CN113202708A - Ionic electric propulsion system and working method under full life cycle - Google Patents
Ionic electric propulsion system and working method under full life cycle Download PDFInfo
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- CN113202708A CN113202708A CN202110531381.6A CN202110531381A CN113202708A CN 113202708 A CN113202708 A CN 113202708A CN 202110531381 A CN202110531381 A CN 202110531381A CN 113202708 A CN113202708 A CN 113202708A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
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- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0087—Electro-dynamic thrusters, e.g. pulsed plasma thrusters
Abstract
The invention belongs to the technical field of spacecraft propulsion, and particularly discloses an ionic electric propulsion system and a working method under a full life cycle, wherein the system comprises a control unit, a power supply processing unit, a storage and supply unit and an ion thruster, and the control unit is used for determining an optimal working mode of the ion thruster; acquiring an electrical parameter and a flow rate parameter in the current state, comparing the electrical parameter and the flow rate parameter with an optimal working parameter in an optimal working mode, and if the electrical parameter and the flow rate parameter do not reach the optimal working parameter, generating control information and sending the control information to the power supply processing unit and the storage and supply unit; the power supply processing unit supplies power to the ion thruster; the storage and supply unit supplies air to the ion thruster. The invention realizes that the ion thruster works in the optimal working mode all the time in the whole life cycle, and each working parameter in the working mode is optimal, thereby realizing the autonomous operation of the multi-mode electric propulsion system in the deep space exploration field, and further ensuring that the exploration task taking the ion electric propulsion system as main propulsion is successfully completed.
Description
Technical Field
The invention relates to the technical field of spacecraft propulsion, in particular to an ionic electric propulsion system and a working method under a full life cycle.
Background
Electric propulsion technology has been widely used in various application fields of space as an advanced space propulsion technology. Particularly in a deep space exploration task, the electric propulsion technology has the characteristics of high specific impulse, long service life and the like, can greatly save the carrying amount of the propellant, increases the effective load proportion of the spacecraft, and has strong advantages.
In a deep space exploration task, the solar energy efficiency is continuously reduced along with the increase of the distance between the spacecraft and the sun, so that the electric propulsion system is required to have the capability of automatically selecting a working mode according to the electric energy provided by the spacecraft and the design of the spacecraft orbit. In addition, as the working time of the electric propulsion system increases, the critical design size of the ion thruster changes due to long-term ion sputtering abrasion, and the working power of the thruster is smaller and smaller along with the increase of the working time in a general deep space detection task, the working parameters of the small power point of the ion thruster are more sensitive to the critical design size of the ion thruster, and the optimal working parameters designed at the initial stage of the ion thruster are not suitable any more due to sputtering abrasion, so that the electric propulsion system is required to have the capability of completing optimal parameter self-matching according to the sensitive parameters in the whole life cycle, and long-term service is realized.
Disclosure of Invention
The invention aims to provide an ionic electric propulsion system and a working method under a full life cycle, aiming at the problems of output power change caused by too long distance change of a spacecraft and optimal working parameter change caused by long-term working abrasion of an ionic thruster in a deep space exploration task mainly propelled by the ionic electric propulsion system.
The invention discloses an ionic electric propulsion system, which comprises a control unit, a power supply processing unit, a storage and supply unit and an ionic thruster, wherein:
the control unit is connected with the power supply processing unit and the storage and supply unit and is used for determining the optimal working mode of the ion thruster according to the electric parameters of the power supply processing unit; and generating control information according to the optimal working mode and sending the control information to the power supply processing unit and the storage and supply unit; and obtaining the electrical parameter and the flow rate parameter in the current state, comparing the electrical parameter and the flow rate parameter with the optimal working parameter in the optimal working mode, and if the electrical parameter and the flow rate parameter do not reach the optimal working parameter, generating control information and sending the control information to the power supply processing unit and the storage and supply unit;
the power supply processing unit is connected with the ion thruster, adjusts the electrical parameters of the ion thruster through control information and supplies power to the ion thruster;
the storage and supply unit is connected with the ion thruster, adjusts the flow rate parameter of the ion thruster through control information and supplies air to the ion thruster;
the ion thruster is connected with the power supply processing unit and the storage and supply unit, and the working parameters of the system reach the optimal working parameters by the power supply of the power supply processing unit and the air supply of the storage and supply unit to reach the optimal working mode.
