CN111352209A - Support structure of large-caliber reflector component of space remote sensor - Google Patents
Support structure of large-caliber reflector component of space remote sensor Download PDFInfo
- Publication number
- CN111352209A CN111352209A CN202010267310.5A CN202010267310A CN111352209A CN 111352209 A CN111352209 A CN 111352209A CN 202010267310 A CN202010267310 A CN 202010267310A CN 111352209 A CN111352209 A CN 111352209A
- Authority
- CN
- China
- Prior art keywords
- flexible
- support structure
- mirror assembly
- remote sensor
- flexible joint
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B7/00—Mountings, adjusting means, or light-tight connections, for optical elements
- G02B7/18—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors
- G02B7/182—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors for mirrors
- G02B7/183—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors for mirrors specially adapted for very large mirrors, e.g. for astronomy, or solar concentrators
Landscapes
- Physics & Mathematics (AREA)
- Life Sciences & Earth Sciences (AREA)
- Astronomy & Astrophysics (AREA)
- Sustainable Development (AREA)
- General Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The application provides a bearing structure of large-diameter mirror assembly of space remote sensor, including speculum, three flexible supporting components of group, evenly set up three taper hole around the circumferencial direction on the speculum, three flexible supporting components of group set up respectively in the taper hole, flexible supporting component adopts metal, the compound flexible construction that nonmetal matching fuses, has promoted the quiet of large-diameter back three point support mirror assembly, dynamics support performance greatly.
Description
Technical Field
The application relates to the technical field of space optical remote sensing, in particular to a support structure of a large-aperture reflector assembly of a space remote sensor.
Background
The optical remote sensor is used for general survey and detailed survey of earth and space resources, and has important scientific and economic significance in the fields of earth observation, space exploration and the like. The optical element-reflector assembly in the remote sensor is the most important component in the whole optical system, and the static and dynamic index performance of the optical element-reflector assembly is directly related to the imaging quality of the whole remote sensor, and the static index comprises: the surface shape precision and the space positioning capability (rigid displacement of the reflector and the inclination angle of the reflector) of the mirror surface; the dynamic indexes are as follows: fundamental frequency, dynamic stress and fatigue resistance.
The traditional back three-point supporting mode is taken as an example for illustration, the specific supporting structure mode is shown in attached figures 1 and 2, the mirror mainly comprises a reflector 1, a first connecting screw 2, a second connecting screw 3, a first positioning pin 4, a taper sleeve 5, a flexible joint 6 and a repairing and grinding pad 7, and the supporting structures are three groups and are distributed at 120 degrees in the circumferential direction. The flexible joint 6 is provided with a characteristic flexible groove 8.
Due to the large size of the mirror surface, the mirror surface is often seriously deformed under the action of comprehensive factors such as gravity load, temperature load, assembly error of the mirror assembly and the like. The surface shape change under the gravity load is closely related to the supporting position of the flexible supporting structure in the optical axis direction of the reflector (namely, the flexible part of the flexible joint and the neutral plane of the reflector have an optimal supporting position), the surface shape change caused by the gravity load is solved by optimizing the size, the inclination angle change of the reflector is also related to the position, the influence of the position on the surface shape change and the inclination angle change under the gravity load is consistent, and the inclination angle is minimum or nearly minimum when the surface shape is optimal. The assembly error of the reflector component and the rigidity of a main support structure of the change of the surface shape size caused by the temperature load are related, the larger the rigidity is, the larger the change of the surface shape caused by the two errors is, in order to reduce the sensitivity of the surface shape precision of the reflector component relative to the assembly error and the temperature load, the support structure of the reflector component generally adopts a flexible support structure, the lower the flexible joint rigidity is relative to the assembly error and the temperature load, the smaller the change of the surface shape caused by the two items is, but the larger the flexibility is, the larger the rigid body displacement of the reflector under the gravity load is, and particularly the dynamic performance of the reflector component is poor, one of the following: the fundamental frequency is low, and the main excitation frequency in the emission process can not be avoided, so that the components resonate and are damaged. The second step is as follows: the dynamic stress is high, and the main structure of the flexible joint is the groove and the sheet, and the flexible joint is easy to exceed the strength limit of the material and be damaged when bearing the action of a main excitation source (even if the fundamental frequency is improved, the assembly is also excited by vibration with a large magnitude in the emission and transportation process). And thirdly: the fatigue resistance performance is poor, and the flexible joint is easy to be damaged by fatigue at the thin sheet and the groove of the flexible joint which can act for a long time in the excitation sources of all frequency bands in the working process of launching and satellites, thereby losing efficacy.
