order to accurately measure the mass of the working fluid ablated by a single pulse, a high-precision electronic balance is used to weigh the mass change of the working fluid after more than 5000 discharges, and the mass of the working fluid ablated by a single pulse m can be calculated by averaging. bit .

[0048] Step S330: Elementary impulse Lorentz force and aerodynamic force to generate impulse The sum is: (7) In formula (7), is the element impulse, is the Lorentz force, Generates impulse for aerodynamic force.

[0049] The impulse generated by the Lorentz force It can be calculated by combining the L' measured in step S100 with the following formula: (8) In formula (8), is the Lorentz force, is the inductance gradient of the discharge channel, is the discharge time, is the discharge current.

[0050] The ratio of the impulse generated by the Lorentz force to the elementary impulse is: (9) In formula (9), is the ratio of the impulse generated by the Lorentz force to the elementary impulse, is the Lorentz force, For the element impulse.

[0051] Step S340: In order to more accurately measure the plasma motion speed under various working conditions , four Langmuir double probes with bias voltage are placed at different spatial angles in the thruster plume area at 8cm, 12cm, 16cm, and 20cm from the working fluid end surface. p The vertical axis is the time t of the first peak of the signal collected by the probe at different positions. peak The horizontal axis is used to fit each numerical point using the least squares estimate. The plasma movement speed can be estimated based on the slope of the fitted straight line. .

[0052] Meta-impulse It can also be expressed as: (10) In formula (10), is the element impulse value, is the mass of the working fluid for a single pulse ablation, The aerodynamic force accelerates the speed of the working fluid; is the velocity of the plasma plume, is the proportion of the working fluid accelerated by the Lorentz force to ablate.

[0053] Furthermore, by changing the setting of system parameters and repeating the above process, the changes in the system discharge and mechanical properties under different parameter setting conditions can be obtained, and the internal change trend of the system performance caused by parameter changes can be summarized to analyze the internal mechanism.

[0054] In order to solve the problem that the relationship between the system electrical parameters, configuration parameters and thruster performance parameters cannot be decoupled and characterized when the system parameters of the existing pulse electromagnetic thruster change, the present invention provides a pulse electromagnetic thruster working performance detection system and analysis method. The system and method can measure the thruster's discharge current, discharge voltage parameters, discharge channel inductance gradient parameters, plasma motion parameters, working fluid ablation mass, thruster impulse, specific impulse, and system efficiency macro performance parameters, and analyze and obtain the system discharge circuit equivalent resistance, inductance, discharge energy transmission efficiency, Lorentz force accelerated ablation working fluid ratio, aerodynamic force accelerated ablation working fluid ratio rate and other micro characteristic changes under the system parameter setting, which is of great significance for the pulse plasma electromagnetic thruster system parameter design, performance optimization and mechanism research.

[0055] The pulse electromagnetic thruster performance detection system and analysis method provided in this embodiment can accurately measure the key performance parameters of the thruster, such as discharge current, discharge voltage, inductance gradient, plasma motion characteristics, etc., as well as macroscopic performance parameters such as impulse, specific impulse and system efficiency. More importantly, it can also deeply reveal the microscopic characteristics such as the equivalent resistance and inductance of the discharge circuit, the discharge energy transmission efficiency, and the proportional change of the Lorentz force and aerodynamic force in the ablative working fluid acceleration under different system parameter settings. These detailed performance data and microscopic characteristic analysis play a vital role in optimizing the design of pulse electromagnetic thrusters, improving their performance, and deeply understanding their working mechanism, thereby solving the problem of accurately evaluating and optimizing thruster performance when parameters change.

[0056] The pulse electromagnetic thruster performance detection system and analysis method provided in this embodiment are of great significance for accurately measuring and deeply analyzing the performance characteristics of pulse electromagnetic thrusters. The system can not only accurately capture the key performance parameters of the thruster, such as discharge current, discharge voltage, inductance gradient, plasma motion characteristics, etc., but also conduct detailed analysis of macro performance parameters such as impulse, specific impulse and system efficiency.

