Wide-adjustment high-reliability Hall electric propulsion system and control method

Abstract

The invention provides a wide-adjustment high-reliability electric propulsion system and a control method. The wide-adjustment high-reliability electric propulsion system comprises a pressure adjustment module, a flow adjustment module and a Hall thruster. The flow adjusting module is composed of an electromagnetic valve and a flow distributor. According to the Hall thruster flow distributor, through different previous series-parallel connection relations, on the premise that flow distributors are not added, the Hall thrusters can work in pairs, meanwhile, the backup number of the cathode flow distributor and the anode flow distributor is increased, and the system reliability is improved. By arranging the flow resistance step of the flow distributor, the large-range flow adjusting capacity of the cathode and anode inlets of the Hall thruster can be obtained, and therefore the large-range variable thrust working mode, the cathode large-flow ignition mode and the anode low-flow starting mode of the Hall thruster are achieved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of space electric propulsion technology, in particular, to a wide adjustment high-reliability Hall electric propulsion system and a control method. BACKGROUND

[0002] The space electric propulsion system generally uses proportional valves or throttling elements to control the inlet flow of the thruster. When using throttling elements for flow regulation, there are two common design schemes. Scheme one: flow distributor, i.e. throttling element and Hall thruster anode, cathode inlet solenoid valve one-to-one correspondence; Scheme two: each cathode branch and anode branch adopts double solenoid valve series redundant design to ensure the system external sealing. Only the anode flow distributor, i.e. throttling element, has a backup, and the downstream solenoid valve is connected in parallel to the anode thruster. The main cathode gas path and the main anode gas path are connected in series with redundant solenoid valves upstream, and the backup cathode gas path and the backup anode gas path are connected in series with redundant solenoid valves upstream.

[0003] However, the existing technology of the propellant supply scheme for electric propulsion, as shown in Figure 3 , only the anode flow distributor has a backup, and different electric thruster flow distributors cannot share the backup. Once the flow distributor is selected, its flow regulation range is limited, and it cannot achieve large range variable thrust. The flow distributor is essentially a large flow resistance throttling element, whether it is designed through a porous medium or a labyrinth flow channel. Its failure mode is mostly clogging, which will cause the electric thruster to fail to work normally, thereby affecting the on-orbit use of the electric propulsion system. SUMMARY

[0004] In view of the defects in the prior art, the purpose of the present application is to provide a wide adjustment high-reliability Hall electric propulsion system and a control method.

[0005] According to the wide adjustment high-reliability Hall electric propulsion system provided by the present application, it comprises: a gas storage module, a pressure regulation module, a flow regulation module and a Hall thruster. The gas storage module, the pressure regulation module, the flow regulation module and the Hall thruster are connected in sequence. The gas storage module is used for storing the propellant required by the Hall electric propulsion system. The pressure regulation module is used for reducing the high-pressure propellant output by the gas storage module to stable low-pressure propellant meeting the preset requirements through two-stage pressure reduction, so as to provide stable inlet pressure for the flow regulation module. The flow regulation module is used for controlling the flow of the propellant entering the cathode and anode of the Hall thruster. The Hall thruster is the thrust execution mechanism of the Hall electric propulsion system. After the propellant entering the Hall thruster is ionized, it is accelerated by the electric field and sprayed at high speed to provide thrust for the spacecraft.

[0006] Preferably, the flow regulating module comprises n sets of flow regulating sub-modules; Each set of the flow regulating sub-modules comprises an anode flow regulating unit and a cathode flow regulating unit; The anode flow regulating unit is configured to control the flow of propellant into the anode of the Hall thruster; The cathode flow regulating unit is configured to control the flow of propellant into the cathode of the Hall thruster; The Hall thruster comprises n sets of Hall thrusters, each set of the Hall thrusters comprising a first Hall thruster and a second Hall thruster; and any one or more of the n sets of Hall thrusters can work simultaneously; The cathode flow regulating unit is connected to the primary and backup cathodes of the first Hall thruster and the second Hall thruster, respectively; The anode flow regulating unit is connected to the anodes of the first Hall thruster and the second Hall thruster, respectively.