On the premise that the rigid body displacement does not exceed the design requirement under the gravity load, the greater the flexibility of the supporting structure, the smaller the sensitivity to the temperature load and the assembly error, and the smaller the surface shape precision root mean square value of the mirror surface of the reflector assembly (the surface shape change and the inclination angle change under the gravity load can be solved by adjusting the axial supporting position); for the dynamic indexes, the support flexibility is too high, so that the fundamental frequency of the reflector assembly is too low, the damping of the support structure is small, the dynamic response is increased, too high dynamic stress is generated at the flexible link, and the support is easy to fail due to strength damage or fatigue damage. For the traditional passive support structure form, static and dynamic indexes are contradictory to the rigid and flexible design requirements of the support structure.
Disclosure of Invention
The application provides a bearing structure of space remote sensor heavy-calibre reflector subassembly solves among the prior art dynamic and static properties of primary mirror subassembly can't accomplish optimal technical problem simultaneously in the back three point support scheme.
In view of this, the application provides a supporting structure of space remote sensor heavy-calibre reflector subassembly, including speculum, three groups of flexible supporting components, evenly set up three taper holes around the circumferencial direction on the speculum, three groups of flexible supporting components set up respectively in the taper hole.
Preferably, flexible supporting component includes taper sleeve, gentle festival, the taper sleeve with the taper hole phase-match, the taper sleeve passes through the screw and the pin is fixed gentle festival, the one end of gentle festival is passed through the screw and is connected with the speculum.
Preferably, flexible section includes connecting plate, hollow cylinder, flexible head, hollow cylinder with set up the necking down between the flexible head, the necking down is hyperboloid structure.
Preferably, an axial flexible groove is arranged on the flexible head.
Preferably, a repairing and grinding pad is arranged on the outer side of the connecting plate of the flexible joint, and the repairing and grinding pad is connected with the connecting plate through a screw.
Preferably, a non-metallic viscoelastic damping material is disposed around said constriction and within said axially flexible groove.
Preferably, the nonmetal viscoelastic damping material is rubber, and the viscoelastic coefficient, the perfusion amount and the perfusion position of the rubber are optimally determined according to design indexes.
Compared with the prior art, the beneficial effects of this application lie in:
the application relates to a supporting structure of a large-caliber reflector component of a space remote sensor, which has the advantages of clear principle and simple structure, adopts a composite flexible structure formed by matching and fusing metal and nonmetal, and greatly improves the static and dynamic supporting performance of the large-caliber back three-point supporting reflector component. The structure can effectively support the space-based large-aperture reflector with the aperture of 2m and the aperture below the same.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the application and together with the description serve to explain the application and not to limit the application. In the drawings:
FIG. 1 is a rear view of a prior art spatial remote sensor mirror assembly;
FIG. 2 is a cross-sectional view of a prior art spatial remote sensor mirror assembly taken along the direction C-C;
FIG. 3 is a schematic view of the flexible segment structure of FIG. 1;
FIG. 4 is a rear view of a support structure for a large aperture mirror assembly of a space remote sensor as provided herein;
FIG. 5 provides a cross-sectional view in the direction C-C of the cross-section of the view of FIG. 4 in the present application;
FIG. 6 is a schematic view of a flexible segment structure of the present application;
FIG. 7 is a schematic view of a flexible joint structure added with a non-metallic viscoelastic damping material according to the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the technical solutions of the present application will be described in detail and completely with reference to the following specific embodiments of the present application and the accompanying drawings. It should be apparent that the described embodiments are only some of the embodiments of the present application, and not all of the embodiments.
