CN115828589B - Structure strengthening method for ion optical system of thruster - Google Patents
Structure strengthening method for ion optical system of thruster Download PDFInfo
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- CN115828589B CN115828589B CN202211533339.9A CN202211533339A CN115828589B CN 115828589 B CN115828589 B CN 115828589B CN 202211533339 A CN202211533339 A CN 202211533339A CN 115828589 B CN115828589 B CN 115828589B
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- 230000003287 optical effect Effects 0.000 title claims abstract description 62
- 238000005728 strengthening Methods 0.000 title claims abstract description 19
- 238000000034 method Methods 0.000 title claims abstract description 17
- 238000013461 design Methods 0.000 claims abstract description 36
- 238000012360 testing method Methods 0.000 claims abstract description 23
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 19
- 239000000463 material Substances 0.000 claims abstract description 12
- 238000004088 simulation Methods 0.000 claims abstract description 10
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- 238000004519 manufacturing process Methods 0.000 abstract description 2
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- 238000000605 extraction Methods 0.000 description 3
- 230000002787 reinforcement Effects 0.000 description 3
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Abstract
The application relates to the technical field of electric propulsion, in particular to a structural strengthening method of an ion optical system of a thruster, which comprises the following steps: step 1: designing the shape and the size of the strengthening structure according to the requirements of the ion optical system of the thruster; step 2: designing the cross-sectional shape of the reinforcing structure according to the shape and the size of the reinforcing structure; step 3: simulating the relationship between the minimum strength and the material strength through finite element mechanical simulation; step 4: calculating whether the grid spacing of the ion optical system meets the design requirement or not through finite element thermal simulation; step 5: performing impact and vibration force environment test according to design requirements; step 6: thermal vacuum testing was performed according to design requirements. The application has simple process, low production cost, high quality reliability, easy engineering realization, effectively improved structural stability of the ion optical system, and wide control range without changing the critical dimension of the ion optical system, and can design strengthening structures with different shapes according to different requirements.
Description
Technical Field
The application relates to the technical field of electric propulsion, in particular to a structural strengthening method of an ion optical system of a thruster.
Background
The electric propulsion system has the outstanding advantages of high specific impulse and high efficiency, and has become a common technical approach for satellites with long service lives and low cost in countries around the world. The application requirements of the space field of China on electric propulsion are very wide in the current and the next decades.
The ion optical system is a core component of the ion thruster, and mainly aims to generate thrust by focusing and accelerating ions, so that the ion optical system is one of key factors for determining the performance, the service life and the reliability of the thruster. The subsequent deep space exploration and other tasks and the breakthrough of nuclear power propulsion and other technologies, the power requirements on the thrusters are higher and higher, the corresponding ion optical system is larger and larger in size, and further the performance requirements on impact resistance, vibration and the like of the ion optical system and the stability of the force and thermal structure are further improved. When designing the current ion optical system, the ion extraction area is all perforated, the number of holes is thousands or tens of thousands, the width of the connecting area between holes is less than 1mm, the geometric transparency is more than 65% at maximum, and the thickness of the ion optical system is generally 0.4-1.0 mm. Therefore, the ion optical system has weak overall structural strength and rigidity, and poor force and thermal stability, and finally affects the performance and reliability of the thruster.
Disclosure of Invention
The application provides a method for strengthening the structure of an ion optical system of a thruster, which can improve the stability of the structure of the ion optical system and the performance and the reliability of the thruster.
