Method for evaluating the remaining quantity of xenon under pressure and flow control for electric propulsion

Abstract

This invention relates to the field of space electric propulsion technology, and particularly to a method for assessing the remaining xenon quantity in electric propulsion under pressure and flow control. The method includes: performing the following steps for each electric propulsion ignition: determining the xenon consumption of the anode under the current electric propulsion ignition based on the anode flow rate collected at each ignition and the time interval between each collection; determining the xenon consumption of the cathode under the current electric propulsion ignition based on the pressure value output by the electronic depressurization system, the temperature value of the flow controller, the calibration relationship of the flow controller, and the time interval between each collection at each ignition; and determining the remaining xenon quantity of the electric propulsion system at the current ignition based on the initial mass of xenon refueling from the ground, the xenon consumption of the anode and cathode under the current electric propulsion ignition, and the xenon consumption of the anode and cathode during each historical electric propulsion ignition, thereby improving the accuracy of xenon quantity calculation.

Description

Technical Field

[0001] This invention relates to the field of space electric propulsion technology, and in particular to a method for assessing the remaining amount of xenon gas in electric propulsion under pressure and flow control. Background Technology

[0002] High-orbit satellites use electric propulsion for north-south position maintenance throughout their entire lifespan after reaching their designated orbit. This requires the electric propulsion system to have a reliable lifespan of 15 years in orbit and a cumulative firing time of 14,000 hours. The electric propulsion propellant supply system uses xenon as the ionized propellant for the electric thruster. The assessment of the remaining xenon supply directly determines the assessment of the electric propulsion lifespan, and thus, the overall satellite lifespan. Therefore, assessing the remaining xenon supply is crucial.

[0003] However, due to the complex physical properties of xenon, the remaining amount in the xenon cylinder cannot be accurately calculated using the traditional PVT method, resulting in a large error.

[0004] Therefore, a new method for assessing the remaining amount of xenon in electric propulsion is urgently needed. Summary of the Invention

[0005] To address the problem that traditional PVT methods cannot accurately calculate the remaining amount of xenon gas in a cylinder, this invention provides a method for assessing the remaining amount of xenon gas in an electric propulsion system under pressure and flow control.

[0006] In a first aspect, embodiments of the present invention provide a method for assessing the remaining amount of xenon gas in electric propulsion under pressure and flow control, comprising:

[0007] Obtain the initial mass of xenon gas during ground refueling;

[0008] During each electric propulsion ignition, the following is performed:

[0009] Based on the anode flow rate and the time interval between each sampling under the current electric propulsion ignition, determine the xenon consumption of the anode under the current electric propulsion ignition.

[0010] Based on the pressure value output by the electronic decompression system, the temperature value of the flow controller, and the calibration relationship of the flow controller during each data acquisition under the current electric propulsion ignition, as well as the time interval between each data acquisition, the xenon consumption of the cathode under the current electric propulsion ignition is determined.

[0011] Based on the initial mass of xenon, the xenon consumption of the anode and the cathode during the current electric propulsion ignition, and the xenon consumption of the anode and the cathode during each historical electric propulsion ignition, the remaining amount of xenon in the current electric propulsion working propellant supply system is determined.

[0012] In a second aspect, embodiments of the present invention also provide an electric propulsion working fluid supply system based on any of the methods described in the specification, comprising: an electronic pressure reduction system consisting of a Bang-bang solenoid valve and a pressure sensor; an anode flow closed-loop system consisting of a piezoelectric proportional valve and a flow sensor; a cathode flow closed-loop system consisting of a flow controller and a temperature sensor; and a controller for implementing the method as described in any of the specifications.

[0013] The output of the electronic pressure reducing system is connected to the inlet of the anode flow closed-loop system and the cathode flow closed-loop system respectively, and is used to provide inlet pressure for the anode flow closed-loop system and the cathode flow closed-loop system;

[0014] The piezoelectric proportional valve is used to control the anode flow rate of xenon gas, and the flow sensor is used to measure the xenon gas flow rate at the anode in real time.