This application mainly provides a neotype support theory to back three point support in the passive bearing structure form, the bearing structure of space remote sensor heavy-calibre reflector component of this application, including speculum, three flexible supporting components of group, evenly set up three taper hole around the circumferencial direction on the speculum, three flexible supporting components of group set up respectively in the taper hole.
The flexible supporting component comprises a taper sleeve and a flexible joint, the taper sleeve is matched with the taper hole, the taper sleeve is fixed through a screw and a pin, and one end of the flexible joint is connected with the reflector through the screw.
The flexible joint comprises a connecting plate, a hollow cylinder and a flexible head, wherein a necking down is arranged between the hollow cylinder and the flexible head, and the necking down is of a hyperboloid structure.
The flexible head is provided with an axial flexible groove.
And a repairing and grinding pad is arranged on the outer side of the connecting plate of the flexible joint and is connected with the connecting plate through a screw.
And non-metal viscoelastic damping materials are arranged around the necking and in the axial flexible groove.
The nonmetal viscoelastic damping material is rubber, and the viscoelastic coefficient, the perfusion amount and the perfusion position of the rubber are determined optimally according to design indexes.
The utility model provides a gentle groove of necking down and axial of festival of metal provides better rotation compliance and radial movement compliance, other flexible structure forms relatively, and the effect is showing in the aspect of the mirror surface shape of face error change that temperature load and assembly error introduced is alleviated to this kind of structure, effectively guarantees the statics performance, matches on this basis and fuses the high damped rubber non-metallic material, increases the fundamental frequency, reduces dynamic stress, reduces the response amplitude, promotes fatigue life. The technical scheme fundamentally solves the contradiction caused by the inconsistent requirements of static and dynamic performances of the reflector assembly adopting the back three-point support on the rigidity and flexibility of the support structure, ensures that the support structure has high flexibility and large damping, greatly improves various static and dynamic performances of the reflector assembly, and realizes the back three-point high-performance (high surface shape precision and excellent dynamic performance) support of the space-based large-caliber reflector.
Example 1:
referring to fig. 4, 5, 6, and 7, a support structure of a large-aperture mirror assembly of a space remote sensor includes a mirror 9 and three sets of flexible support assemblies, wherein three taper holes are uniformly formed on the mirror 9 in the circumferential direction, and the three sets of flexible support assemblies are respectively disposed in the taper holes.
Flexible supporting component includes taper sleeve 13, gentle festival 14, the taper sleeve with the taper hole phase-match, the taper sleeve passes through the screw and the pin is fixed gentle festival, the one end of gentle festival is passed through the screw and is connected with the speculum. The flexible joint 14 comprises a connecting plate 19, a hollow cylinder 20 and a flexible head 21, wherein a necking 16 is arranged between the hollow cylinder 20 and the flexible head 21, and the necking 16 is of a hyperboloid structure.
The flexible head 21 is provided with an axial flexible groove 17. The structural dimensions of the flexible joint constriction 16 and of the axial flexible groove 17 are correlated with the design inputs of the primary mirror assembly, the design being done and the structural parameters being optimized according to the mirror dimensions, the ability to adapt to temperature loads and assembly errors.
And a repairing and grinding pad 15 is arranged on the outer side of the connecting plate 19 of the flexible joint, and the repairing and grinding pad 15 is connected with the connecting plate 19 through a screw.
A non-metallic viscoelastic damping material 18 is disposed around the constriction 16 and within the axially flexible groove.
The nonmetal viscoelastic damping material is rubber, and the viscoelastic coefficient, the perfusion amount and the perfusion position of the rubber are determined optimally according to design indexes.
