CN113125063B - Electric propulsion thrust measurement calibration device - Google Patents
Electric propulsion thrust measurement calibration device Download PDFInfo
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- CN113125063B CN113125063B CN202110416234.4A CN202110416234A CN113125063B CN 113125063 B CN113125063 B CN 113125063B CN 202110416234 A CN202110416234 A CN 202110416234A CN 113125063 B CN113125063 B CN 113125063B
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- frame
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- ejector rod
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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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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The application relates to the technical field of aerospace testing, and specifically relates to an electric propulsion thrust measurement calibration device, which comprises a static frame, a dynamic frame, a balance weight, a base, a calibration device and a supporting structure, wherein: the movable frame is fixed on the static frame through a supporting structure and can swing around the supporting structure; the base is arranged between the connecting rods at the two sides of the movable frame; the balance weight is arranged on the ejector rod of the movable frame; the calibration device is fixedly connected with the ejector rod of the movable frame and the ejector rod of the static frame respectively. The invention mainly improves the supporting form of the movable frame in the balance pendulum measuring device, and integrates the electromagnetic damping structure and the electromagnetic force generating device, has simple structure and convenient use, can adapt to the thrust measurement of the electric thruster with larger mass, ensures that the measuring and calibrating device has more compact structure, is beneficial to the implementation of electromagnetic shielding, effectively reduces the complexity of products and ensures the reliable operation of the measuring and calibrating device in a vacuum environment.
Description
Technical Field
The application relates to the technical field of aerospace testing, in particular to an electric propulsion thrust measurement calibration device.
Background
Along with the wide application of electric propulsion technology, various types of electric thrusters are being developed, thrust measurement is one of the necessary items for ground test evaluation in the development process of the electric thrusters, can directly show the change relation between electric parameters and thrust, and has important significance for the design of an electric propulsion space application strategy. The measurement of the electric propulsion micro-thrust is challenging due to the fact that the measurement is affected by the vibration in the environment, the thermal load generated in the operation of the electric thruster, the plasma, the electromagnetism and other factors.
The current common electric propulsion thrust measurement principles are divided into torsion pendulum type, single pendulum type, cantilever beam structure, inverted pendulum type and balance pendulum type principles, wherein the torsion pendulum type is sensitive to temperature, the balancing is difficult, and the bearing is limited; the simple pendulum structure is the earliest structure, and the sensitivity is related to the length of the swing rod; the cantilever beam has simple structure principle and good thermal deformation resistance effect, and has zero drift phenomenon under the influence of thrust deflection angle; the inverted pendulum structure is applied to the measurement of the high-power thrusters, and has poor applicability to different types of thrusters due to the instability of the structure; the balance pendulum structure has the advantages of inverted pendulum and simple pendulum structure, but the knife edge supporting structure which is commonly used cannot adapt to a large-mass thruster and cannot be quickly replaced and needs an independent skin adjusting mechanism, damping and calibration force are two parts, and the integral structure is dispersed and cannot adapt to the requirement of measurement automation.
Disclosure of Invention
Aiming at the problems existing in the background technology, the invention provides an electric propulsion thrust measurement calibration device which integrates damping and calibration into a part and can be suitable for thrust measurement calibration of a large-mass thruster.
The utility model provides an electric propulsion thrust measures calibration device, including quiet frame, movable frame, balancing piece, base, calibration device and bearing structure, wherein: the movable frame is fixed on the static frame through a supporting structure and can swing around the supporting structure; the base is arranged between the connecting rods at the two sides of the movable frame; the balance weight is arranged on the ejector rod of the movable frame; the calibration device is fixedly connected with the ejector rod of the movable frame and the ejector rod of the static frame respectively.
Further, the supporting structure is an adjustable screw supporting structure.
Further, the calibrating device comprises a permanent magnet gravity calibrating rod, a coil and a copper plate.
Further, the permanent magnet gravity calibration rod is vertically connected with the ejector rod of the movable frame.
Further, the copper plate is fixed on the ejector rod of the static frame.
Further, the coil is disposed inside the copper plate.
Furthermore, in operation, the permanent magnet gravity calibration rod and the coil form an electromagnetic eddy current damping system.