[0015] The flow controller is used to control the cathode flow rate of xenon gas, and the temperature sensor is used to measure the temperature value of the flow controller.

[0016] This invention provides a method for assessing the remaining xenon quantity in electric propulsion under pressure and flow control. By determining the xenon consumption at the anode and cathode during each electric propulsion ignition, and subtracting the xenon consumption at the anode and cathode during previous electric propulsion ignitions from the initial mass of xenon during ground refueling, the remaining xenon quantity in the current electric propulsion propellant supply system is determined, thereby improving the accuracy of xenon quantity calculation in the electric propulsion propellant supply system. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a flowchart of a method for assessing the remaining amount of xenon gas in electric propulsion under pressure and flow control, provided by an embodiment of the present invention;

[0019] Figure 2 This is a schematic diagram of the structure of an electric propulsion working fluid supply system provided in an embodiment of the present invention. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0021] The following describes the specific implementation of the above concept.

[0022] Please refer to Figure 1 This invention provides a method for assessing the remaining amount of xenon gas in electric propulsion under pressure and flow control, the method comprising:

[0023] Step 100: Obtain the initial mass of xenon gas during ground refueling;

[0024] Step 102: During each electric propulsion ignition, perform the following: Based on the anode flow rate and the time interval between each sampling under the current electric propulsion ignition, determine the xenon consumption of the anode under the current electric propulsion ignition.

[0025] Step 104: Based on the pressure value output by the electronic decompression system, the temperature value of the flow controller, and the calibration relationship of the flow controller during each data acquisition under the current electric propulsion ignition, as well as the time interval between each data acquisition, determine the xenon consumption of the cathode under the current electric propulsion ignition.

[0026] Step 106: Based on the initial mass of xenon, the xenon consumption of the anode and the cathode under the current electric propulsion ignition, and the xenon consumption of the anode and the cathode under each historical electric propulsion ignition, determine the remaining amount of xenon in the current electric propulsion working propellant supply system.

[0027] In this embodiment of the invention, by determining the xenon consumption of the anode and the xenon consumption of the cathode at each electric propulsion ignition, and by subtracting the xenon consumption of the anode and the cathode at each previous electric propulsion ignition from the initial mass of xenon during ground refueling, the remaining xenon quantity of the electric propulsion working propellant supply system at the current time is determined, thereby improving the calculation accuracy of the remaining xenon quantity of the electric propulsion working propellant supply system.

[0028] For step 100:

[0029] In this step, the satellite will be refueled with a certain amount of xenon while on the ground to support its north-south position-keeping missions using the electric propulsion system throughout its entire lifespan in space. To accurately calculate the remaining xenon amount during the satellite's entire lifespan, it is necessary to obtain the initial mass of xenon at the time of ground refueling.

[0030] Regarding step 102:

[0031] In embodiments of the present invention, reference can be made to Figure 2 The diagram shows the structure of the electric propulsion propellant supply system, which includes an electronic pressure reduction system, an anode flow closed-loop system, and a cathode flow closed-loop system. By querying the current desired target value, the electronic pressure reduction system outputs the corresponding pressure value to stabilize the anode flow rate of xenon at the target value.

[0032] In some implementation methods, reference may be made to Figure 2 The anode flow rate is measured by a flow sensor in the anode flow closed-loop system, which consists of a piezoelectric proportional valve and a flow sensor. The piezoelectric proportional valve is used to stably control the xenon flow rate of the anode at the target value, and the flow sensor is used to measure the xenon flow rate of the anode in real time.