[0007] Preferably, the cathode flow regulating unit comprises downstream solenoid valves SVd5-SVd8 of a flow distributor, flow distributors J1-J4, downstream solenoid valves SV1-1, SV1-3, SV4-1, SV4-3 of the flow distributor; The anode flow regulating unit comprises downstream solenoid valves SVd9-SVd12 of a flow distributor, flow distributors J5-J8, downstream solenoid valves SV1-2, SV1-4, SV4-2, SV4-4 of the flow distributor; The downstream solenoid valves SV1-1, SV1-3 of the flow distributor are connected to the primary and backup cathodes A1, B1 of the first Hall thruster, respectively, and the downstream solenoid valves SV1-2, SV1-4 of the flow distributor are connected to the anode of the first Hall thruster after being connected in parallel downstream; The downstream solenoid valves SV4-1, SV4-3 of the flow distributor are connected to the primary and backup cathodes A4, B4 of the second Hall thruster, respectively, and the downstream solenoid valves SV4-2, SV4-4 of the flow distributor are connected to the anode of the second Hall thruster after being connected in parallel downstream.

[0008] Preferably, the flow distributors J1-J4 of the cathode flow regulating unit are backup to each other, and any one to four of the flow distributors can be selected to supply any one to two cathodes A1, A4, B1, B4 of the primary and backup cathodes of the first Hall thruster and the second Hall thruster.

[0009] Preferably, the flow distributors J5-J8 of the anode flow regulating unit are backup to each other, and any one to four of the flow distributors can be selected to supply any one to two anodes of the first Hall thruster and the second Hall thruster.

[0010] Preferably, when the primary backup cathode top orifice of the first Hall thruster and the primary backup cathode top orifice of the second Hall thruster are blocked, the optional 4-way cathode flow distributor flushes the Hall thruster cathode.

[0011] Preferably, when any one of the flow distributors of the cathode flow regulating unit or the anode flow regulating unit is blocked, the blocked flow distributor is isolated, and the remaining flow distributors of the cathode flow regulating unit or the anode flow regulating unit are designated as flow suppliers.

[0012] Preferably, the anode flow is set by the number of valve switching paths, so as to realize thrust regulation.

[0013] According to the present application, a wide-regulation high-reliability Hall electric propulsion system control method is provided, which comprises the following steps: Step S1: Before the Hall electric propulsion system is ignited, the working Hall thruster is designated, and the thrust value of the designated working Hall thruster is set. Step S2: The Hall electric propulsion system thruster cathode ignition process is triggered, the Hall thruster cathode gas supply is started, the Hall thruster cathode is ignited, if the Hall thruster cathode ignition fails, the valve opening path is configured according to the cathode large flow set value to increase the cathode flow supply, if the cathode ignition is successful, it is judged whether the current Hall thruster cathode gas supply is restored to the rated flow, if the cathode ignition fails and has timed out, the ignition program is exited. Step S3: The Hall electric propulsion system thruster anode ignition process is triggered, the Hall thruster anode gas supply is started, the Hall thruster anode is ignited, and the program is ended until the end of the orbit control countdown.

[0014] Preferably, the step S3 comprises: During the Hall thruster anode gas supply process, it is judged whether the current Hall thruster anode gas supply is selected to start with low flow, if the Hall thruster anode is selected to start with low flow, the valve opening path is configured according to the anode low flow set value, if the thruster anode is not selected to start with low flow, the Hall thruster anode flow Y0 is set, the valve opening path is configured according to the corresponding thrust set value F0, the Hall thruster anode ignition is started, if the anode ignition is successful, it is judged according to the task demand whether the anode gas supply flow is restored to Y0; According to the task demand, it is judged whether the thrust is regulated, if yes, the phased adjustment is performed according to the demand.

[0015] Compared with the prior art, the present application has the following beneficial effects: 1. The application can share backup for the cathode and anode flow distributors of the thruster without increasing the flow distributor assembly, and when one of the flow distributors is blocked at the end of the life of the Hall electric propulsion system, the other three flow distributors can be used for flow control, which helps to improve the working reliability of the electric propulsion system. 2. The application has a wide range of Hall thruster cathode and anode inlet flow adjustment capability through the flow distributor flow resistance ladder, so as to realize the Hall thruster wide range variable thrust working mode, cathode large flow ignition mode and anode low flow starting mode. BRIEF DESCRIPTION OF DRAWINGS

[0016] Other features, objects and advantages of the application will become more apparent from the following detailed description of non-limiting embodiments with reference to the attached drawings: Figure 1 The device principle diagram of the wide adjustment and high reliability electric propulsion system.

