CN112268704A - Device and method for combined measurement of thrust flow and current of electric thruster - Google Patents
Device and method for combined measurement of thrust flow and current of electric thruster Download PDFInfo
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- CN112268704A CN112268704A CN202011093250.6A CN202011093250A CN112268704A CN 112268704 A CN112268704 A CN 112268704A CN 202011093250 A CN202011093250 A CN 202011093250A CN 112268704 A CN112268704 A CN 112268704A
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- shielding plate
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
- G01F1/00—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow
- G01F1/76—Devices for measuring mass flow of a fluid or a fluent solid material
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/0028—Force sensors associated with force applying means
- G01L5/0038—Force sensors associated with force applying means applying a pushing force
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R19/00—Arrangements for measuring currents or voltages or for indicating presence or sign thereof
- G01R19/0046—Arrangements for measuring currents or voltages or for indicating presence or sign thereof characterised by a specific application or detail not covered by any other subgroup of G01R19/00
- G01R19/0061—Measuring currents of particle-beams, currents from electron multipliers, photocurrents, ion currents; Measuring in plasmas
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- Testing Relating To Insulation (AREA)
- Tests Of Circuit Breakers, Generators, And Electric Motors (AREA)
Abstract
The invention provides a thrust flow current combined measurement device and method of an electric thruster, and the device comprises an electronic balance, a lower shielding plate, a balance weighing disc, a thrust table, side shielding plates, a front shielding plate, a charge collection plate and a lifting support, wherein the center of the lower shielding plate is provided with a lower shielding plate center hole, a thrust table support leg is arranged below the thrust table, a lifting support channel is arranged at the rear of each side shielding plate, the lower shielding plate is placed above the electronic balance, the balance weighing disc is connected with the electronic balance through the lower shielding plate center hole, each side shielding plate is of a three-surface structure and forms a four-surface closed body together with the front shielding plate, the charge collection plate is connected with the side shielding plates through an insulating connector, and the lifting support is connected with a lifter through the lifting support channel. The invention realizes that the thrust, the flow and the current of the electric thruster are measured simultaneously on the premise of not damaging a vacuum test environment, and the flow error caused by natural mass volatilization of the electric thruster in vacuum can be corrected. The invention simplifies the performance test flow of the electric thruster, reduces the test difficulty and improves the test accuracy.
Description
Technical Field
The invention belongs to the field of aerospace propulsion, and relates to a device and a method for jointly measuring thrust flow and current of an electric thruster.
Background
An electric thruster for generating thrust through charged particle beams is a thruster commonly used in the field of aerospace propulsion, has excellent propulsion performance, and is widely used for spacecraft orbit maneuvering, attitude control and the like. The thruster has the characteristics of small thrust magnitude, small mass flow of the propellant, high specific impulse and the like. The specific impulse refers to the impulse generated by the propellant in unit weight, is a parameter for measuring the propelling performance and the weight of the electric thruster, and can be calculated by measuring the mass flow and the propelling force of the propellant. The current is a weight parameter for power measurement in the operation of the electric thruster. Multiple performance parameters of the electric thruster need to depend on the measurement of the thrust, the flow and the current, and even the simultaneous measurement results of the three are required. In summary, the measurement of the thrust, flow and current of the electric thruster is an inevitable requirement for evaluating the performance of the electric thruster.
As for the electric thruster, the thrust and the flow are very small, and the test is difficult. The test of electric thruster usually needs to be carried out under vacuum environment, in the prior art, the thrust, flow and electric current of electric thruster often can only be measured respectively, and test equipment is complicated, and the flow is loaded down with trivial details, the difficult operation. For example, the measurement of the thrust of the electric thruster is usually performed through torsion pendulum or the like, the operation such as system counterweight is required, the measurement is sensitive to the test environment and the operation, and the flow cannot be measured while the thrust is measured. Therefore, for the specific impulse performance, the vacuum environment is often required to be relieved, and the mass change of the electric thruster before and after the work is weighed to calculate the flow during the work, so as to calculate the specific impulse of the electric thruster. The method not only needs to destroy the vacuum environment, wastes time and labor, but also cannot count the natural volatilization mass of the system in the working process of the electric thruster, so that the flow numerical value is higher and the specific impulse calculation is inaccurate. The invention provides a device and a method for jointly measuring thrust, flow and current of an electric thruster, which can simultaneously measure the thrust, flow and current of the electric thruster, simplify a test process and improve test accuracy.
