CN111409875A - Composite material bearing structure suitable for space vehicle separation cabin section - Google Patents
Composite material bearing structure suitable for space vehicle separation cabin section Download PDFInfo
- Publication number
- CN111409875A CN111409875A CN202010197369.1A CN202010197369A CN111409875A CN 111409875 A CN111409875 A CN 111409875A CN 202010197369 A CN202010197369 A CN 202010197369A CN 111409875 A CN111409875 A CN 111409875A
- Authority
- CN
- China
- Prior art keywords
- separation
- nut
- box
- end frame
- angle box
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Springs (AREA)
Abstract
The invention provides a composite material bearing structure suitable for a space vehicle separation cabin, which comprises: the device comprises a separation nut angle box 1, a separation nut angle box cover 2, a shear-resistant taper sleeve 3, a separation spring angle box 5 and an upper end frame 6; the separation nut angle box cover 2 is tightly connected with the separation nut angle box 1; the upper end frame 6 is arranged at the upper part of the separation nut angle box 1; the shear-resistant taper sleeve 3 penetrates through the upper end frame 6 to be connected with the separation nut angle box 1; the separation spring angle box 5 is mounted on the upper end frame 6. According to the corner box and the end frame made of the composite material, the rigidity and the strength of the bearing structure are enhanced, the structural quality is reduced, and the bearing capacity of the structure is improved.
Description
Technical Field
The invention relates to the field of spacecrafts, in particular to a composite material bearing structure applicable to separation cabin sections of a spacecraft.
Background
At present, on-orbit separation spacecrafts are often separated through initiating explosive devices (such as separation nuts and the like), however, the separation mode can generate larger impact on connection structures among the spacecrafts, so that connection parts of the spacecrafts bear various load effects of tension, compression, bending, shearing and the like, and high requirements are provided for connection bearing structures among the spacecrafts. In order to improve the bearing capacity of the connection structure, the angle box is commonly used in the spacecraft at present to enhance the rigidity and the strength of the connection structure between the spacecrafts, and meanwhile, the angle box provides the installation space of initiating explosive devices. In addition to this, such structures can also transfer part of the impact-generated loads to the force-bearing structures of the spacecraft. The traditional connection structure between spacecraft cabins as disclosed in patent document CN204021262U comprises a first cabin body and a second cabin body which need to be connected, wherein a first groove is formed in the first cabin body, a second groove is formed in the second cabin body, the first groove and the second groove are corresponding in position, an open-ended spring collar is clamped on the first groove, a plurality of threaded holes are formed in the spring washer along the radial direction, the spring washer further comprises a plurality of set screws, the set screws penetrate through the second groove and are matched with the threaded holes, when the first cabin body and the second cabin body need to be connected, the set screws are rotated, and the spring collar is expanded to the side wall of the spring collar to be inconsistent with the side wall of the second groove.
However, the structure of the prior art has large weight, low rigidity and strength, and greatly limits the performance of the separated spacecraft.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a composite material bearing structure suitable for a separation cabin section of a spacecraft.
According to the invention, the composite material bearing structure suitable for the separation cabin section of the spacecraft comprises: the device comprises a separation nut angle box 1, a separation nut angle box cover 2, a shear-resistant taper sleeve 3, a separation spring angle box 5 and an upper end frame 6;
the separation nut angle box cover 2 is tightly connected with the separation nut angle box 1;
the upper end frame 6 is arranged at the upper part of the separation nut angle box 1;
the shear-resistant taper sleeve 3 penetrates through the upper end frame 6 to be connected with the separation nut angle box 1;
the separation spring angle box 5 is mounted on the upper end frame 6.
Preferably, the split nut angle box 1 comprises: a separation nut corner box bottom plate 101, a separation nut corner box side plate 102 and a separation nut corner box top plate 103;
the separation nut angle box bottom plate 101 is fixedly connected with the upper end frame 6;
the separation nut angle box side plate 102 is tightly connected with the separation nut angle box cover 2;
the separation nut corner box top plate 103 is connected with the separation nut corner box bottom plate 101 and the separation nut corner box side plate 102.