[0033] Therefore, at each electric propulsion ignition, the anode flow rate q of the electric propulsion working fluid supply system at each acquisition time can be measured using a flow sensor. i阳 The anode flow rate q at each sampling time i阳 The periodic time interval Δt at each acquisition i Multiplying these values ​​yields the xenon consumption of the anode for each sampling session. Adding the xenon consumption of the anode for all sampling sessions under the current electric propulsion ignition gives the xenon consumption of the anode under the current electric propulsion ignition. It can be understood that each electric propulsion ignition will involve several sampling sessions, and the time interval between each sampling session can be determined based on actual needs and circumstances; therefore, no specific time limit is set for the sampling cycle here.

[0034] Regarding step 104:

[0035] In some implementations, reference may continue to be made. Figure 2 The flow controller and temperature sensor form a cathode flow closed-loop system. The flow controller changes the xenon flow resistance by heating the valve body located in the flow controller, thereby changing the xenon flow rate of the cathode. The temperature sensor is used to measure the temperature value of the flow controller. The xenon flow rate of the cathode is related to the temperature of the flow controller and the inlet pressure of the flow controller.

[0036] In some implementations, reference may continue to be made. Figure 2 The electronic pressure reduction system consists of a Bang-bang solenoid valve and a pressure sensor. The Bang-bang solenoid valve is used to control the inlet pressure of the anode flow closed-loop system and the cathode flow closed-loop system. The pressure sensor is used to measure the pressure value output by the electronic pressure reduction system. The pressure value output by the electronic pressure reduction system is equal to the inlet pressure of the anode flow closed-loop system and the cathode flow closed-loop system.

[0037] In this embodiment, the Bang-bang solenoid valve and pressure sensor form an electronic pressure reduction system, with the pressure output exhibiting a sawtooth bang-bang pattern, fluctuating within a certain range positive and negative of the target pressure value. The piezoelectric proportional valve and flow sensor form an anode flow closed-loop system, which can stably control the anode flow rate at the target value. The flow sensor can measure the anode flow rate q in real time. i阳 The flow controller and temperature sensor form a cathode flow closed-loop system. The flow controller uses the temperature of the heated valve body to change the xenon flow resistance, thereby changing the xenon flow rate. At the same temperature, different inlet pressures (i.e., the pressure output by the electronic pressure reduction system) in the cathode flow closed-loop system result in different xenon flow rates at the cathode. Therefore, the xenon flow rate at the cathode can be calculated jointly from the flow controller's temperature (i.e., the temperature value measured by the temperature sensor) and the flow controller's inlet pressure (i.e., the pressure output by the electronic pressure reduction system).

[0038] It is understandable that the flow-pressure-temperature relationship of the flow controller needs to be calibrated in advance to obtain the calibration relationship of the flow controller. Based on the pressure value output by the electronic pressure reduction system and the temperature value of the flow controller in each acquisition, the xenon flow rate of the cathode can be determined. Furthermore, based on the xenon flow rate of the cathode and the time interval of each acquisition, the xenon consumption of the cathode in each acquisition can be determined, thus obtaining the xenon consumption of the cathode under the current electric propulsion ignition.

[0039] Specifically, the calibration relationship of the flow controller can be expressed as:

[0040] q 阴极 =f(P,T)

[0041] In the formula, q 阴极 Let f be the anode flow rate, f() be the functional relationship, P be the pressure value output by the electronic pressure reducing system, and T be the temperature value of the flow controller.

[0042] Therefore, each time the electric propulsion system ignites, the pressure value output by the electric propulsion electronic decompression system and the temperature value of the flow controller are measured, and f(P) is used. i ,T i ) to obtain the cathode flow rate at the i-th sampling, and then use f(P) i ,T i )Δt i Obtain the xenon consumption of the cathode during the i-th sampling of the electric propulsion propellant supply system; sum the xenon consumption of the cathode during all sampling times under the current electric propulsion ignition to obtain the xenon consumption of the cathode under the current electric propulsion ignition.