Disclosure of Invention
Technical problem to be solved
The invention provides a device and a method for jointly measuring thrust flow and current of an electric thruster, and aims to solve the problems that the thrust, the flow and the current of the electric thruster are difficult to simultaneously measure and the flow test of the electric thruster is inaccurate. The invention can realize the simultaneous measurement of three key quantities of thrust, flow and current, wherein the flow is a time average result and the natural mass volatilization of the electric thruster in vacuum is considered, thereby simplifying the test process of the electric thruster, improving the test precision of the electric thruster and obtaining the simultaneous measurement results of the thrust, the flow and the current.
Technical scheme
A thrust flow current combined measuring device of an electric thruster comprises an electronic balance (1), a lower shielding plate (2), a balance weighing disc (4), a thrust platform (5), side shielding plates (7), a front shielding plate (9), a charge collecting plate (11) and a lifting support (12), wherein a lower shielding plate center hole (3) is formed in the center of the lower shielding plate (2), thrust platform support legs (6) are arranged below the thrust platform (5), and a lifting support channel (8) is formed in the rear of each side shielding plate (7);
the lower shielding plate (2) is placed above the electronic balance (1), and the balance weighing disc (4) is connected with the electronic balance (1) through the lower shielding plate central hole (3);
wherein, the side shielding plate (7) is a three-surface structure and forms a four-surface closed body together with the front shielding plate (9);
wherein the charge collection plate (11) is connected with the side shielding plate (7) through an insulating connector (10);
wherein the lifting support (12) is connected with the lifter (13) through a lifting support channel (8).
In a preferred embodiment of the present invention, the lower shield plate (2) is made of a conductive material, the side shield plates (7) are made of a conductive material, the front shield plate (9) is made of a conductive material, the insulating connector (10) is made of an insulating material, and the charge collecting plate (11) is made of a conductive material.
In a preferable scheme of the invention, the lifting support (12) is placed below the thrust platform (5), the lifting support (12) is driven by the lifter (13) to move up and down, the upper limit of the stroke of the lifting support (12) is enough to separate the thrust platform (5) from the balance weighing plate (4), and the lower limit of the stroke of the lifting support (12) is enough to separate the thrust platform (5) from the lifting support (12).
As a preferred aspect of the present invention, the insulating connector (10) may be, but is not limited to, an insulating rope, a bolt, a bracket, a boss, a groove.
As a preferable scheme of the invention, the lower shielding plate (2), the side shielding plate (7) and the front shielding plate (9) are connected with a ground potential, and the charge collecting plate (11) is connected with a micro-nano current measuring instrument.
As a preferred embodiment of the invention, the electronic balance (1) has an internal calibration function.
As a preferable scheme of the invention, the tested electric thruster generates thrust through the charged particle beam, is placed on the surface of the thrust table (5), and the charged particle beam generated by the electric thruster is sprayed to the charge collecting plate (11).
The technical scheme also provides a using method of the electric thruster thrust flow current combined measuring device, the electric thruster thrust flow current combined measuring device is adopted, and the method comprises the following steps:
s1, adjusting the level of the electronic balance: adjusting a horizontal state adjuster of the electronic balance through the level gauge to enable the electronic balance to be in a horizontal state;
s2, mounting the electric thruster to be tested: placing an electric thruster which can generate charged particle beams and generates thrust through the charged particle beams on the surface of a thrust table (5), placing the thrust table (5) on the surface of a balance weighing disc (4), wherein the charged particle beams generated by the electric thruster are configured to be sprayed to a charge collecting plate (11), connecting the electric thruster with all equipment required by the normal work of the electric thruster, and configuring the working environment to a state required by the electric thruster;
s3, calibrating the electronic balance: adjusting the height of the lifting support (12), so that the thrust platform (5) is separated from the balance weighing disc (4) to start the internal calibration function of the electronic balance (1), and completing the calibration of the electronic balance;
s4, resetting the thrust table: adjusting the height of the lifting support (12), enabling the thrust platform (5) to be separated from the lifting support (12) and enabling the thrust platform (5) to be placed on the surface of the balance weighing disc (4), and recording the reading M0 of the electronic balance (1);
s5, measuring system drift: keeping the electronic balance (1) in a working state for a period of time T1, and recording the reading M1 of the electronic balance;
s6, collecting working data of the electric thruster: starting the electric thruster, simultaneously recording the current passing through the charge collecting plate (11) and the reading of the electronic balance (1) in real time to obtain a balance reading curve Mt changing along with time, and after the electric thruster works for a period of time T2, closing the electric thruster and recording the reading M2 of the electronic balance;
s7, measuring system drift: keeping the electronic balance (1) in a working state for a period of time T1, and recording the reading M3 of the electronic balance;
s8, repeating the steps S3-S7 for a plurality of times until the expected test is completely finished, turning off the electric thruster, turning off all equipment required by the work of the electric thruster, and turning off the electronic balance (1);
s9, data processing: the current data can be directly read and recorded by a micro-nano current measuring instrument, the flow data can be obtained by a formula (M2-M1)/T2-0.5 (M0-M1+ M2-M3)/T1, and the thrust can be obtained by subtracting the lower envelope curve of the Mt curve from the Mt curve.