Preferably, the separation spring angle box 5 comprises: a separation spring corner box bottom plate 501 and a separation spring corner box side plate 502;
the separation spring corner box bottom plate 501 is connected with the upper end frame 6;
the separation spring corner box side plate 502 is connected with the separation spring corner box bottom plate 501.
Preferably, a separation spring corner box reinforcing rib 503 is arranged between the separation spring corner box bottom plate 501 and the separation spring corner box side plate 502.
Preferably, an interface is arranged on the upper end frame 6.
Preferably, the shear-resistant taper sleeve 3 is made of a titanium alloy material, and the separation nut angle box 1, the separation nut angle box cover 2, the separation spring angle box 5 and the upper end frame 6 are made of composite materials.
Preferably, the separation nut angle box 1, the separation nut angle box cover 2 and the upper end frame 6 form a closed cavity.
Preferably, the separation nut angle box bottom plate 101 is provided with a nut hole.
Preferably, the inner diameter of the nut bore is equal to the outer diameter of the shear cone sleeve 3.
Preferably, the split nut angle box 1 is plural.
Compared with the prior art, the invention has the following beneficial effects:
1. through the angle box and the end frame made of the composite material, the rigidity and the strength of the bearing structure are enhanced, the structural quality is reduced, and the bearing capacity of the structure is improved.
2. The separating nut angle box is simple in structural form, reinforcing structures such as reinforcing ribs do not exist, initiating explosive devices such as separating nuts with large size can be installed, a large space is reserved for future improvement, and bearing capacity can be further enhanced.
3. The separation among the spacecrafts is realized by adding a plurality of corner boxes on the periphery of the structure, the occupied space is small, the number of adopted parts is small, and the reliability of the system is improved.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic view of a composite load bearing structure of the present invention.
Fig. 2 is a schematic structural view of a separation nut angle box.
Fig. 3 is a sectional view of the split nut angle box structure of the present invention.
Fig. 4 is a schematic view of a split spring corner box structure.
Figure 5 is a partial view of a load bearing structure.
The figures show that:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1 to 5, the present invention provides a composite material bearing structure suitable for use between spacecraft separation modules, comprising: the device comprises a separation nut angle box 1, a separation nut angle box cover 2, a shear-resistant taper sleeve 3, a separation spring angle box 5 and an upper end frame 6; the separation nut angle box cover 2 is tightly connected with the separation nut angle box 1; the upper end frame 6 is arranged at the upper part of the separation nut angle box 1; the shear-resistant taper sleeve 3 penetrates through the upper end frame 6 to be connected with the separation nut angle box 1; the separation spring angle box 5 is mounted on the upper end frame 6. In a preferred embodiment, the bottom plate of the separation nut angle box is connected with the upper end frame, the side plate perpendicular to the bottom plate is connected with the separation nut angle box cover through a fastener 4, the top plate perpendicular to the side plate is abutted against the outer wall of the end frame, a separation nut hole is reserved in the bottom plate, the shear-resistant taper sleeve 3 penetrates through the upper end frame and the bottom plate of the separation nut angle box, and the separation nut angle box cover 2, the separation nut angle box 1 and the outer wall of the end frame jointly enclose a polyhedral cavity. In a preferred embodiment, as shown in fig. 1, in order to enhance the bearing capacity of the end frame 6, a plurality of corner box supporting portions are arranged in the circumferential direction of the end frame, the number of the corner box supporting portions is more than two, the corner box supporting portions are symmetrically distributed, six corner box supporting portions are arranged in the embodiment, and each corner box supporting portion is provided with a separation nut corner box 1 and a separation spring corner box 5; and a separation nut hole is reserved on the bottom plate of the separation nut angle box, the inner diameter of the separation nut hole is equal to the outer diameter of the anti-shearing taper sleeve 3, and the anti-shearing taper sleeve 3 penetrates through the separation nut hole to be connected with the upper end frame.