The electric propulsion thrust measurement calibration device provided by the invention has the following beneficial effects:
the invention mainly improves the supporting form of the movable frame in the balance pendulum measuring device, and integrates the electromagnetic damping structure and the electromagnetic force generating device, has simple structure and convenient use, can adapt to the thrust measurement of the electric thruster with larger mass, ensures that the measuring and calibrating device has more compact structure, is beneficial to the implementation of electromagnetic shielding, effectively reduces the complexity of products and ensures the reliable operation of the measuring and calibrating device in a vacuum environment.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, are included to provide a further understanding of the application and to provide a further understanding of the application with regard to the other features, objects and advantages of the application. The drawings of the illustrative embodiments of the present application and their descriptions are for the purpose of illustrating the present application and are not to be construed as unduly limiting the present application. In the drawings:
FIG. 1 is a schematic structural view of an electric propulsion thrust measurement calibration device of the present application;
FIG. 2 is a schematic view of a support structure of the electric propulsion thrust measurement calibration device of the present application;
FIG. 3 is a gravity, electromagnetic force calibration and damping system of the electric propulsion thrust measurement calibration device of the present application;
in the figure: 1-movable frame, 2-static frame, 3-balancing piece, 4-permanent magnet gravity calibration pole, 5-electric thruster, 6-copper, 7-coil, 8-bearing structure, 9-base.
Detailed Description
In order to make the present application solution better understood by those skilled in the art, the following description will be made in detail and with reference to the accompanying drawings in the embodiments of the present application, it is apparent that the described embodiments are only some embodiments of the present application, not all embodiments. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, shall fall within the scope of the present application.
As shown in fig. 1 to 3, the electric propulsion thrust measurement calibration device provided by the application comprises a static frame 2, a dynamic frame 1, a balance weight 3, a base 9, a calibration device and a support structure 8, wherein: the movable frame 1 is fixed on the static frame 2 through a supporting structure 8 and can swing around the supporting structure 8; the base 9 is arranged between the connecting rods at the two sides of the movable frame 1; the balance weight 3 is arranged on the ejector rod of the movable frame 1; the calibration device is fixedly connected with the ejector rod of the movable frame 1 and the ejector rod of the static frame 2 respectively.
Specifically, the electric propulsion thrust measurement calibration device provided by the embodiment of the application is mainly used for improving the existing balance pendulum type measurement device, optimizing the supporting structure 8 of the movable frame 1, and integrating the gravity calibration, the electromagnetic calibration and the damping system into a part, so that the measurement calibration device is more compact in structure and suitable for thrust measurement of the electric thruster 5 with larger mass. The static frame 2 mainly plays a role of fixing and supporting and is mainly used for fixing the movable frame 1 and the calibration device; the movable frames 1 are connected with the static frames 2 through the supporting structures 8, and in the measuring process, under the action of the electric thrusters 5, the movable frames 1 swing around the supporting structures 8 between the static frames 2; the balance weight 3 is mainly used for balancing the mass of the electric thruster 5, and ensures that the gravity center of the movable frame 1 is as close to the swing supporting position as possible, thereby obtaining a larger swing angle; the base 9 is mainly used for fixedly placing the electric thruster 5, and after the electric thruster 5 generates thrust, the base 9 drives the movable frame 1 to swing; the calibration device is mainly used for providing damping and a calibration system, wherein the damping system is an eddy current damping system and is mainly used for enabling the movable frame 1 to quickly return to the balance position in the measurement and calibration process, and the calibration system can adopt two calibration modes, namely gravity calibration under the atmospheric condition and electromagnetic calibration under the vacuum condition; the supporting structure 8 mainly facilitates the adjustment of the gravity center of the swing of the movable frame 1, so that the swing point position is kept horizontal.
Further, the support structure 8 is an adjustable screw support structure 8. The supporting structure 8 adopts an adjustable screw rod, so that the adjustment of the gravity center is more convenient, the sharp point type supporting structure 8 can be quickly replaced according to the electric thrusters 5 with different masses, the gravity center of the system can be finely adjusted by adjusting the length of the screw rod, the gravity center of the system is enabled to be as close to the position of a supporting swing point as possible, the gravity center is in point-to-surface contact with a semicircular supporting surface, the interference of friction force on measurement is reduced, and meanwhile, the movable frame 1 can be conveniently adjusted to enable the swing point to be kept horizontal.
Further, the calibrating device comprises a permanent magnet gravity calibrating rod 4, a coil 7 and a copper plate 6. The gravity calibration can be realized under the atmospheric condition through the permanent magnet gravity calibration rod 4, and the moment generated by the thrust of the standard weight simulation thruster is hung at different scales of the permanent magnet gravity calibration rod 4; electromagnetic calibration can be realized under the vacuum condition through the coil 7 and the copper plate 6, current is loaded in the coil 7 on the surface of the copper plate 6, the electrified electromagnetic coil 7 is acted by Lorentz magnetic force in a uniform magnetic field generated inside the permanent magnet, the reaction force enables the permanent magnet to drive the movable frame 1 to start swinging, and the thrust generated by the thruster is simulated.