Advantageous effects
The invention at least comprises the following beneficial effects:
firstly, the electronic balance, the omnibearing shielding structure and the charge collection structure are designed in a combined mode, so that the thrust, the flow and the current of the electric thruster can be measured simultaneously, the performance test flow of the electric thruster is simplified, and the test difficulty is reduced.
Secondly, the support capable of moving up and down is arranged below the thrust table, so that the thrust table and the electric thruster on the thrust table can be separated from the balance to be in contact with the balance under the condition of not damaging a vacuum environment, calibration of the electronic balance is achieved, a performance test flow of the electric thruster is simplified, and test efficiency is improved.
Thirdly, the invention can be used for measuring the natural mass volatilization of the system by respectively measuring the system mass for a period of time before and after the electric thruster works, thereby correcting the flow test result, increasing the accuracy of flow data and further improving the accuracy of the performance test of the electric thruster.
Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention.
Drawings
FIG. 1 is a schematic partial cross-sectional view of an axial quarter of a thrust flow current combination measuring device of an electric thruster according to an embodiment of the present invention;
FIG. 2 is a schematic partial cross-sectional view of one half of the shaft side of the thrust flow current combination measuring device of the electric thruster in accordance with one embodiment of the present invention;
FIG. 3 is a schematic axial three-quarter sectional view of a combined thrust flow and current measuring device of an electric thruster according to an embodiment of the present invention;
FIG. 4 is a schematic axial view of a combined thrust flow and current measurement device of an electric thruster in accordance with an embodiment of the present invention;
FIG. 5 is a schematic left side view of a combined thrust flow and current measurement device of an electric thruster according to an embodiment of the present invention;
FIG. 6 is an axial view of a lift platform according to an embodiment of the present invention;
FIG. 7 is an axial view of a thrust table in accordance with an embodiment of the present invention;
FIG. 8 is an isometric cross-sectional view of a thrust stage in accordance with an embodiment of the present invention.
In the figure, (1) an electronic balance, (2) a lower shielding plate, (3) a lower shielding plate center hole, (4) a balance weighing disc, (5) a thrust table, (6) a thrust table support leg, (7) a side shielding plate, (8) a lifting support channel, (9) a front shielding plate, (10) an insulating connector, (11) a charge collecting plate, (12) a lifting support and (13) a lifter.
Detailed Description
The present invention will now be further described with reference to the embodiments and drawings so that those skilled in the art can practice the invention with reference to the description. The following examples are intended to illustrate the invention but are not intended to limit the scope of the invention.
It will be understood that terms such as "having," "including," and "comprising," as used herein, do not preclude the presence or addition of one or more other elements or groups thereof.
Fig. 1 to 8 show an implementation form of a thrust flow current combined measuring device of an electric thruster according to the present invention, which includes:
the device comprises an electronic balance (1), a lower shielding plate (2), a balance weighing disc (4), a thrust platform (5), side shielding plates (7), a front shielding plate (9), a charge collecting plate (11) and a lifting support (12), wherein the center of the lower shielding plate (2) is provided with a lower shielding plate center hole (3), a thrust platform support leg (6) is arranged below the thrust platform (5), and the rear part of each side shielding plate (7) is provided with a lifting support channel (8);
the lower shielding plate (2) is placed above the electronic balance (1), and the balance weighing disc (4) is connected with the electronic balance (1) through the lower shielding plate central hole (3);
the side shielding plate (7) is of a three-panel structure and forms a four-surface closed cylinder together with the front shielding plate (9);
wherein the charge collecting plate (11) is connected with the side shielding plate (7) through an insulating connector (10);
wherein, the lifting bracket (12) is connected with the lifter (13) through the lifting bracket channel (8).
In this embodiment, the lower shielding plate (2) is made of copper foil-clad glass material, the side shielding plate (7) is made of copper foil-clad glass material, the front shielding plate (9) is made of copper foil-clad glass material, the insulating connector (10) is made of nylon flexible thin rope, and the charge collecting plate (11) is made of stainless steel material.