In order to achieve the above object, the present application provides a method for strengthening the structure of an ion optical system of a thruster, comprising the steps of: step 1: designing the shape and the size of the strengthening structure according to the requirements of the ion optical system of the thruster; step 2: designing the cross-sectional shape of the reinforcing structure according to the shape and the size of the reinforcing structure; step 3: considering the safety margin, verifying the design result of the reinforced structure, simulating the relationship between the lowest strength and the material strength through finite element mechanical simulation, returning to the step 1 if the lowest strength is greater than the material strength after considering the safety margin, continuously optimizing the shape and the size of the reinforced structure, and entering the next step if the lowest strength is less than or equal to the material strength; step 4: calculating whether the grid spacing of the ion optical system meets the design requirement or not through finite element thermal simulation, returning to the step 1 if the grid spacing does not meet the design requirement, continuously optimizing the shape and the size of the reinforced structure, and entering the next step if the grid spacing meets the design requirement; step 5: performing impact and vibration force environment tests according to design requirements, returning to the step 1 if the test is failed, continuously optimizing the shape and the size of the reinforced structure, and entering the next step if the test is passed; step 6: and (3) carrying out a thermal vacuum test according to the design requirements, returning to the step (1) if the test is failed, continuously optimizing the shape and the size of the reinforced structure, and if the test is passed, proving that the reinforced structure meets the requirements and completing the design of the reinforced structure of the ion optical system.
Further, in step 1, the ion optical system requirements include a geometry transparency requirement, a force environment requirement, a thermal environment requirement, a diameter requirement of the gate hole, and a diameter requirement of the ion optical system.
Further, the geometric transparency refers to the ratio of the ion optical system open area to the total area.
Further, the reinforcing structure refers to a portion of the ion optical system that is not perforated.
Further, the shape of the reinforcing structure is 1 regular hexagon or a plurality of regular hexagons or a circle.
Further, the cross-sectional shape of the reinforcing structure is a planar shape or a curved shape or other shape having a shape reinforcing effect.
The method for strengthening the structure of the ion optical system of the thruster has the following beneficial effects:
The application has simple process, low production cost, high quality reliability, easy engineering realization, effectively improved structural stability of the ion optical system, large regulating and controlling range, no change to key dimension of the ion optical system and small influence to functional performance of the product, and can design reinforcing structures with different shapes according to different requirements.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application, are incorporated in and constitute a part of this specification. The drawings and their description are illustrative of the application and are not to be construed as unduly limiting the application. In the drawings:
FIG. 1 is a schematic diagram of a shape design of a reinforcing structure according to an embodiment of the present application;
FIG. 2 is a diagram illustrating a second shape design of a reinforcement structure according to an embodiment of the present application;
FIG. 3 is a schematic diagram of a shape design of a reinforcing structure provided according to an embodiment of the present application;
FIG. 4 is a schematic diagram of a shape design of a reinforcing structure according to an embodiment of the present application;
FIG. 5 is a schematic diagram showing a shape design of a reinforcing structure according to an embodiment of the present application;
FIG. 6 is a schematic cross-sectional view without shape strengthening provided in accordance with an embodiment of the present application;
FIG. 7 is a schematic cross-sectional view of a reinforcing structure provided in accordance with an embodiment of the present application;
FIG. 8 is a schematic view of the shape of a reinforced ion optical system provided according to an embodiment of the present application;
FIG. 9 is a schematic view of portion A (open area) of FIG. 8 provided in accordance with an embodiment of the present application;
FIG. 10 is a schematic view of portion B of FIG. 8 (non-open cell reinforced structure area) provided in accordance with an embodiment of the present application;
in the figure: 1-reinforced structure, an open area of the A-ion optical system, and an unopened area of the B-ion optical system.
Detailed Description
In order that those skilled in the art will better understand the present application, a technical solution in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in which 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 those skilled in the art based on the embodiments of the present application without making any inventive effort, shall fall within the scope of the present application.
It should be noted that the terms "first," "second," and the like in the description and the claims of the present application and the above figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate in order to describe the embodiments of the application herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
In the present application, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal" and the like indicate an azimuth or a positional relationship based on that shown in the drawings. These terms are only used to better describe the present application and its embodiments and are not intended to limit the scope of the indicated devices, elements or components to the particular orientations or to configure and operate in the particular orientations.
Also, some of the terms described above may be used to indicate other meanings in addition to orientation or positional relationships, for example, the term "upper" may also be used to indicate some sort of attachment or connection in some cases. The specific meaning of these terms in the present application will be understood by those of ordinary skill in the art according to the specific circumstances.
In addition, the term "plurality" shall mean two as well as more than two.
It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. The application will be described in detail below with reference to the drawings in connection with embodiments.