Further, the power supply processing unit comprises a cathode touch power supply, a cathode ignition power supply, a cathode heating power supply, an anode power supply, a screen grid power supply, an acceleration power supply, a neutralizer touch power supply, a neutralizer ignition power supply and a neutralizer heating power supply.
Further, the storage and supply unit comprises a xenon cylinder, a pressure regulating module and a flow regulating module, wherein the pressure regulating module and the flow regulating module are arranged on a pipeline for supplying gas to the ion thruster from the xenon cylinder; the pressure adjusting module and the flow adjusting module are both connected with the control unit.
The invention discloses a working method of an ionic electric propulsion system under a full life cycle, which comprises the following steps:
s1: the control unit acquires the input power of the electric propulsion system and determines the optimal working mode of the ion thruster according to the input power of the electric propulsion system;
s2: the control unit generates corresponding control information according to the optimal working mode and sends the control information to the power supply processing unit and the storage and supply unit;
s3: the power supply processing unit adjusts the electrical parameters of the ion thruster through the control information and supplies power to the ion thruster;
s4: the storage and supply unit adjusts the flow rate parameters of the ion thruster through the control information and supplies air to the ion thruster;
s5: the ion thruster works for a set time length under the current working parameters;
s6: the control unit obtains the electrical parameter and the flow rate parameter in the current state, and compares the electrical parameter and the flow rate parameter with the optimal working parameter in the optimal working mode, if the electrical parameter and the flow rate parameter do not reach the optimal working parameter, the steps S2 to S6 are executed, and if the electrical parameter and the flow rate parameter both reach the optimal working parameter, the ion thruster continues to work under the current working parameter.
Further, the control unit determines an optimal operation mode of the ion thruster according to the input power of the electric propulsion system in step S1, including:
the control unit calculates the input power of the ion thruster according to an input power-efficiency curve of the electric propulsion system;
determining an optional working mode of the ion thruster under the current input power according to a preset ion thruster power-power working mode comparison table and the input power of the ion thruster;
and selecting the optimal working mode from the selectable working modes according to the requirement relation of the spacecraft orbit design on the thrust and the specific impulse at the current position.
Further, in S2, the control unit generates corresponding control information according to the optimal operation mode and sends the control information to the power processing unit and the storage and supply unit, including:
the control unit acquires electrical parameters of a cathode touch power supply, a cathode ignition power supply, a cathode heating power supply, an anode power supply, a screen grid power supply, an acceleration power supply, a neutralizer touch power supply, a neutralizer ignition power supply and a neutralizer heating power supply in the power supply processing unit, acquires flow rate parameters of a pressure adjusting module and a flow adjusting module in the storage and supply unit, and compares the electrical parameters and the flow rate parameters with optimal working parameters in an optimal working mode;
matching corresponding working parameters for a cathode touch power supply, a cathode ignition power supply, a cathode heating power supply, an anode power supply, a screen grid power supply, an acceleration power supply, a neutralizer touch power supply, a neutralizer ignition power supply, a neutralizer heating power supply, a pressure adjusting module and a flow adjusting module according to the comparison result and a preset optimal parameter matching strategy;
and generating corresponding control information according to the working parameters.
Further, the optimal parameter matching strategy comprises:
judging whether electron reflux occurs due to grid abrasion or not according to 20% reduction of discharge loss compared with an initial state, or neutralization device arc blowout immediately after a screen grid power supply and an acceleration power supply are started, or beam restarting or protection shutdown caused by a phenomenon different from ignition of a power supply processing unit; if any one of the above phenomena exists, the voltage of the acceleration power supply is continuously reduced by a set step length until no electron backflow phenomenon exists;
judging whether the cathode works in a pinnate mode under the original design value of the cathode flow rate or not due to the abrasion of the cathode small hole according to the main electric shock voltage value; if yes, increasing the cathode flow rate by a set step length until the voltage of the cathode touch voltage meets the optimal working parameters;
judging whether the anode voltage is increased or not due to the increase of the neutral gas loss rate caused by the abrasion of the grid electrode according to the anode voltage and is higher than a required value; if so, calculating to obtain the anode flow rate to be increased according to the absolute value of the sensitivity of the anode voltage to the anode flow rate divided by the anode voltage increment;
judging whether the neutralizer works in a pinnate mode under the original design value of the flow rate of the neutralizer due to abrasion of the small hole of the neutralizer or according to the contact voltage of the neutralizer or the suspension potential of the thruster relative to the spacecraft; if so, the neutralizer flow rate is increased by setting step sizes until the neutralizer holding voltage meets the optimal operating parameters.