[0043] Regarding step 106:

[0044] In some implementations, step 106 may include:

[0045] Based on the xenon consumption of the anode during the previous electric propulsion ignition and the xenon consumption of the anode during each historical electric propulsion ignition, the total xenon consumption of the anode is determined.

[0046] Based on the xenon consumption of the cathode during the current electric propulsion ignition and the xenon consumption of the cathode during each previous electric propulsion ignition, the total xenon consumption of the cathode is determined.

[0047] Based on the initial xenon mass, the total xenon consumption of the anode, and the total xenon consumption of the anode, the remaining xenon quantity in the current electric propulsion working fluid supply system is determined.

[0048] In this embodiment of the invention, the remaining amount of xenon gas in the current electric propulsion propellant supply system can be calculated using the following formula:

[0049] m = m0 - m 阳 -m 阴

[0050] =m0-∑q i阳 Δt i -∑f(P i ,T i )Δt i

[0051] In the formula, m represents the current remaining amount of xenon in the electric propulsion working propellant supply system, m0 represents the initial mass of xenon, and m 阳 The total xenon consumption at the anode, m 阴 q represents the total xenon gas consumption at the cathode. i阳 Δt represents the anode flow rate at each sampling point. i Let f() be the time interval for each data acquisition, P be the pressure value output by the electronic pressure reducing system, T be the temperature value of the flow controller, and i represent the number of data acquisitions.

[0052] like Figure 2 As shown, this embodiment of the invention provides an electric propulsion working fluid supply system based on any of the methods described in the embodiments of this specification. The system includes: an electronic pressure reduction system composed of a Bang-bang solenoid valve and a pressure sensor; an anode flow closed-loop system composed of a piezoelectric proportional valve and a flow sensor; a cathode flow closed-loop system composed of a flow controller and a temperature sensor; and a controller for implementing any of the methods described in the embodiments of this specification.

[0053] The output of the electronic pressure reducing system is connected to the inlet of the anode flow closed-loop system and the cathode flow closed-loop system respectively, and is used to provide inlet pressure for the anode flow closed-loop system and the cathode flow closed-loop system;

[0054] A piezoelectric proportional valve is used to control the anode flow rate of xenon gas, and a flow sensor is used to measure the xenon gas flow rate at the anode in real time.

[0055] The flow controller is used to control the cathode flow rate of xenon gas, and the temperature sensor is used to measure the temperature value of the flow controller.

[0056] Since the above system is based on the same concept as the method embodiment of the present invention, the specific details can be found in the description of the method embodiment of the present invention, and will not be repeated here.

[0057] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus.

[0058] Those skilled in the art will understand that all or part of the steps of the above method embodiments can be implemented by hardware related to program instructions. The aforementioned program can be stored in a computer-readable storage medium. When the program is executed, it performs the steps of the above method embodiments. The aforementioned storage medium includes various media that can store program code, such as ROM, RAM, magnetic disk, or optical disk.

