CN115828589A - Thruster ion optical system structure strengthening method - Google Patents
Thruster ion optical system structure strengthening method Download PDFInfo
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- CN115828589A CN115828589A CN202211533339.9A CN202211533339A CN115828589A CN 115828589 A CN115828589 A CN 115828589A CN 202211533339 A CN202211533339 A CN 202211533339A CN 115828589 A CN115828589 A CN 115828589A
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Abstract
The application relates to the technical field of electric propulsion, in particular to a thruster ion optical system structure strengthening method, which comprises the following steps: step 1: designing the shape and size of the strengthening structure according to the requirements of the ion optical system of the thruster; step 2: designing the cross section shape of the reinforcing structure according to the shape and the size of the reinforcing structure; and step 3: simulating the relation between the lowest strength and the material strength through finite element mechanics simulation; and 4, step 4: calculating whether the grid spacing of the ion optical system meets the design requirements or not through finite element thermal simulation; and 5: carrying out impact and vibration force environment tests according to design requirements; step 6: the thermal vacuum test was performed as designed. The method has the advantages of simple process, low production cost, high quality reliability, easy engineering realization, capability of effectively improving the structural stability of the ion optical system, capability of designing different shapes of strengthening structures according to different requirements, large regulation and control range and no change on the key size of the ion optical system.
Description
Technical Field
The application relates to the technical field of electric propulsion, in particular to a thruster ion optical system structure strengthening method.
Background
The electric propulsion system has the outstanding advantages of high specific impulse and high efficiency, and has become a technical approach commonly adopted by satellites with long service life and low cost in various countries in the world. In the present and the next decades, the application demand of the space field of China for electric propulsion is extremely wide.
The ion optical system is a core component of the ion thruster, mainly plays a role in generating thrust by focusing and accelerating ions, and is one of key factors determining the performance, service life and reliability of the thruster. The requirements on the power of a thruster are higher and higher, the size of a corresponding ion optical system is larger and larger, and the performance requirements on the impact resistance, the vibration resistance and the like of the ion optical system, the force stability and the thermal structure stability are further improved. When the current ion optical system is designed, all the ion leading-out areas are provided with holes, the number of the holes reaches thousands or tens of thousands, the width of the connection area between the holes is less than 1mm, the geometric transparency is more than 65 percent at most, and the thickness of the ion optical system is generally 0.4 to 1.0mm. Therefore, the ion optical system has weak overall structural strength and rigidity and poor force and thermal stability, and finally influences the performance and reliability of the thruster.
Disclosure of Invention
The application provides a thruster ion optical system structure strengthening method which can improve stability of an ion optical system structure and performance and reliability of a thruster.
In order to achieve the above object, the present application provides a method for strengthening a thruster ion optical system structure, comprising the following steps: step 1: designing the shape and size of the strengthening structure according to the requirements of the ion optical system of the thruster; step 2: designing the cross section shape of the reinforcing structure according to the shape and the size of the reinforcing structure; and 3, 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 mechanics simulation, returning to the step 1 if the lowest strength is greater than the material strength after considering the safety margin, continuing to optimize 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; and 4, step 4: calculating whether the grid spacing of the ion optical system meets the design requirements through finite element thermal simulation, if not, returning to the step 1, continuously optimizing the shape and the size of the reinforced structure, and if so, entering the next step; and 5: performing impact and vibration force environment tests according to design requirements, returning to the step 1 if the tests are not passed, continuously optimizing the shape and the size of the reinforced structure, and entering the next step if the tests are passed; step 6: and (4) performing a thermal vacuum test according to design requirements, returning to the step 1 if the test is not passed, continuing to optimize the shape and the size of the strengthening structure, and if the test is passed, proving that the strengthening structure meets the requirements, and completing the design of the strengthening structure of the ion optical system.
Further, in step 1, the requirements of the ion optical system include geometric transparency requirements, force environment requirements, thermal environment requirements, diameter requirements of the gate hole, and diameter requirements of the ion optical system.
Further, geometric transparency refers to the ratio of the area of the ion optical system opening to the total area.
Further, the reinforcing structure refers to a portion of the ion optical system that is not apertured.
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, a curved surface shape, or another shape having a shape reinforcing effect.