In the embodiment, a lifting support (12) is placed below a thrust platform (5), the lifting support (12) is driven by a lifter (13) to move up and down, the upper limit of the stroke of the lifting support (12) is enough to separate the thrust platform (5) from a balance weighing plate (4), the lower limit of the stroke of the lifting support (12) is enough to separate the thrust platform (5) from the lifting support (12), and the lifter (13) adopts a single-shaft electric lifter.
In the embodiment, the lower shielding plate (2), the side shielding plate (7) and the front shielding plate (9) are connected with the earth potential, and the charge collecting plate (11) is connected with a picoampere meter of the micro-nano current measuring instrument.
In this example, the electronic balance (1) was a semi-microanalysis balance having an internal calibration function.
In this embodiment, the electric thruster under test generates thrust by means of a charged particle beam, the electric thruster is placed on the face of a thrust table (5), and the charged particle beam generated by the electric thruster is ejected towards a charge collection plate (11).
The embodiment also provides a using method of the combined thrust flow and current measuring device of the electric thruster, which adopts the combined thrust flow and current measuring device of the electric thruster as described above, and the method includes the following steps:
s1, adjusting the level of the electronic balance: adjusting a horizontal state adjuster of the electronic balance through the level gauge to enable the electronic balance to be in a horizontal state;
s2, mounting the electric thruster to be tested: placing an electric thruster which can generate charged particle beams and generates thrust through the charged particle beams on the surface of a thrust table (5), placing the thrust table (5) on the surface of a balance weighing disc (4), wherein the charged particle beams generated by the electric thruster are configured to be sprayed to a charge collecting plate (11), connecting the electric thruster with all equipment required by the normal work of the electric thruster, and configuring the working environment to a state required by the electric thruster;
s3, calibrating the electronic balance: adjusting the height of the lifting support (12), so that the thrust platform (5) is separated from the balance weighing disc (4) to start the internal calibration function of the electronic balance (1), and completing the calibration of the electronic balance;
s4, resetting the thrust table: adjusting the height of the lifting support (12), enabling the thrust platform (5) to be separated from the lifting support (12) and enabling the thrust platform (5) to be placed on the surface of the balance weighing disc (4), and recording the reading M0 of the electronic balance (1);
s5, measuring system drift: keeping the electronic balance (1) in a working state for a period of time T1, and recording the reading M1 of the electronic balance;
s6, collecting working data of the electric thruster: starting the electric thruster, simultaneously recording the current passing through the charge collecting plate (11) and the reading of the electronic balance (1) in real time to obtain a balance reading curve Mt changing along with time, and after the electric thruster works for a period of time T2, closing the electric thruster and recording the reading M2 of the electronic balance;
s7, measuring system drift: keeping the electronic balance (1) in a working state for a period of time T1, and recording the reading M3 of the electronic balance;
s8, repeating the steps S3-S7 for a plurality of times until the expected test is completely finished, turning off the electric thruster, turning off all equipment required by the work of the electric thruster, and turning off the electronic balance (1);
s9, data processing: the current data can be directly read and recorded by a micro-nano current measuring instrument, the flow data can be obtained by a formula (M2-M1)/T2-0.5 (M0-M1+ M2-M3)/T1, and the thrust can be obtained by subtracting the lower envelope curve of the Mt curve from the Mt curve.
Claims (8)
1. The electric thruster thrust flow current combined measuring device is characterized by comprising an electronic balance (1), a lower shielding plate (2), a balance weighing disc (4), a thrust platform (5), side shielding plates (7), a front shielding plate (9), a charge collecting plate (11) and a lifting support (12), wherein a lower shielding plate center hole (3) is formed in the center of the lower shielding plate (2), thrust platform support legs (6) are arranged below the thrust platform (5), and a lifting support channel (8) is formed in the rear of each side shielding plate (7);
the lower shielding plate (2) is placed above the electronic balance (1), and the balance weighing disc (4) is connected with the electronic balance (1) through the lower shielding plate central hole (3);
wherein, the side shielding plate (7) is a three-surface structure and forms a four-surface closed body together with the front shielding plate (9);
wherein the charge collection plate (11) is connected with the side shielding plate (7) through an insulating connector (10);
wherein the lifting support (12) is connected with the lifter (13) through a lifting support channel (8).