[0017] Figure 2 The control flow chart of the wide adjustment and high reliability electric propulsion system.

[0018] Figure 3 The propellant supply device principle diagram in the prior art. DETAILED DESCRIPTION

[0019] The application will be described in detail below with reference to specific embodiments. The following embodiments will help those skilled in the art to further understand the application, but do not limit the application in any form. It should be pointed out that those skilled in the art can make several changes and improvements without departing from the concept of the application. These all belong to the protection scope of the application.

[0020] Example 1 According to the wide adjustment and high reliability Hall electric propulsion system provided by the application, comprising: a gas storage module, a pressure regulation module, a flow regulation module and a Hall thruster; The gas storage module, the pressure regulation module, the flow regulation module and the Hall thruster are connected in sequence; The gas storage module is used for storing the propellant required by the Hall electric propulsion system; The pressure regulation module is used for reducing the high-pressure propellant output by the gas storage module to stable low-pressure propellant meeting the preset requirements through two-stage pressure reduction, so as to provide stable inlet pressure for the flow regulation module; The flow regulation module is used for controlling the flow of the propellant into the cathode and anode of the Hall thruster; The Hall thruster is a thrust executing mechanism of a Hall electric propulsion system. After the propellant entering the Hall thruster is ionized, the propellant is accelerated by an electric field and sprayed at a high speed to provide a thrust for a spacecraft.

[0021] Specifically, the flow adjusting module includes n groups of flow adjusting sub-modules. Each group of the flow adjusting sub-modules includes an anode flow adjusting unit and a cathode flow adjusting unit. The anode flow adjusting unit is configured to control the flow of the propellant entering the anode of the Hall thruster. The cathode flow adjusting unit is configured to control the flow of the propellant entering the cathode of the Hall thruster. The Hall thruster includes n groups of Hall thrusters, and each group of the Hall thrusters includes a first Hall thruster and a second Hall thruster. Any one or more of the n groups of Hall thrusters can work simultaneously. The cathode flow adjusting units are connected to the main and backup cathodes of the first and second Hall thrusters, respectively. The anode flow adjusting units are connected to the anodes of the first and second Hall thrusters, respectively.

[0022] In this embodiment, as shown in Figure 1 The flow adjusting module includes 2 groups of flow adjusting sub-modules, and the Hall thruster includes 2 groups of Hall thrusters. The 4 Hall thrusters of the 2 groups of Hall thrusters can work simultaneously.

[0023] Specifically, the 2 groups of flow adjusting sub-modules include upstream electromagnetic valves SVd5-SVd20 of a flow distributor, downstream electromagnetic valves SV1-1-SV4-4 of the flow distributor, cathode flow distributors J1-J4 and J9-J12, and anode flow distributors J5-J8 and J13-J16.

[0024] The downstream of the flow distributors J1-J4 is connected, the downstream of the flow distributors J5-J8 is connected, the downstream of the flow distributors J9-J12 is connected, and the downstream of the flow distributors J13-J16 is connected.

[0025] The electromagnetic valves SV1-1 and SV1-3 are connected to the main backup cathodes A1 and B1 of the Hall thruster H1 respectively, the electromagnetic valves SV1-2 and SV1-4 are connected to the anode of the Hall thruster H1 in parallel downstream, the electromagnetic valves SV2-1 and SV2-3 are connected to the main backup cathodes A2 and B2 of the Hall thruster H2 respectively, the electromagnetic valves SV2-2 and SV2-4 are connected to the anode of the Hall thruster H2 in parallel downstream, the electromagnetic valves SV3-1 and SV3-3 are connected to the main backup cathodes A3 and B3 of the Hall thruster H3 respectively, the electromagnetic valves SV3-2 and SV3-4 are connected to the anode of the Hall thruster H3 in parallel downstream, the electromagnetic valves SV4-1 and SV4-3 are connected to the main backup cathodes A4 and B4 of the Hall thruster H4 respectively, and the electromagnetic valves SV4-2 and SV4-4 are connected to the anode of the Hall thruster H4 in parallel downstream.