[0059] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for assessing the remaining amount of xenon gas in electric propulsion under pressure and flow control, applied to the controller of an electric propulsion working propellant supply system, characterized in that, include: Obtain the initial mass of xenon gas during ground refueling; During each electric propulsion ignition, the following is performed: Based on the anode flow rate and the time interval between each sampling under the current electric propulsion ignition, determine the xenon consumption of the anode under the current electric propulsion ignition. Based on the pressure value output by the electronic decompression system, the temperature value of the flow controller, and the calibration relationship of the flow controller during each data acquisition under the current electric propulsion ignition, as well as the time interval between each data acquisition, the xenon consumption of the cathode under the current electric propulsion ignition is determined. Based on the initial mass of xenon, the xenon consumption of the anode and the xenon consumption of the cathode under the current electric propulsion ignition, and the xenon consumption of the anode and the xenon consumption of the cathode during each previous electric propulsion ignition, the remaining amount of xenon in the current electric propulsion working propellant supply system is determined. The electric propulsion propellant supply system includes an electronic pressure reduction system, an anode flow closed-loop system, and a cathode flow closed-loop system. The electric propulsion propellant supply system controls the output pressure value of the electronic pressure reduction system by querying the current desired target value, so as to stably control the anode flow rate of xenon gas at the target value. The flow controller and temperature sensor form a cathode flow closed-loop system. The flow controller changes the xenon flow resistance by heating the valve body located in the flow controller, thereby changing the xenon flow rate at the cathode. The temperature sensor is used to measure the temperature value of the flow controller. The xenon flow rate at the cathode is related to the temperature of the flow controller and the inlet pressure of the flow controller. The electronic pressure reduction system consists of a Bang-bang solenoid valve and a pressure sensor. The Bang-bang solenoid valve is used to control the inlet pressure of the anode flow closed-loop system and the cathode flow closed-loop system. The pressure sensor is used to measure the pressure value output by the electronic pressure reduction system. The pressure value output by the electronic pressure reduction system is equal to the inlet pressure of the anode flow closed-loop system and the cathode flow closed-loop system. The calibration relationship of the flow controller is as follows: In the formula, For cathode flow rate, It is a functional relationship. The pressure value output by the electronic pressure reduction system. This refers to the temperature value of the flow controller.

2. The method according to claim 1, characterized in that, The anode flow rate is measured by a flow sensor in the anode flow closed-loop system, which consists of a piezoelectric proportional valve and the flow sensor. The piezoelectric proportional valve is used to stably control the xenon flow rate of the anode at the target value, and the flow sensor is used to measure the xenon flow rate of the anode in real time.

3. The method according to claim 1, characterized in that, The determination of the remaining xenon quantity in the electric propulsion working propellant supply system based on the initial xenon mass, the xenon consumption at the anode and cathode during the current electric propulsion ignition, and the xenon consumption at the anode and cathode during each historical electric propulsion ignition includes: Based on the xenon consumption of the anode under the current electric propulsion ignition and the xenon consumption of the anode during each historical electric propulsion ignition, the total xenon consumption of the anode is determined. Based on the xenon consumption of the cathode during the current electric propulsion ignition and the xenon consumption of the cathode during each previous electric propulsion ignition, the total xenon consumption of the cathode is determined. Based on the initial mass of xenon, the total xenon consumption of the anode, and the total xenon consumption of the anode, the remaining amount of xenon in the current electric propulsion working fluid supply system is determined.

4. The method according to claim 3, characterized in that, The remaining amount of xenon gas in the current electric propulsion propellant supply system is calculated using the following formula: In the formula, This refers to the remaining xenon gas in the current electric propulsion propellant supply system. The initial mass of the xenon gas is... This represents the total xenon gas consumption at the anode. This represents the total xenon gas consumption at the cathode. The anode flow rate at each data collection point. The time interval for each data collection. It is a functional relationship. The pressure value output by the electronic pressure reduction system. The temperature value is the value from the flow controller, and i represents the number of times the data was collected.

5. An electric propulsion working propellant supply system based on the method of any one of claims 1-4, characterized in that, include: An electronic pressure reducing system consisting of a Bang-bang solenoid valve and a pressure sensor; an anode flow closed-loop system consisting of a piezoelectric proportional valve and a flow sensor; a cathode flow closed-loop system consisting of a flow controller and a temperature sensor; and a controller for implementing the method as described in any one of claims 1-4. The output of the electronic pressure reducing system is connected to the inlet of the anode flow closed-loop system and the cathode flow closed-loop system respectively, and is used to provide inlet pressure for the anode flow closed-loop system and the cathode flow closed-loop system; The piezoelectric proportional valve is used to control the anode flow rate of xenon gas, and the flow sensor is used to measure the xenon gas flow rate at the anode in real time. The flow controller is used to control the cathode flow rate of xenon gas, and the temperature sensor is used to measure the temperature value of the flow controller.

Images