According to the method for strengthening the structure of the ion optical system of the thruster, provided by the embodiment of the application, in the non-perforated area of the ion optical system, strengthening structures with different shapes and sizes are designed according to the geometric transparency requirement and the force and thermal environment requirement under the condition that the distribution of holes is symmetrical, the structural strength of the ion optical system is obviously improved, the impact resistance and vibration performance of the ion optical system are improved, and the structural stability is improved on the premise that the performance of the ion optical system is not obviously influenced, and the method specifically comprises the following steps:
Step 1: the shape and the size of the reinforced structure 1 are designed according to the actual requirements of the ion optical system of the thruster, namely the geometric transparency requirement (the ratio of the opening area of the ion optical system to the total area), the force environment requirement, the thermal environment requirement, the diameter requirement of the grid hole and the diameter requirement of the ion optical system, and if the caliber of the ion optical system is smaller, the geometric transparency is lower, the reinforced structure 1 can be simplified;
The strengthening structure 1 refers to a part of an ion optical system (an ion extraction area) which is not perforated, when the existing ion optical system is designed, the ion optical system (the ion extraction area) is completely perforated, the number of holes is thousands or tens of thousands, and the width of a connecting area between holes is less than 1 mm.
Step 2: designing the cross-sectional shape of the reinforcing structure according to the shape and size of the reinforcing structure 1; as shown in fig. 6-7, the cross-sectional shape of the reinforcing structure is a planar shape or a curved shape or other shape having a shape reinforcing effect.
Step 3: considering the safety margin, verifying the design result of the reinforced structure 1, simulating the relationship between the lowest strength and the material strength through finite element mechanical simulation, returning to the step 1 if the lowest strength is greater than the material strength after the safety margin is considered, continuously optimizing the shape and the size of the reinforced structure 1, and entering the next step if the lowest strength is less than or equal to the material strength;
Step 4: calculating whether the grid spacing of the ion optical system meets the design requirement or not through finite element thermal simulation, returning to the step 1 if the grid spacing does not meet the design requirement, continuously optimizing the shape and the size of the reinforced structure 1, and entering the next step if the grid spacing meets the design requirement;
step 5: performing impact and vibration force environment tests according to design requirements, returning to the step 1 if the test is failed, continuously optimizing the shape and the size of the reinforced structure 1, and entering the next step if the test is passed;
Step 6: and (3) carrying out a thermal vacuum test according to the design requirements, returning to the step (1) if the test is failed, continuously optimizing the shape and the size of the reinforced structure (1), and if the test is passed, proving that the reinforced structure meets the requirements and completing the design of the reinforced structure of the ion optical system.
The method for strengthening the structure of the ion optical system of the thruster provided by the embodiment of the application is specifically described below by taking an ion optical system with a caliber of 50cm as an example:
Step 1: designing the shape of a reinforced structure according to the requirements of 50cm caliber, 6.8mm screen hole diameter and geometric transparency more than or equal to 67% of the ion optical system needing structural reinforcement, wherein the shape of the reinforced structure adopts a regular hexagon inscribed in 25cm diameter, the length of 12 reinforced structures is 125cm, the width of the reinforced structures is 5mm, the connecting ribs between holes are 2.1mm, the width of the connecting ribs between holes is moderate, as shown in fig. 8-10, wherein A is an open hole area of the ion optical system, and B is a non-open hole area of the ion optical system, namely the reinforced structure;
Step 2: and according to the shape and the size of the reinforced structure, the cross section of the reinforced structure adopts a curved surface shape for reinforcement, wherein the arch height is 1mm, and the width is 3mm.
Step 3: considering safety margin, verifying the design result of the reinforced structure, and simulating the relationship between the lowest strength and the material strength through finite element mechanical simulation, wherein the lowest strength is smaller than or equal to the material strength;
step 4: calculating the grid spacing of the ion optical system through finite element thermal simulation, and meeting the design requirement;
Step 5: performing impact and vibration force environment tests according to design requirements, and passing the tests;
Step 6: the thermal vacuum test is carried out according to the design requirements, and the experiment proves that the reinforced structure of the ion optical system provided by the embodiment of the application meets the design requirements.