[0026] The cathode flow distributors J1 to J4 are backup to each other, and any one to four of the cathode flow distributors J1 to J4 can be selected to supply any one to two of the main backup cathodes A1, A4, B1 and B4 of the Hall thrusters H1 and H4, and any one of the cathode flow distributors J1 to J4 can be selected as a cathode rated flow supply. When the thruster cathode rated flow is connected, the corresponding upstream and downstream electromagnetic valves are opened. When the cathode ignition fails, the thruster cathode increases the flow supply, at this time, any one to four of the cathode flow distributors J1 to J4 can be selected as a cathode large flow set value, and the corresponding upstream and downstream electromagnetic valves are opened. For example, when the thruster 1 cathode flow is configured, the J1 flow distributor can be selected as the thruster 1 cathode rated flow supply. The thruster 1 cathode large flow set value has the following options: “J1+J2 combination”, “J2+J3 combination”, “J3+J4 combination”, “J1+J2+J3 combination”, “J2+J3+J4 combination”, “J1+J2+J4 combination”, and “J1+J2+J3+J4 combination”. When the corresponding flow distributor combination is selected, the corresponding upstream and downstream electromagnetic valves are opened and closed. Whether to restore to the thruster cathode rated flow and open the corresponding upstream and downstream electromagnetic valves of the cathode flow distributor or not can be selected, and the corresponding electromagnetic valves of the cathode large flow mode are closed. Similarly, the Hall thrusters H2 and H3 also have the above functions.

[0027] J5-J8 anode flow distributors are backup for each other, and any one of 1-4 paths can be selected to supply the Hall thruster H1 and H4 with any one of 1-2 anodes. Assuming that the J5-J8 anode flow distributors provide the same flow, any selection of one path in the J5-J8 anode flow distributors provides equal thrust level. In addition to the rated anode flow supply, the thruster 1 anode flow combination has the following options: "J5+J6 combination", "J5+J6+J7 combination", "J5+J6+J7+J8 combination", each of the above anode flow combinations corresponds to different thrust level. If there is a step setting for the flow resistance provided by the J5-J8 anode flow distributors, the thruster has a larger adjustment range. By analogy, the Hall thruster H2 and H3 flow adjustment module also has the above functions. Different combinations of the 4-path flow distributor can realize the change of the Hall thruster anode inlet flow, so as to realize the adjustment of the Hall thruster thrust size.

[0028] Specifically, when the primary backup cathode top small hole of the first Hall thruster and the primary backup cathode top small hole of the second Hall thruster have a blockage failure, the optional 4-path cathode flow distributor can be selected to flush the Hall thruster cathode.

[0029] Specifically, when any one of the cathode flow adjustment unit or the anode flow adjustment unit has a blockage failure, the flow distributor with the blockage failure is isolated, and the remaining flow distributors of the cathode flow adjustment unit or the anode flow adjustment unit are designated as flow supply.

[0030] Specifically, the anode flow is set by the valve switching path number, so as to realize thrust adjustment; for example, when the H1 thruster is working, J5 gas supply or J5+J6 can be selected; under certain conditions, the thrust and the flow are in a proportional relationship. Assuming that J5 and J6 provide the same flow, the flow is twice the former, and by analogy, it can also be J5+J6+J7.