The application discloses a method for assembling and implementing a support structure of a large-caliber reflector assembly of a space remote sensor, which comprises the following steps:
1. all parts are thoroughly cleaned before implementation, no impurities are guaranteed, and the assembly environment needs to be clean.
2. The large-damping non-metal rubber material is bonded around the necking 16 of the flexible joint and inside the axial flexible groove 17 shown in fig. 6 by epoxy resin glue, and the structure of the non-metal material is determined according to the suppression requirement of the reflector component on the fundamental frequency, the dynamic stress and the fatigue life requirement of the support. Rubber selection for determining a damping coefficient, the filling amount of rubber and the specific filling position of the rubber are executed strictly according to a design analysis model, and a tool matched with a specific flexible joint form is designed to assist in accurate control of the rubber amount and the filling position. And after the bonding of the composite flexible joint formed by matching and fusing the metal and the nonmetal materials is finished, curing for 1 week at normal pressure and room temperature.
3. After the composite flexible joint formed by matching and fusing the metal and the nonmetal materials is in a component integration state, the component assembly is carried out according to the structural form shown in the figures 4 and 5. The detailed assembly was carried out as follows:
and (3) fixing the flexible joint 14 and the taper sleeve 13 together by using a second screw 11, coating GD414 thread anti-loosening glue on the second screw 11, fastening the second screw 11 by using standard torque, and then matching and driving a pin between the taper sleeve 13 and the flexible joint 14, wherein the pin is also coated with the GD414 thread anti-loosening glue. The flexible segments 14 and the drogues 13 are marked. And assembling other two sets of flexible supporting components in the same step.
Epoxy resin glue is smeared on the outward bonding conical surface of the taper sleeve 13 of the three groups of flexible supporting assemblies, the taper sleeve is completely covered with the glue and is smeared uniformly, and meanwhile, epoxy resin glue is smeared on the outward bonding surface of the reflector taper hole corresponding to each group of flexible supporting assemblies, and the taper sleeve is completely covered and is smeared uniformly. And placing the three groups of flexible supporting components in corresponding taper holes, wherein the conical surfaces of the taper sleeves and the taper holes are in fit contact and are oppositely ground (clockwise or anticlockwise) for 5-8 weeks respectively along one direction.
The relative spatial position of six external connection screw holes on each flexible joint is accurately positioned by adopting the flexible joint external connection screw hole positioning tool, and the positioning tool is connected by screws and is pressed on external connection flanges of three flexible joints as a heavy object, so that firm bonding between the taper sleeve and the taper hole in the curing process is ensured. Curing at room temperature for 2 weeks at normal pressure.
After the solidification is finished, the positioning tool is taken down, three repairing and grinding pads are installed, the first screw 10 is fastened by adopting standard torque, whether the coplanarity of the end faces of the three repairing and grinding pieces is better than 0.008mm or not is detected, and otherwise, the three repairing and grinding pieces are ground. After the coplanarity meets the requirement, 18 first screws 10 for fastening the repaired piece are respectively taken down, GD414 thread anti-loosening glue is coated, and fastening and standard torque are applied.
The above description is only an example of the present application and is not intended to limit the present application. Various modifications and changes may occur to 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 scope of the claims of the present application.
Claims (7)
1. The utility model provides a bearing structure of space remote sensor heavy-calibre reflector subassembly which characterized in that, includes speculum, three flexible supporting component of group, evenly set up three taper hole around the circumferencial direction on the speculum, three flexible supporting component of group set up respectively in the taper hole.
2. The support structure of the large-aperture mirror assembly of the space remote sensor according to claim 1, wherein the flexible support assembly comprises a taper sleeve and a flexible joint, the taper sleeve is matched with the taper hole, the taper sleeve fixes the flexible joint through a screw and a pin, and one end of the flexible joint is connected with the mirror through a screw.
3. The support structure of a large-caliber reflector assembly of a space remote controller according to claim 2, wherein the flexible joint comprises a connecting plate, a hollow cylinder and a flexible head, a necking is arranged between the hollow cylinder and the flexible head, and the necking is of a hyperboloid structure.