The structure strengthening method for the ion optical system of the thruster provided by the invention has the following beneficial effects:
the method has the advantages of simple process, low production cost, high quality reliability, easy engineering realization, capability of effectively improving the structural stability of the ion optical system, capability of designing different shapes of strengthening structures according to different requirements, large regulation and control range, no change on the key size of the ion optical system and small influence on the functional performance of a product.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, serve to provide a further understanding of the application and to enable other features, objects, and advantages of the application to be more apparent. The drawings and their description illustrate the embodiments of the invention and do not limit it. In the drawings:
FIG. 1 is a first schematic view of a shape design of a reinforcing structure according to an embodiment of the present disclosure;
FIG. 2 is a second schematic view of a shape design of a reinforcing structure according to an embodiment of the present disclosure;
FIG. 3 is a third schematic view of the shape design of a reinforcing structure provided in accordance with an embodiment of the present application;
FIG. 4 is a fourth schematic view of the shape design of the reinforcing structure provided in accordance with the embodiment of the present application;
FIG. 5 is a schematic diagram illustrating a shape design of a reinforcing structure according to an embodiment of the present disclosure;
FIG. 6 is a schematic cross-sectional view without shape reinforcement 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 diagram of a shape of an enhanced ion optical system provided in accordance with an embodiment of the present application;
FIG. 9 is a schematic view of portion A (the open area) of FIG. 8 according to an embodiment of the present application;
FIG. 10 is a schematic view of portion B (not having an open reinforcement structure region) of FIG. 8 according to an embodiment of the present disclosure;
in the figure: 1-strengthening structure, an A-ion optical system open hole area, and a B-ion optical system non-open hole area.
Detailed Description
In order to make the technical solutions better understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only partial embodiments of the present application, but not all 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 application.
It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It should be understood that the data so used may be interchanged under appropriate circumstances such that embodiments of the application described herein may be used. 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 this application, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings. These terms are used primarily to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to a particular orientation or to be constructed and operated in a particular orientation.
Moreover, some of the above terms may be used to indicate other meanings besides the orientation or positional relationship, for example, the term "on" may also be used to indicate some kind of attachment or connection relationship in some cases. The specific meaning of these terms in this application will be understood by those of ordinary skill in the art as appropriate.
In addition, the term "plurality" shall mean two as well as more than two.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
The strengthening method for the thruster ion optical system structure provided by the embodiment of the application designs strengthening structures with different shapes and sizes according to the symmetrical hole distribution condition in the un-perforated area of the ion optical system and the requirements of geometric transparency and force and thermal environment, obviously improves the structural strength of the ion optical system on the premise of no obvious influence on the performance of the ion optical system, increases the shock resistance and vibration resistance of the ion optical system, and improves the structural stability, and specifically comprises the following steps:
step 1: according to the practical requirements of the thruster ion optical system, namely geometric transparency requirement (the ratio of the opening area of the ion optical system to the total area), force environment requirement, thermal environment requirement, diameter requirement of a gate hole and diameter requirement of the ion optical system, the shape and the size of the strengthening structure 1 are designed, and if the caliber of the ion optical system is smaller and the geometric transparency is lower, the strengthening structure 1 can be simply designed;
in the present embodiment, the ion optical system (ion extraction region) is divided into an aperture part and an un-aperture part, and according to the actual requirements of the thruster ion optical system, the un-aperture part (reinforced structure) is designed into 1 regular hexagon or a plurality of regular hexagons or a circle, as shown in fig. 1-5, so that the width of the inter-aperture connection region is increased, the structural strength and rigidity of the ion optical system can be significantly improved, and the stability of the ion optical system can be ensured.
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 to 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.
And 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 mechanics simulation, returning to the step 1 if the lowest strength is greater than the material strength after the safety margin is considered, continuing to optimize 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;
and 4, step 4: calculating whether the grid spacing of the ion optical system meets the design requirements through finite element thermal simulation, if not, returning to the step 1, continuously optimizing the shape and the size of the reinforced structure 1, and if so, entering the next step;
and 5: performing impact and vibration force environment tests according to design requirements, returning to the step 1 if the tests are not passed, continuously optimizing the shape and the size of the reinforced structure 1, and entering the next step if the tests are passed;
step 6: and (4) performing a thermal vacuum test according to design requirements, returning to the step 1 if the test is not passed, continuing to optimize the shape and the size of the strengthening structure 1, and if the test is passed, proving that the strengthening structure meets the requirements, and completing the design of the strengthening structure of the ion optical system.