Further, the power supply processing unit has continuous adjustment capacity for the electrical parameters; the storage and supply unit has a wide range of continuous or gear adjustment capability for the flow rate parameters.
The ionic electric propulsion system and the working method under the full life cycle realize that the ionic thruster works in the optimal working mode all the time within the full life cycle, and each working parameter under the working mode is optimal, realize that the multi-mode electric propulsion system autonomously operates in the deep space exploration field, maximize the service life and the reliability of the multi-mode electric propulsion system, and further ensure that the detection task taking the ionic electric propulsion system as main propulsion is successfully completed.
Drawings
FIG. 1 is a structural assembly diagram of an ionic electric propulsion system in accordance with an embodiment of the present invention;
FIG. 2 is a flowchart illustrating steps of a method for operating an ion electric propulsion system according to an embodiment of the present invention during a full life cycle.
FIG. 3 is a flowchart illustrating another step of a method for operating an ion electric propulsion system according to an embodiment of the present invention during a full life cycle.
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
An embodiment of the present invention is an ion electric propulsion system, as shown in fig. 1, the ion electric propulsion system includes a control unit, a power supply processing unit, a storage and supply unit, and an ion thruster, wherein: the control unit is connected with the power supply processing unit and the storage and supply unit and is used for determining the optimal working mode of the ion thruster according to the electric parameters of the power supply processing unit; and generating control information according to the optimal working mode and sending the control information to the power supply processing unit and the storage and supply unit; and obtaining the electrical parameter and the flow rate parameter in the current state, comparing the electrical parameter and the flow rate parameter with the optimal working parameter in the optimal working mode, and if the electrical parameter and the flow rate parameter do not reach the optimal working parameter, generating control information and sending the control information to the power supply processing unit and the storage and supply unit; the power supply processing unit is connected with the ion thruster, adjusts the electrical parameters of the ion thruster through control information and supplies power to the ion thruster; the storage and supply unit is connected with the ion thruster, adjusts the flow rate parameter of the ion thruster through control information and supplies air to the ion thruster; the ion thruster is connected with the power supply processing unit and the storage and supply unit, and the optimal working mode is achieved through power supply of the power supply processing unit and air supply of the storage and supply unit, so that the working parameters of the ion thruster reach the optimal working parameters.
As shown in fig. 1, the power supply processing unit includes a cathode touch power supply, a cathode ignition power supply, a cathode heating power supply, an anode power supply, a screen grid power supply, an acceleration power supply, a neutralizer touch power supply, a neutralizer ignition power supply, and a neutralizer heating power supply. The storage and supply unit comprises a xenon cylinder, a pressure adjusting module and a flow adjusting module, wherein the pressure adjusting module and the flow adjusting module are arranged on a pipeline for supplying gas to the ion thruster by the xenon cylinder; the pressure adjusting module and the flow adjusting module are both connected with the control unit.
The ionic electric propulsion system has the autonomous control capability, and the control unit samples working parameters of a cathode touch power supply, a cathode ignition power supply, a cathode heating power supply, an anode power supply, a screen grid power supply, an acceleration power supply, a neutralizer touch power supply, a neutralizer ignition power supply and a neutralizer heating power supply and controls the working states of the cathode touch power supply, the cathode ignition power supply, the cathode heating power supply, the anode power supply, the screen grid power supply, the acceleration power supply, the neutralizer touch power supply, the neutralizer ignition power supply and the neutralizer heating power supply. Meanwhile, the control unit samples working parameters of the pressure adjusting module and the flow adjusting module and controls working states of the pressure adjusting module and the flow adjusting module, so that the pressure and the flow of the xenon are adjusted. The embodiment realizes the purpose that the ionic electric propulsion system works in the optimal working mode all the time in the whole life cycle, and each working parameter is optimal in the working mode.