[0057] What is even more striking is that the pulse electromagnetic thruster performance detection system and analysis method provided in this embodiment can also reveal the change rules of microscopic characteristics such as equivalent resistance and inductance of the discharge circuit and discharge energy transmission efficiency under different system parameter settings. In addition, it can also analyze in detail the proportional changes of Lorentz force and aerodynamic force in the acceleration of ablative working fluid, providing strong data support for our in-depth understanding of the working mechanism of thrusters.

[0058] These detailed performance data and microscopic characteristic analysis play a vital role in optimizing the design of pulsed electromagnetic thrusters. They help to more accurately predict and evaluate the performance of thrusters under various parameter settings, thereby guiding researchers to carry out targeted design optimization and further improve the performance of thrusters.

[0059] It is worth mentioning that the pulse electromagnetic thruster performance detection system and analysis method provided in this embodiment solves the long-standing problem of accurately evaluating and optimizing thruster performance when parameters change. Traditional performance detection methods often find it difficult to fully capture the performance characteristics of thrusters, especially when parameters change, and their accuracy and reliability are often questioned. However, with this new working performance detection system and analysis method, we can understand the performance characteristics of thrusters more comprehensively and deeply, and provide a more accurate and reliable basis for the design and optimization of thrusters.

[0060] In general, the pulse electromagnetic thruster performance detection system and analysis method provided in this embodiment not only provides new tools and means for the performance detection and optimization of pulse electromagnetic thrusters, but also opens up a new way for us to deeply understand the working mechanism of thrusters. Its emergence will undoubtedly have a far-reaching impact on the development of the electromagnetic thruster field.

[0061] Although preferred embodiments of the present invention have been described, additional changes and modifications may be made to these embodiments by those skilled in the art once the basic inventive concepts are known. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present invention. Obviously, those skilled in the art may make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

Claims

1. A pulse electromagnetic thruster performance detection system, characterized in that: The invention comprises a direct current power supply (10), an ignition trigger controller (20), a pulse current detector (30), a pulse high voltage detector (40), a discharge waveform collector (50), a pulse electromagnetic thruster (60), a plate inductance intensity measuring device (70), a thruster impulse measuring device (80) and a plasma motion speed measuring device (90), wherein: The direct current power supply (10) is electrically connected to the pulsed electromagnetic thruster (60) and is used to charge the pulsed electromagnetic thruster (60); The pulse current detector (30) is placed around the discharge circuit transmission line of the pulse electromagnetic thruster (60) and is used to detect the pulse current amplitude data of the discharge circuit of the pulse electromagnetic thruster (60); The pulse high voltage detector (40) is loaded on the pulse electromagnetic thruster (60) and is used to detect the discharge circuit voltage waveform data of the pulse electromagnetic thruster (60); The discharge waveform collector (50) is connected to the ignition trigger controller (20), the pulse current detector (30) and the pulse high voltage detector (40) respectively, and is used to collect the discharge circuit pulse current amplitude data detected by the pulse current detector (30) and the discharge circuit voltage waveform data detected by the pulse high voltage detector (40) according to the collection trigger signal provided by the ignition trigger controller (20); The pulse electromagnetic thruster (60) is mounted on the thruster impulse measuring device (80); The plate inductance intensity measuring device (70) is arranged close to the pulse electromagnetic thruster (60) and is used to measure the inductance gradient of the plate discharge channel of the pulse electromagnetic thruster (60) under different plate configurations; The thruster impulse measuring device (80) is located below the pulse electromagnetic thruster (60) and is used to obtain the thruster output impulse value when the pulse electromagnetic thruster (60) is in discharge operation; The plasma motion speed measuring device (90) is arranged at the front end of the nozzle of the pulse electromagnetic thruster (60) and is used to measure the motion speed of the plasma plume ejected by the pulse electromagnetic thruster (60).

2. The pulse electromagnetic thruster performance detection system according to claim 1, characterized in that: The pulse current detector (30) is a Rogowski coil or a current transformer.

3. The pulse electromagnetic thruster performance detection system according to claim 1, characterized in that: The pulse high voltage detector (40) is a high voltage probe or a capacitive voltage divider.

4. The pulse electromagnetic thruster performance detection system according to claim 1, characterized in that: The pulsed electromagnetic thruster (60) is a pulsed plasma thruster, a laser electromagnetic induced plasma thruster or a magnetic plasma thruster.