2. The micro-thrust flow current combined measuring device of the electric thruster is characterized in that the lower shielding plate (2) is made of a conductive material, the side shielding plates (7) are made of a conductive material, the front shielding plate (9) is made of a conductive material, the insulating connector (10) is made of an insulating material, and the charge collecting plate (11) is made of a conductive material.
3. The thrust flow current combined measuring device of the electric thruster is characterized in that the lifting support (12) is arranged below the thrust table (5), the lifting support (12) is driven by the lifter (13) to move up and down, the upper limit of the stroke of the lifting support (12) is enough to separate the thrust table (5) from the balance weighing plate (4), and the lower limit of the stroke of the lifting support (12) is enough to separate the thrust table (5) from the lifting support (12).
4. The thrust flow current combination device of an electric thruster as claimed in claim 1, characterized in that said insulating connector (10) can be, but is not limited to, an insulating rope, a bolt, a bracket, a boss, a groove.
5. The thrust flow current combined measuring device of the electric thruster is characterized in that the lower shielding plate (2), the side shielding plates (7) and the front shielding plate (9) are connected with the earth potential, and the charge collecting plate (11) is connected with a micro-nano current measuring instrument.
6. The thrust-flow-current joint measurement device of an electric thruster as claimed in claim 1, characterized in that said electronic balance (1) has an internal calibration function.
7. The thrust-flow-current combined measurement device of an electric thruster as claimed in claim 1, characterized in that the electric thruster under test generates thrust by means of a beam of charged particles, the electric thruster being placed on the face of a thrust table (5), the beam of charged particles generated by the electric thruster being directed towards the charge collection plates (11).
8. A method for using a combined thrust-flow-current measuring device of an electric thruster, which is used as the combined thrust-flow-current measuring device of any one of claims 1 to 7, wherein the method comprises the following steps:
s1, adjusting the level of the electronic balance: adjusting a horizontal state adjuster of the electronic balance through the level gauge to enable the electronic balance to be in a horizontal state;
s2, mounting the electric thruster to be tested: placing an electric thruster which can generate charged particle beams and generates thrust through the charged particle beams on the surface of a thrust table (5), placing the thrust table (5) on the surface of a balance weighing disc (4), wherein the charged particle beams generated by the electric thruster are configured to be sprayed to a charge collecting plate (11), connecting the electric thruster with all equipment required by the normal work of the electric thruster, and configuring the working environment to a state required by the electric thruster;
s3, calibrating the electronic balance: adjusting the height of the lifting support (12), so that the thrust platform (5) is separated from the balance weighing disc (4) to start the internal calibration function of the electronic balance (1), and completing the calibration of the electronic balance;
s4, resetting the thrust table: adjusting the height of the lifting support (12), enabling the thrust platform (5) to be separated from the lifting support (12) and enabling the thrust platform (5) to be placed on the surface of the balance weighing disc (4), and recording the reading M0 of the electronic balance (1);
s5, measuring system drift: keeping the electronic balance (1) in a working state for a period of time T1, and recording the reading M1 of the electronic balance;
s6, collecting working data of the electric thruster: starting the electric thruster, simultaneously recording the current passing through the charge collecting plate (11) and the reading of the electronic balance (1) in real time to obtain a balance reading curve Mt changing along with time, and after the electric thruster works for a period of time T2, closing the electric thruster and recording the reading M2 of the electronic balance;
s7, measuring system drift: keeping the electronic balance (1) in a working state for a period of time T1, and recording the reading M3 of the electronic balance;
s8, repeating the steps S3-S7 for a plurality of times until the expected test is completely finished, turning off the electric thruster, turning off all equipment required by the work of the electric thruster, and turning off the electronic balance (1);
s9, data processing: the current data can be directly read and recorded by a micro-nano current measuring instrument, the flow data can be obtained by a formula (M2-M1)/T2-0.5 (M0-M1+ M2-M3)/T1, and the thrust can be obtained by subtracting the lower envelope curve of the Mt curve from the Mt curve.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011093250.6A CN112268704B (en) | 2020-10-13 | 2020-10-13 | Device and method for combined measurement of thrust, flow and current of electric thruster |
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| CN202011093250.6A CN112268704B (en) | 2020-10-13 | 2020-10-13 | Device and method for combined measurement of thrust, flow and current of electric thruster |
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| CN112268704B CN112268704B (en) | 2022-12-20 |
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| CN115684777A (en) * | 2022-10-18 | 2023-02-03 | 兰州空间技术物理研究所 | Combined test method for medium-high power ion thruster |
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| CN112268704B (en) | 2022-12-20 |
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