The invention discloses a working method of an ionic electric propulsion system under a full life cycle, which comprises the following steps as shown in figure 2:
s1: the control unit obtains the input power of the electric propulsion system, and determines the optimal working mode of the ion thruster according to the input power of the electric propulsion system.
Specifically, the control unit determines an optimal operation mode of the ion thruster according to the input power of the electric propulsion system in step S1, including:
the control unit calculates the input power of the ion thruster according to an input power-efficiency curve of the electric propulsion system;
determining an optional working mode of the ion thruster under the current input power according to a preset ion thruster power-power working mode comparison table and the input power of the ion thruster;
and selecting the optimal working mode from the selectable working modes according to the requirement relation of the spacecraft orbit design on the thrust and the specific impulse at the current position.
As shown in table 1, an example of an "ion thruster power-power operation mode comparison table" is enumerated.
Table 1 ion thruster power-power working mode comparison table
S2: the control unit generates corresponding control information according to the optimal working mode and sends the control information to the power supply processing unit and the storage and supply unit.
Specifically, the step S2, in which the control unit generates corresponding control information according to the optimal operating mode and sends the control information to the power processing unit and the storage and supply unit, includes:
the control unit acquires electrical parameters of a cathode touch power supply, a cathode ignition power supply, a cathode heating power supply, an anode power supply, a screen grid power supply, an acceleration power supply, a neutralizer touch power supply, a neutralizer ignition power supply and a neutralizer heating power supply in the power supply processing unit, acquires flow rate parameters of a pressure adjusting module and a flow adjusting module in the storage and supply unit, and compares the electrical parameters and the flow rate parameters with optimal working parameters in an optimal working mode;
matching corresponding working parameters for a cathode touch power supply, a cathode ignition power supply, a cathode heating power supply, an anode power supply, a screen grid power supply, an acceleration power supply, a neutralizer touch power supply, a neutralizer ignition power supply, a neutralizer heating power supply, a pressure adjusting module and a flow adjusting module according to the comparison result and a preset optimal parameter matching strategy;
and generating corresponding control information according to the working parameters.
As shown in fig. 3, the optimal parameter matching strategy includes:
judging whether electron reflux occurs due to grid abrasion or not according to 20% reduction of discharge loss compared with an initial state, or neutralization device arc blowout immediately after a screen grid power supply and an acceleration power supply are started, or beam restarting or protection shutdown caused by a phenomenon different from ignition of a power supply processing unit; if any one of the above phenomena exists, the voltage of the acceleration power supply is continuously reduced by a set step length until no electron backflow phenomenon exists;
judging whether the cathode works in a pinnate mode under the original design value of the cathode flow rate or not due to the abrasion of the cathode small hole according to the main electric shock voltage value; if yes, increasing the cathode flow rate by a set step length until the voltage of the cathode touch voltage meets the optimal working parameters;
judging whether the anode voltage is increased or not due to the increase of the neutral gas loss rate caused by the abrasion of the grid electrode according to the anode voltage and is higher than a required value; if so, calculating to obtain the anode flow rate to be increased according to the absolute value of the sensitivity of the anode voltage to the anode flow rate divided by the anode voltage increment;
judging whether the neutralizer works in a pinnate mode under the original design value of the flow rate of the neutralizer due to abrasion of the small hole of the neutralizer or according to the contact voltage of the neutralizer or the suspension potential of the thruster relative to the spacecraft; if so, the neutralizer flow rate is increased by setting step sizes until the neutralizer holding voltage meets the optimal operating parameters.
Specifically, the power supply processing unit has continuous adjustment capability on the electrical parameters; the storage and supply unit has a wide range of continuous or gear adjustment capability for the flow rate parameters.
As shown in table 2 and table 3, an example of the operating parameter requirement table of each operating point of the ion thruster is shown, and an example of the operating parameter sensitivity and adjustment step length table of each operating point of the ion thruster is shown.