4. A support structure for a large aperture mirror assembly for a space remote sensor according to claim 3, wherein said flexible head is provided with an axial flexible groove.
5. The support structure of a large-aperture mirror assembly for a spatial remote controller according to claim 3, wherein a grinding pad is provided on an outer side of the connection plate of the flexible joint, and the grinding pad is connected with the connection plate by a screw.
6. The support structure for a large-aperture mirror assembly of a spatial remote controller according to claim 4, wherein a non-metallic viscoelastic damping material is provided around said constriction and within said axial flexible groove.
7. The support structure of a large-aperture mirror assembly of a spatial remote controller according to claim 6, wherein the non-metallic viscoelastic damping material is rubber, and the viscoelastic coefficient, the pouring amount and the pouring position of the rubber are determined optimally according to design criteria.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010267310.5A CN111352209A (en) | 2020-04-07 | 2020-04-07 | Support structure of large-caliber reflector component of space remote sensor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010267310.5A CN111352209A (en) | 2020-04-07 | 2020-04-07 | Support structure of large-caliber reflector component of space remote sensor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111352209A true CN111352209A (en) | 2020-06-30 |
Family
ID=71196297
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010267310.5A Pending CN111352209A (en) | 2020-04-07 | 2020-04-07 | Support structure of large-caliber reflector component of space remote sensor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111352209A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112130277A (en) * | 2020-09-28 | 2020-12-25 | 吉林大学 | Flexible supporting structure suitable for space camera reflector |
| CN113640939A (en) * | 2021-07-29 | 2021-11-12 | 长光卫星技术有限公司 | Two-dimensional angle precision adjustment device for large-diameter plane reflector |
| CN114578505A (en) * | 2022-03-11 | 2022-06-03 | 中国科学院长春光学精密机械与物理研究所 | Back three-point supporting structure of space large-diameter reflector |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204009191U (en) * | 2014-06-06 | 2014-12-10 | 苏州华徕光电仪器有限公司 | A kind of heavy caliber principal reflection mirror flexible support structure |
| CN106371191A (en) * | 2016-11-28 | 2017-02-01 | 长光卫星技术有限公司 | Flexible support structure of light optical reflector |
| CN108594399A (en) * | 2018-06-08 | 2018-09-28 | 中国科学院西安光学精密机械研究所 | Supporting structure and supporting component of large-diameter reflector |
| CN109669253A (en) * | 2019-01-31 | 2019-04-23 | 中国科学院西安光学精密机械研究所 | Large caliber reflecting mirror vibration damping flexible support structure and mirror assembly |
| CN109683278A (en) * | 2019-01-30 | 2019-04-26 | 杭州电子科技大学 | Heavy caliber infrared telescope adjustable support based on gradient type porous structure |
| CN109932805A (en) * | 2019-03-04 | 2019-06-25 | 杭州电子科技大学 | A kind of large caliber reflecting mirror adaptivity method for supporting |
| CN110018550A (en) * | 2019-04-12 | 2019-07-16 | 中国科学院长春光学精密机械与物理研究所 | Assembly method, system and the device of back supported at three point space-based large caliber reflecting mirror |
-
2020
- 2020-04-07 CN CN202010267310.5A patent/CN111352209A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204009191U (en) * | 2014-06-06 | 2014-12-10 | 苏州华徕光电仪器有限公司 | A kind of heavy caliber principal reflection mirror flexible support structure |
| CN106371191A (en) * | 2016-11-28 | 2017-02-01 | 长光卫星技术有限公司 | Flexible support structure of light optical reflector |
| CN108594399A (en) * | 2018-06-08 | 2018-09-28 | 中国科学院西安光学精密机械研究所 | Supporting structure and supporting component of large-diameter reflector |