Further, the permanent magnet gravity calibration rod 4 is vertically connected with the ejector rod of the movable frame 1. The permanent magnet gravity calibration rod 4 has a scale at one end, which can show the vertical distance from the calibration weight to the rotating shaft, so that the torque of the gravity of the calibration weight to the rotating shaft can be easily judged; the other end is provided with a U-shaped permanent magnet for generating a uniform magnetic field, generating electromagnetic damping for a coil moving in the U-shaped permanent magnet, generating Lorentz force when the coil is electrified, and taking the Lorentz force as a calibration force in a vacuum environment, the whole permanent magnet gravity calibration rod 4 is arranged on the movable frame 1 and swings along with the movable frame 1, and the gravity calibration, the electromagnetic calibration and the damping are integrated into one part, so that the whole structure is more compact.
Further, the copper plate 6 is fixed on the ejector rod of the static frame 2. The copper plate 6 can be welded on the ejector rod of the static frame 2 through a connecting short rod according to actual conditions.
Further, a coil 7 is provided inside the copper plate 6. A current may be applied to the coil 7 to generate a magnetic field.
Further, in operation, the permanent magnet gravity calibration rod 4 and the coil 7 form an electromagnetic eddy current damping system. Through the permanent magnet that sets up on moving frame 1 and copper 6, the coil 7 on quiet frame 2, when the thruster ignition work, moving frame 1 begins the swing, and copper 6 can cut the magnetic induction line this moment, thereby can produce the vortex in copper 6 and block the swing of moving frame 1 under the effect of the inhomogeneous magnetic field of disorder, help moving frame 1 to get back to the equilibrium position rapidly.
The foregoing description of the preferred embodiments of the present application is not intended to be limiting, but rather, it will be apparent to those skilled in the art that various changes and modifications can be made without departing from the spirit and principles of the application, and it is intended to cover any and all such modifications, equivalents, improvements or modifications that fall within the spirit and scope of the present application.
Claims (1)
1. The utility model provides an electric propulsion thrust measurement calibration device which characterized in that, includes static frame, moves frame, balancing piece, base, calibration device and bearing structure, wherein:
the movable frame is fixed on the static frame through the supporting structure and can swing around the supporting structure;
the base is arranged between the connecting rods at two sides of the movable frame;
the balance weight is arranged on the ejector rod of the movable frame;
the calibration device is fixedly connected with the ejector rod of the movable frame and the ejector rod of the static frame respectively;
the supporting structure is an adjustable screw supporting structure;
the calibrating device comprises a permanent magnet gravity calibrating rod, a coil and a copper plate;
the permanent magnet gravity calibration rod is vertically connected with the ejector rod of the movable frame;
the copper plate is fixed on the ejector rod of the static frame;
the coil is arranged in the copper plate;
when the electromagnetic vortex damping system works, the permanent magnet gravity calibration rod and the coil form an electromagnetic vortex damping system.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110416234.4A CN113125063B (en) | 2021-04-16 | 2021-04-16 | Electric propulsion thrust measurement calibration device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110416234.4A CN113125063B (en) | 2021-04-16 | 2021-04-16 | Electric propulsion thrust measurement calibration device |
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| CN113125063A CN113125063A (en) | 2021-07-16 |
| CN113125063B true CN113125063B (en) | 2023-06-23 |
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105181241A (en) * | 2015-08-12 | 2015-12-23 | 中国石油大学(华东) | Adjustable work bench type force loading apparatus and calibration method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102072790B (en) * | 2010-11-16 | 2011-12-07 | 北京航空航天大学 | Device for measuring micro impulse |
| CN102721456B (en) * | 2012-06-27 | 2013-11-13 | 中国人民解放军国防科学技术大学 | Method for directly calibrating micro thrust and micro impulse |
| CN207263362U (en) * | 2017-09-14 | 2018-04-20 | 上海怀德机电有限公司 | A kind of device for measuring micro-thrust |
| CN108981974B (en) * | 2018-07-10 | 2020-08-07 | 南京航空航天大学 | Ultra-high-precision micro-force measuring device and method based on gravity compound pendulum |
| CN109724771B (en) * | 2018-12-17 | 2020-07-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Simple pendulum type balance for measuring underwater vehicle resistance |
| CN110413015B (en) * | 2019-06-27 | 2023-08-01 | 北京控制工程研究所 | Micro-bovine-magnitude micro-thrust dynamic test board based on closed-loop control and test method |
| CN111595512A (en) * | 2020-06-11 | 2020-08-28 | 中国船舶重工集团公司第七0四研究所 | Torque generator for micro-torque calibration |
| CN111829709B (en) * | 2020-06-22 | 2022-04-22 | 中国空间技术研究院 | Method and device for measuring torque of Hall thruster |
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Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105181241A (en) * | 2015-08-12 | 2015-12-23 | 中国石油大学(华东) | Adjustable work bench type force loading apparatus and calibration method thereof |
Non-Patent Citations (1)
| Title |
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| 施陈波 ; 汤海滨 ; 张莘艾 ; 秦超晋 ; 曹熙炜 ; .mN级推力架静态特性及推力测量不确定度分析.固体火箭技术.2011,第34卷(第03期),第398-402页. * |
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