Table 2 operating parameter requirement table for each operating point of ion thruster
TABLE 3 sensitivity of working parameters and adjusting step length table for each working point of ion thruster
S3: and the power supply processing unit adjusts the electrical parameters of the ion thruster through the control information and supplies power to the ion thruster.
S4: the storage and supply unit adjusts the flow rate parameters of the ion thruster through control information and supplies air to the ion thruster.
S5: and the ion thruster works in the current parameter mode for a set time length.
S6: the control unit obtains the electrical parameter and the flow rate parameter in the current state, and compares the electrical parameter and the flow rate parameter with the optimal working parameter in the optimal working mode, if the electrical parameter and the flow rate parameter do not reach the optimal working parameter, the steps S2 to S6 are executed, and if the electrical parameter and the flow rate parameter both reach the optimal working parameter, the ion thruster continues to work under the current working parameter.
According to the embodiment of the invention, through the selection of the optimal working mode by the control unit and the closed-loop control mode of sampling, controlling, re-sampling and re-controlling, all the parameters finally reach the optimal working parameters, so that the performance loss of the electronic thruster is minimized.
Before implementation, a plurality of working modes are determined according to an electric propulsion system input power-efficiency curve, an ion thruster power-power working mode comparison table and a spacecraft orbit design, and optimal working parameters are correspondingly arranged in each working mode. Therefore, the method of the invention realizes the matching of the optimal working mode, and then performs the optimized matching on each working parameter so as to ensure that the cathode and the neutralizer work in a point mode, the grid interception current and the discharge voltage are less than the requirements under the condition of the minimum performance loss of the ionic electric propulsion system, thereby maximizing the service life and the reliability of the ion thruster.
The ionic electric propulsion system and the working method under the full life cycle realize that the ionic thruster works in the optimal working mode all the time within the full life cycle, and each working parameter under the working mode is optimal, realize that the multi-mode electric propulsion system autonomously operates in the deep space exploration field, maximize the service life and the reliability of the multi-mode electric propulsion system, and further ensure that the detection task taking the ionic electric propulsion system as main propulsion is successfully completed.
The above description is only a preferred embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (8)
1. An ionic electric propulsion system comprising a control unit, a power supply processing unit, a storage and supply unit, and an ion thruster, wherein:
the control unit is connected with the power supply processing unit and the storage and supply unit and is used for determining the optimal working mode of the ion thruster according to the electrical parameters of the power supply processing unit; and generating control information according to the optimal working mode and sending the control information to the power supply processing unit and the storage and supply unit; and obtaining the electrical parameter and the flow rate parameter in the current state, comparing the electrical parameter and the flow rate parameter with the optimal working parameter in the optimal working mode, and if the electrical parameter and the flow rate parameter do not reach the optimal working parameter, generating control information and sending the control information to the power supply processing unit and the storage and supply unit;
the power supply processing unit is connected with the ion thruster, adjusts the electrical parameters of the ion thruster through the control information and supplies power to the ion thruster;
the storage and supply unit is connected with the ion thruster, adjusts the flow rate parameter of the ion thruster through the control information and supplies air to the ion thruster;
the ion thruster is connected with the power supply processing unit and the storage and supply unit, and the working parameters of the system reach the optimal working parameters by the power supply of the power supply processing unit and the air supply of the storage and supply unit to reach the optimal working mode.
2. The ionic electric propulsion system of claim 1, wherein said power processing unit includes a cathode ignition power source, a cathode heating power source, an anode power source, a screen grid power source, an acceleration power source, a neutralizer ignition power source, and a neutralizer heating power source.
3. The ionic electric propulsion system of claim 1, wherein said storage and supply unit comprises a xenon cylinder and a pressure regulation module and a flow regulation module, said pressure regulation module and said flow regulation module being mounted on a conduit for said xenon cylinder to supply gas to said ion thruster; the pressure adjusting module and the flow adjusting module are both connected with the control unit.