The following specifically describes the structure strengthening method of the thruster ion optical system provided in the embodiment of the present application, taking an ion optical system with a diameter of 50cm as an example:
step 1: designing the shape of a reinforced structure for an ion optical system needing structural reinforcement according to the requirements of the caliber size of 50cm, the diameter of a screen grid hole of 6.8mm and the geometric transparency of more than or equal to 67 percent, wherein the shape of the reinforced structure adopts a regular hexagon which is internally connected with the diameter of 25cm, the length of 12 reinforced structures is 125cm, the width of the reinforced structures is 5mm, the width of inter-hole connecting ribs is 2.1mm, and the width of the inter-hole connecting ribs is moderate, as shown in figures 8-10, wherein A is a perforated area of the ion optical system, and B is an un-perforated area of the ion optical system, namely the reinforced structure;
step 2: according to the shape and the size of the strengthening structure, the cross section of the strengthening structure is strengthened in a curved surface shape, wherein the arch height is 1mm, and the width is 3mm.
And step 3: considering the 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 mechanics simulation, wherein the lowest strength is less than or equal to the material strength;
and 4, step 4: calculating the grid spacing of the ion optical system through finite element thermal simulation to meet the design requirement;
and 5: the impact and vibration force environment tests are carried out according to the design requirements, and the tests can be passed;
and 6: the thermal vacuum test is carried out according to the design requirement, and the experiment proves that the ion optical system strengthening structure provided by the embodiment of the application meets the design requirement.
The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (6)
1. A thruster ion optical system structure strengthening method is characterized by comprising the following steps:
step 1: designing the shape and size of the strengthening structure according to the requirements of an ion optical system of the thruster;
step 2: designing the cross section shape of the reinforcing structure according to the shape and the size of the reinforcing structure;
and 3, 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 mechanics simulation, returning to the step 1 if the lowest strength is greater than the material strength after considering the safety margin, continuing to optimize 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;
and 4, step 4: calculating whether the grid spacing of the ion optical system meets the design requirements through finite element thermal simulation, if not, returning to the step 1, continuously optimizing the shape and the size of the reinforced structure, and if so, entering the next step;
and 5: performing impact and vibration force environment tests according to design requirements, returning to the step 1 if the tests are not passed, continuously optimizing the shape and the size of the reinforced structure, and entering the next step if the tests are passed;
step 6: and (4) performing a thermal vacuum test according to design requirements, returning to the step 1 if the test is not passed, continuing to optimize the shape and the size of the strengthening structure, and if the test is passed, proving that the strengthening structure meets the requirements, and completing the design of the strengthening structure of the ion optical system.
2. The method for strengthening the structure of the ion optical system of the thruster of claim 1, wherein in step 1, the requirements of the ion optical system comprise geometric transparency requirements, force environment requirements, thermal environment requirements, diameter requirements of a grid hole and diameter requirements of the ion optical system.
3. The method of claim 2, wherein the geometric transparency is a ratio of an open area to a total area of the ion optical system.
4. The thruster ion optical system structure strengthening method of claim 1, wherein the strengthening structure refers to a portion of the ion optical system that is not perforated.
5. The thruster ion optical system structure strengthening method of claim 4, wherein the shape of the strengthening structure is 1 regular hexagon or a plurality of regular hexagons or a circle.
6. The thruster ion optical system structure strengthening method of claim 5, wherein the cross-sectional shape of the strengthening structure is a plane shape or a curved surface shape or other shape having a shape strengthening effect.
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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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| 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 |
| US20190195206A1 (en) * | 2016-08-01 | 2019-06-27 | Georgia Tech Research Corporation | Deployable gridded ion thruster |
| 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 |
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- 2022-11-30 CN CN202211533339.9A patent/CN115828589B/en active Active
Patent Citations (4)
| 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 |
| US20190195206A1 (en) * | 2016-08-01 | 2019-06-27 | Georgia Tech Research Corporation | Deployable gridded ion thruster |
| 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)
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| NESTOR D. CHATZIDIAMANTIS ET AL.: ""Adaptive Subcarrier PSK Intensity Modulation in Free Space Optical Systems"", 《IEEE TRANSACTIONS ON COMMUNICATIONS》, vol. 59, no. 5, 3 March 2011 (2011-03-03) * |
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