| CN109683278A (en) * | 2019-01-30 | 2019-04-26 | 杭州电子科技大学 | Heavy caliber infrared telescope adjustable support based on gradient type porous structure |
| CN109669253A (en) * | 2019-01-31 | 2019-04-23 | 中国科学院西安光学精密机械研究所 | Large caliber reflecting mirror vibration damping flexible support structure and mirror assembly |
| CN109932805A (en) * | 2019-03-04 | 2019-06-25 | 杭州电子科技大学 | A kind of large caliber reflecting mirror adaptivity method for supporting |
| CN110018550A (en) * | 2019-04-12 | 2019-07-16 | 中国科学院长春光学精密机械与物理研究所 | Assembly method, system and the device of back supported at three point space-based large caliber reflecting mirror |
Non-Patent Citations (2)
| Title |
|---|
| 江浩: "《超轻量化SiC反射镜及支撑技术研究》", 《中国科学院大学硕士论文》 * |
| 高宏伟: "《电子封装工艺与装备技术基础教程》", 30 June 2017, 西安电子科技大学出版社 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112130277A (en) * | 2020-09-28 | 2020-12-25 | 吉林大学 | Flexible supporting structure suitable for space camera reflector |
| CN112130277B (en) * | 2020-09-28 | 2021-06-25 | 吉林大学 | Flexible supporting structure suitable for space camera reflector |
| CN113640939A (en) * | 2021-07-29 | 2021-11-12 | 长光卫星技术有限公司 | Two-dimensional angle precision adjustment device for large-diameter plane reflector |
| CN113640939B (en) * | 2021-07-29 | 2023-06-23 | 长光卫星技术股份有限公司 | Two-dimensional angle precise adjustment device for large-caliber plane mirror |
| CN114578505A (en) * | 2022-03-11 | 2022-06-03 | 中国科学院长春光学精密机械与物理研究所 | Back three-point supporting structure of space large-diameter reflector |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111352209A (en) | Support structure of large-caliber reflector component of space remote sensor | |
| CN109239887B (en) | Flexible supporting structure for large circular reflector of space optical remote sensor | |
| CN109633859B (en) | Large-caliber optical reflector with back flexible supporting structure | |
| CN103969788B (en) | A kind of side flexible support structure of space optical remote sensor circular reflector | |
| CN106371191B (en) | The flexible support structure of light optical reflecting mirror | |
| JP6214773B2 (en) | Optimal kinematic mount for large mirrors | |
| CN107310821B (en) | Propellant storage tank skirt mounting structure and manufacturing method thereof | |
| US20090314426A1 (en) | Bolted joint | |
| CN209311766U (en) | Large-caliber optical reflector with back flexible supporting structure | |
| CN114200634B (en) | Directional reflector assembly of space camera | |
| CN110412714B (en) | Large-diameter reflector supporting mechanism | |
| CN115903170B (en) | Double-shaft flexible supporting structure of large-caliber strip-shaped reflecting mirror | |
| CN218726009U (en) | Composite material pipe large-load tensile test fixture | |
| CN114578505B (en) | Back three-point supporting structure of space large-diameter reflector | |
| CN206429507U (en) | M64 internal and external threads sleeve bolt connection components | |
| CN209021586U (en) | Center line correction clamp for tracked vehicle transmission device | |
| US11534984B2 (en) | Hybrid metallic/composite joint with integral bearing | |
| CN112130277B (en) | Flexible supporting structure suitable for space camera reflector | |
| CN111232249A (en) | Support structure suitable for satellite orbital transfer engine | |
| CN114355554A (en) | Aerospace lightweight reflector assembly and assembling method | |
| CN114326013B (en) | Primary mirror assembly for tilt measurement camera | |
| CN109911251B (en) | Multipurpose tool for heat-proof and bearing integrated structure of return airship | |
| JPS60175900A (en) | Tension and compression supporter | |
| CN220490080U (en) | Bush bonding and storing pier | |
| CN112610574B (en) | Metal reinforcing component for ceramic matrix composite material support and support assembling method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200630 |