4. A method of operating an ionic electric propulsion system according to any one of claims 1 to 3 over a full life cycle, comprising:
s1: the control unit acquires the input power of the electric propulsion system and determines the optimal working mode of the ion thruster according to the input power of the electric propulsion system;
s2: the control unit generates corresponding control information according to the optimal working mode and sends the control information to the power supply processing unit and the storage and supply unit;
s3: the power supply processing unit adjusts the electrical parameters of the ion thruster through the control information and supplies power to the ion thruster:
s4: the storage and supply unit adjusts the flow rate parameters of the ion thruster through the control information and supplies air to the ion thruster;
s5: the ion thruster works for a set time length under the current working parameters;
s6: the control unit obtains the electrical parameter and the flow rate parameter in the current state, and compares the electrical parameter and the flow rate parameter with the optimal working parameter in the optimal working mode, if the electrical parameter and the flow rate parameter do not reach the optimal working parameter, the steps S2 to S6 are executed, and if the electrical parameter and the flow rate parameter both reach the optimal working parameter, the ion thruster continues to work under the current working parameter.
5. The method of operating an ionic electric propulsion system under a full life cycle as claimed in claim 4, wherein the step S1 the control unit determining the optimal operation mode of the ion thruster according to the input power of the electric propulsion system includes:
the control unit calculates the input power of the ion thruster according to an input power-efficiency curve of the electric propulsion system;
determining an optional working mode of the ion thruster under the current input power according to a preset ion thruster power-power working mode comparison table and the input power of the ion thruster;
and selecting the optimal working mode from the selectable working modes according to the requirement relation of the spacecraft orbit design on the thrust and the specific impulse at the current position.
6. The method of operation of an ion electric propulsion system over a life cycle of claim 4, wherein the step S2 of the control unit generating corresponding control information according to the optimal operation mode and sending the control information to the power processing unit and the storage and supply unit includes:
the control unit acquires electrical parameters of a cathode touch power supply, a cathode ignition power supply, a cathode heating power supply, an anode power supply, a screen grid power supply, an acceleration power supply, a neutralizer touch power supply, a neutralizer ignition power supply and a neutralizer heating power supply in the power supply processing unit, acquires flow rate parameters of a pressure adjusting module and a flow adjusting module in the storage and supply unit, and compares the electrical parameters and the flow rate parameters with optimal working parameters in an optimal working mode;
matching corresponding working parameters for a cathode touch power supply, a cathode ignition power supply, a cathode heating power supply, an anode power supply, a screen grid power supply, an acceleration power supply, a neutralizer touch power supply, a neutralizer ignition power supply, a neutralizer heating power supply, a pressure adjusting module and a flow adjusting module according to the comparison result and a preset optimal parameter matching strategy;
and generating corresponding control information according to the working parameters.
7. The method of operation of an ionic electric propulsion system over a full life cycle of claim 6, wherein the optimal parameter matching strategy comprises:
judging whether electron reflux occurs due to grid abrasion or not according to 20% reduction of discharge loss compared with an initial state, or neutralization device arc blowout immediately after a screen grid power supply and an acceleration power supply are started, or beam restarting or protection shutdown caused by a phenomenon different from ignition of a power supply processing unit; if any one of the above phenomena exists, the voltage of the acceleration power supply is continuously reduced by a set step length until no electron backflow phenomenon exists;
judging whether the cathode works in a pinnate mode under the original design value of the cathode flow rate or not due to the abrasion of the cathode small hole according to the main electric shock voltage value; if yes, increasing the cathode flow rate by a set step length until the voltage of the cathode touch power supply meets the optimal working parameters;
judging whether the anode voltage is increased or not due to the increase of the neutral gas loss rate caused by the abrasion of the grid electrode according to the anode voltage and is higher than a required value; if so, calculating to obtain the anode flow rate to be increased according to the absolute value of the sensitivity of the anode voltage to the anode flow rate divided by the anode voltage increment;
judging whether the neutralizer works in a pinnate mode under the original design value of the flow rate of the neutralizer due to abrasion of the small hole of the neutralizer or according to the contact voltage of the neutralizer or the suspension potential of the thruster relative to the spacecraft; if so, the neutralizer flow rate is increased by setting step sizes until the neutralizer holding voltage meets the optimal operating parameters.
8. The method of claim 7, wherein said power processing unit is capable of continuous adjustment of electrical parameters; the storage and supply unit has a wide range of continuous or gear adjustment capability for flow rate parameters.
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