[0031] According to the wide adjustment and high reliability Hall electric propulsion system control method provided by the application, the following steps are performed based on the wide adjustment and high reliability Hall electric propulsion system as described above: Figure 2 As shown in the figure, the following steps are performed based on the wide adjustment and high reliability Hall electric propulsion system as described above: Step 1: Before the Hall electric propulsion system is ignited, the working thruster is designated, the thrust value F0 / F1 / F2 is set, and the waiting time T1 / T2 is set; wherein the thrust setting value F0 corresponds to the thruster anode flow Y0, the thrust setting value F1 corresponds to the thruster anode flow Y1, and the thrust setting value F2 corresponds to the thruster anode flow Y2, and the thruster cathode ignition process is entered in step 2; Step 2: the thruster cathode is supplied with gas at the rated flow rate, the thruster cathode ignition process is started, if the cathode ignition is successful, step 3 is entered, if the cathode ignition fails, the valve opening path is increased to increase the cathode flow rate according to the cathode large flow rate setting value, and the cathode ignition is re-judged, if successful, step 3 is entered, if the large flow rate ignition measure has been taken and the ignition is still unsuccessful and the cathode ignition timeout has been reached, the ignition program is exited; Step 3: the thruster cathode gas supply can be optionally restored to the normal flow rate, specifically, the corresponding valve is closed according to the normal cathode flow rate or the cathode large flow rate setting is kept unchanged, and step 4 is entered; Step 4: the thruster anode gas supply can be optionally started at a low flow rate, if the thruster anode is started at a low flow rate, step 5 is entered, if the thruster anode is not started at a low flow rate, step 6 is entered; Step 5: the valve opening path is configured according to the anode low flow rate setting value, and step 7 is entered; Step 6: the thruster anode flow rate Y0 is set, the valve opening path is configured according to the thrust setting value F0, and step 7 is entered; Step 7: the thruster anode ignition process is started, if the anode ignition is successful, step 8 is entered; Step 8: according to the on-orbit task requirement, it is selected whether the thruster anode gas supply flow rate is restored to Y0, the valve opening path is configured according to the thrust setting value F0, and step 9 is entered; Step 9: whether the thrust is adjusted, if yes, step 10 is entered, if no, step 11 is entered; Step 10: T1 time length is waited, the thruster anode flow rate Y1 is set, the valve opening path is configured according to the thrust setting value F1, T2 time length is waited, whether the thruster anode flow rate Y2 is set is selected, the valve opening path is configured according to the thrust setting value F2, whether the setting is selected is selected, and step 10 is entered; Step 11: the on-orbit control countdown is waited to end, and the program is ended.

[0032] Those skilled in the art know that, in addition to implementing the system, device and each module thereof provided by the present application in the form of pure computer readable program code, the same program can also be implemented by logically programming the method steps in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers and embedded microcontrollers. Therefore, the system, device and each module thereof provided by the present application can be considered as a hardware component, and the modules included therein for implementing various programs can also be considered as structures in the hardware component; the modules for implementing various functions can also be considered as both software programs for implementing methods and structures in the hardware component.

[0033] The specific embodiments of the present application are described above. It needs to be understood that the present application is not limited to the specific embodiments described above, and various changes or modifications can be made by those skilled in the art within the scope of the claims, which does not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be combined with each other at will without conflict.

Claims

1. A wide regulation high reliability Hall electric propulsion system, characterized in that, The application relates to a Hall electric propulsion system. The Hall electric propulsion system comprises a gas storage module, a pressure regulating module, a flow regulating module and a Hall thruster. The gas storage module, the pressure regulating module, the flow regulating module and the Hall thruster are sequentially connected. The gas storage module is used for storing propellant required by the Hall electric propulsion system. The pressure regulating module is used for reducing high-pressure propellant output by the gas storage module into stable low-pressure propellant meeting preset requirements through two-stage pressure reduction, so as to provide stable inlet pressure for the flow regulating module. The flow regulating module is used for controlling the flow of propellant into the cathode and the anode of the Hall thruster. The Hall thruster is a thrust execution mechanism of the Hall electric propulsion system, and the propellant entering the Hall thruster is ionized, accelerated by an electric field and sprayed at high speed, so as to provide thrust for a spacecraft.

2. The wide-adjustment high-reliability Hall electric propulsion system according to claim 1, characterized in that, The flow regulating module comprises n groups of flow regulating submodules. Each group of the flow regulating submodules comprises an anode flow regulating unit and a cathode flow regulating unit. The anode flow regulating unit is used for controlling the flow of propellant into the anode of the Hall thruster. The cathode flow regulating unit is used for controlling the flow of propellant into the cathode of the Hall thruster. The Hall thruster comprises n groups of Hall thrusters, each group of the Hall thrusters comprises a first Hall thruster and a second Hall thruster, and any one or more of the n groups of Hall thrusters can work simultaneously. The cathode flow regulating unit is connected with the main backup cathodes of the first Hall thruster and the second Hall thruster. The anode flow regulating unit is connected with the anodes of the first Hall thruster and the second Hall thruster.