5. The pulse electromagnetic thruster performance detection system according to claim 1, characterized in that: The electrode plate inductance strength measuring device (70) comprises an electric displacement platform, a short-circuited copper bar, a support rod and a copper bar clamp, wherein the support rod is vertically arranged above the electric displacement platform, one end of the copper bar clamp is connected to the support rod, and the other end of the copper bar clamp is used to clamp the short-circuited copper bar.

6. The pulse electromagnetic thruster performance detection system according to claim 1, characterized in that: The discharge waveform collector (50) is a high-speed oscilloscope or a high-speed data acquisition card.

7. The pulse electromagnetic thruster performance detection system according to claim 1, characterized in that: The thruster impulse measuring device (80) is a torsion wire type impulse measuring device, a torsion pendulum type impulse measuring device or an inverted pendulum balance type impulse measuring device.

8. The pulse electromagnetic thruster performance detection system according to claim 1, characterized in that: The plasma motion speed measuring device (90) comprises a probe array, an ultra-high-speed camera and a narrow-band filter.

9. A pulse electromagnetic thruster performance analysis method, applied to the pulse electromagnetic thruster performance detection system according to any one of claims 1 to 8, characterized in that: The pulsed electromagnetic thruster performance analysis method comprises the following steps: Measuring the inductance gradient of the discharge channel of the pulse electromagnetic thruster: boosting the low-voltage direct current of the direct current power supply and supplying it to the energy storage capacitor of the pulse electromagnetic thruster to charge to the rated voltage; using the electric displacement platform to control the short-circuited copper bar to short-circuit the cathode and anode plates of the pulse electromagnetic thruster at the starting position of the thruster discharge channel, the main discharge energy storage capacitor of the pulse electromagnetic thruster is discharged, and a pulse current is generated in the discharge circuit, the pulse current detector detects the pulse current, and the discharge waveform collector collects multiple discharge pulse current amplitude data at the starting position of the thruster discharge channel, and obtains the average value of the current amplitude changing with time; using the electric displacement platform to control the short-circuited copper bar at different positions X of the discharge channel i Short-circuit and obtain multiple discharge pulse current waveform data at this position; according to the equivalent inductance formula of the LCR discharge circuit, combined with the measured discharge cycle and ignition energy storage capacitance value, obtain the inductance value L at different short-circuit positions. eqxi Data; then according to the different positions X in the discharge channel i And the inductance value L at different short-circuit positions eqxi Data, fitting to obtain the discharge channel inductance gradient L'; Obtaining the discharge characteristic parameters of the pulsed electromagnetic thruster: the ignition trigger controller controls the discharge operation of the plasma induction source, and induces the main discharge circuit of the pulsed electromagnetic thruster to generate a pulse current. The working fluid of the pulsed electromagnetic thruster is acted upon by the discharge arc between the cathode and anode plates of the discharge channel, and is ablated and ionized, and is accelerated to be ejected out of the discharge channel; the pulse current detector detects the pulse current waveform data of the discharge circuit, and the high-voltage detector detects the voltage waveform data of the discharge circuit; the impulse generated by the Lorentz force is calculated based on the discharge channel inductance gradient L' obtained by fitting and the pulse current waveform data of the discharge circuit obtained by detection ; Obtain the dynamic performance parameters of the pulsed electromagnetic thruster: Obtain the mass of the working fluid ablated by a single pulse ; Obtain the movement speed of the plasma plume ejected by the pulsed electromagnetic thruster measured by the plasma movement speed measuring device ; Obtain the impulse I of the pulsed electromagnetic thruster output element measured by the thruster impulse measuring device bit According to the single pulse ablation working fluid quality and the velocity of the plasma plume , and the impulse generated by the Lorentz force is calculated , calculate the ratio of the working fluid accelerated by the Lorentz force and the velocity of the pneumatic accelerator .

10. The pulse electromagnetic thruster performance analysis method according to claim 9, characterized in that: In the step of obtaining the dynamic performance parameters of the pulsed electromagnetic thruster, the impulse value It is expressed as: in, is the element impulse value, is the mass of the working fluid for a single pulse ablation, The aerodynamic force accelerates the speed of the working fluid; is the velocity of the plasma plume, is the proportion of the working fluid accelerated by the Lorentz force to ablate.

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