The above description is only of the preferred embodiments of the present application and is not intended to limit the present application, but various modifications and variations can be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims (1)
1. The method for strengthening the structure of the ion optical system of the thruster is characterized by comprising the following steps of:
Step 1: designing the shape and the size of a strengthening structure according to the requirements of an ion optical system of a thruster, wherein the ion optical system requirements comprise geometric transparency requirements, force environment requirements, thermal environment requirements, diameter requirements of a grid hole and diameter requirements of the ion optical system, and the geometric transparency refers to the ratio of the open area of the ion optical system to the total area; the strengthening structure refers to a part which is not perforated in the ion optical system, the shape of the strengthening structure is 1 regular hexagon or a plurality of regular hexagons or circles, the width of a connecting area between holes can be enlarged, the structural strength and the rigidity of the ion optical system are improved, and the stability of the ion optical system is ensured;
Step 2: designing the cross section shape of the reinforced structure according to the shape and the size of the reinforced structure, wherein the cross section shape of the reinforced structure is a plane shape or a curved surface shape or other shapes with shape reinforcing effect;
Step 3: considering the safety margin, verifying the design result of the reinforced structure, simulating the relationship between the lowest strength and the material strength through finite element mechanical simulation, returning to the step 1 if the lowest strength is greater than the material strength after considering the safety margin, continuously optimizing the shape and the size of the reinforced structure, and entering the next step if the lowest strength is less than or equal to the material strength;
Step 4: calculating whether the grid spacing of the ion optical system meets the design requirement or not through finite element thermal simulation, returning to the step 1 if the grid spacing does not meet the design requirement, continuously optimizing the shape and the size of the reinforced structure, and entering the next step if the grid spacing meets the design requirement;
Step 5: performing impact and vibration force environment tests according to design requirements, returning to the step 1 if the test is failed, continuously optimizing the shape and the size of the reinforced structure, and entering the next step if the test is passed;
Step 6: and (3) carrying out a thermal vacuum test according to the design requirements, returning to the step (1) if the test is failed, continuously optimizing the shape and the size of the reinforced structure, and if the test is passed, proving that the reinforced structure meets the requirements and completing the design of the reinforced structure of the ion optical system.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211533339.9A CN115828589B (en) | 2022-11-30 | 2022-11-30 | Structure strengthening method for ion optical system of thruster |
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| CN202211533339.9A CN115828589B (en) | 2022-11-30 | 2022-11-30 | Structure strengthening method for ion optical system of thruster |
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| CN115828589A CN115828589A (en) | 2023-03-21 |
| CN115828589B true CN115828589B (en) | 2024-05-07 |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008023071A1 (en) * | 2006-08-25 | 2008-02-28 | Carl Zeiss Smt Ag | Method and system for correcting image changes |
| CN111649912A (en) * | 2020-06-02 | 2020-09-11 | 兰州空间技术物理研究所 | Accelerated life test method for ion thruster |
| CN114398774A (en) * | 2021-12-28 | 2022-04-26 | 北京遥感设备研究所 | High-reliability optical system optimization design method |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10823158B2 (en) * | 2016-08-01 | 2020-11-03 | Georgia Tech Research Corporation | Deployable gridded ion thruster |
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- 2022-11-30 CN CN202211533339.9A patent/CN115828589B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008023071A1 (en) * | 2006-08-25 | 2008-02-28 | Carl Zeiss Smt Ag | Method and system for correcting image changes |
| CN111649912A (en) * | 2020-06-02 | 2020-09-11 | 兰州空间技术物理研究所 | Accelerated life test method for ion thruster |
| CN114398774A (en) * | 2021-12-28 | 2022-04-26 | 北京遥感设备研究所 | High-reliability optical system optimization design method |
Non-Patent Citations (3)
| Title |
|---|
| "Adaptive Subcarrier PSK Intensity Modulation in Free Space Optical Systems";Nestor D. Chatzidiamantis et al.;《IEEE Transactions on Communications》;20110303;第59卷(第5期);全文 * |
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