3. The wide-adjustment high-reliability Hall electric propulsion system according to claim 2, characterized in that, The cathode flow regulating unit comprises downstream electromagnetic valves SVd5-SVd8 of a flow distributor, flow distributors J1-J4, downstream electromagnetic valves SV1-1, SV1-3, SV4-1, SV4-3 of the flow distributor. The anode flow regulating unit comprises downstream electromagnetic valves SVd9-SVd12 of a flow distributor, flow distributors J5-J8, downstream electromagnetic valves SV1-2, SV1-4, SV4-2, SV4-4 of the flow distributor. The downstream electromagnetic valves SV1-1, SV1-3 of the flow distributor are connected with the main backup cathodes A1, B1 of the first Hall thruster, and the downstream electromagnetic valves SV1-2, SV1-4 of the flow distributor are connected with the anode of the first Hall thruster after being connected in parallel downstream. The downstream electromagnetic valves SV4-1, SV4-3 of the flow distributor are connected with the main backup cathodes A4, B4 of the second Hall thruster, and the downstream electromagnetic valves SV4-2, SV4-4 of the flow distributor are connected with the anode of the second Hall thruster after being connected in parallel downstream.

4. The wide-adjustment high-reliability Hall electric propulsion system according to claim 3, characterized in that, The flow distributors J1-J4 in the cathode flow regulating unit are backup for each other, and any 1-4 paths can be selected to supply any 1-2 paths of the main backup cathodes A1, A4, B1, B4 of the first Hall thruster and the second Hall thruster.

5. The wide-adjustment high-reliability Hall electric propulsion system according to claim 3, characterized in that, The flow distributors J5-J8 in the anode flow regulating unit are backup for each other, and any 1-4 paths can be selected to supply any 1-2 paths of the anodes of the first Hall thruster and the second Hall thruster.

6. The wide-adjustment, high-reliability Hall electric propulsion system according to claim 2, characterized in that, When the primary backup cathode top orifice of the first Hall thruster and the primary backup cathode top orifice of the second Hall thruster are blocked, the optional 4-way cathode flow distributor flushes the Hall thruster cathode.

7. The wide-adjustment, high-reliability Hall electric propulsion system of claim 1, wherein, When any one of the cathode flow regulating unit or the anode flow regulating unit is blocked, the blocked flow distributor is isolated, and the remaining flow distributors of the cathode flow regulating unit or the anode flow regulating unit are designated as flow suppliers.

8. The wide-adjustment, high-reliability Hall electric propulsion system according to claim 3, characterized in that, The anode flow is set by the number of valve switching paths, thereby realizing thrust regulation.

9. A method of controlling a wide-regulation high-reliability Hall electric propulsion system, characterized in that, The wide-regulation high-reliability Hall electric propulsion system based on any one of claims 1 to 8 performs the following steps: Step S1: Before the Hall electric propulsion system is ignited, the working Hall thruster is designated, and the thrust value of the designated working Hall thruster is set respectively. Step S2: The Hall electric propulsion system thruster cathode ignition process is triggered, the Hall thruster cathode gas supply is started, the Hall thruster cathode is ignited, if the Hall thruster cathode ignition fails, the valve opening path is configured according to the cathode large flow setting value to increase the cathode flow supply, if the cathode ignition is successful, it is judged whether the current Hall thruster cathode gas supply is restored to the rated flow. If the cathode ignition fails and has timed out, the ignition program is exited. Step S3: The Hall electric propulsion system thruster anode ignition process is triggered, the Hall thruster anode gas supply is started, the Hall thruster anode is ignited, and the program is ended until the end of the orbit control countdown.

10. The method of claim 9, wherein, The step S3 includes: During the Hall thruster anode gas supply process, it is judged whether the current Hall thruster anode gas supply is selected to start with low flow, if the Hall thruster anode is selected to start with low flow, the valve opening path is configured according to the anode low flow setting value, if the thruster anode is not selected to start with low flow, the Hall thruster anode flow Y0 is set, the valve opening path is configured according to the corresponding thrust setting value F0, the Hall thruster anode ignition is started, if the anode ignition is successful, according to the task demand, it is judged whether the anode gas supply flow is restored to Y0. According to the task demand, it is judged whether the thrust is regulated, if yes, the phased adjustment is performed according to the demand.

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