The separation nut angle box 1 further comprises a separation nut angle box bottom plate 101, a separation nut angle box side plate 102 and a separation nut angle box top plate 103, the separation nut angle box bottom plate 101 is in fastening connection with an upper end frame 6, the separation nut angle box side plate 102 is in fastening connection with a separation nut angle box cover 2, the separation nut angle box top plate 103 is connected with the separation nut angle box bottom plate 101 and the separation nut angle box side plate 102, the separation spring angle box 5 comprises a separation spring angle box bottom plate 501 and a separation spring angle box side plate 502, the separation spring angle box bottom plate 501 is connected with the upper end frame 6, the separation spring angle box side plate 502 is connected with the separation spring angle box bottom plate 501, in a preferred embodiment, the separation nut angle box 1, the separation nut angle box cover 2, the separation spring angle box 5 and the upper end frame 6 are all made of an M55/cyanate composite material, in a preferred embodiment, a separation nut angle box bottom plate is provided with a 4-phi 3.1mm circle uniformly distributed on the separation nut angle box bottom plate as shown in 49.5mm circle, a separation nut angle box bottom plate is provided with a separation nut angle box bottom plate, a separation nut angle box cover 35, a separation nut angle box bottom plate is provided with a separation nut angle box cover 2, a separation nut angle box cover 3-phi 3 cone cover, a separation nut angle box cover is provided with a separation nut angle box cover 3 cone cover, a separation nut cover is provided with a through hole provided with a through hole, a through hole provided with a through hole provided with a shear nut, a.
Furthermore, a separation spring corner box reinforcing rib 503 is arranged between the separation spring corner box bottom plate 501 and the separation spring corner box side plate 502. And an interface is arranged on the upper end frame 6. The shear-resistant taper sleeve 3 is made of a titanium alloy material. The separation nut angle box 1, the separation nut angle box cover 2 and the upper end frame 6 form a closed cavity. And a nut hole is formed in the separation nut angle box bottom plate 101. The inner diameter of the nut hole is equal to the outer diameter of the shear cone sleeve 3. The number of the split nut angle boxes 1 is multiple. In a preferred embodiment, as shown in fig. 2 and 3, the shape of the corner box cover 2 of the separation nut is matched with that of the outer wall of the end frame, and the corner box cover, the corner box and the outer wall of the end frame form a polyhedral cavity. The shear-resistant taper sleeve 3 is made of titanium alloy TC 4. As shown in fig. 4, a reinforcing rib is arranged between the bottom plate and the side plate of the separation spring corner box 5 to improve the support rigidity of the structure. As shown in fig. 5, the separation nut angle box 1 and the separation spring angle box 5 are arranged on the same side of the end frame 6, the separation nut angle box 1 is connected with the end frame 6 through a rivet, and the separation spring angle box 5 is connected with the end frame 6 through high-strength structural adhesive.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A composite load bearing structure adapted for use between spacecraft separation bay sections, comprising: the device comprises a separation nut angle box (1), a separation nut angle box cover (2), a shear-resistant taper sleeve (3), a separation spring angle box (5) and an upper end frame (6);
the separation nut angle box cover (2) is tightly connected with the separation nut angle box (1);
the upper end frame (6) is arranged on the upper part of the separation nut angle box (1);
the shear-resistant taper sleeve (3) penetrates through the upper end frame (6) to be connected with the separation nut angle box (1);
the separation spring angle box (5) is arranged on the upper end frame (6).
2. The composite material bearing structure suitable for spacecraft separation bay sections according to claim 1, wherein said split nut corner box (1) comprises: a separation nut corner box bottom plate (101), a separation nut corner box side plate (102) and a separation nut corner box top plate (103);
the separation nut angle box bottom plate (101) is fixedly connected with the upper end frame (6);
the separation nut corner box side plate (102) is tightly connected with the separation nut corner box cover (2);
and the separation nut corner box top plate (103) is connected with the separation nut corner box bottom plate (101) and the separation nut corner box side plate (102).
3. The composite material bearing structure adapted for use between spacecraft separation nacelle sections according to claim 1, wherein said separation spring corner box (5) comprises: a separation spring corner box bottom plate (501) and a separation spring corner box side plate (502);
the separation spring corner box bottom plate (501) is connected with the upper end frame (6);
the separation spring corner box side plate (502) is connected with the separation spring corner box bottom plate (501).
4. The composite material bearing structure suitable for spacecraft bay sections according to claim 3, wherein a separation spring corner box stiffener (503) is provided between said separation spring corner box bottom panel (501) and separation spring corner box side panel (502).
5. The composite material bearing structure adapted for use between spacecraft separation nacelle sections according to claim 1, wherein an interface is provided on the upper end frame (6).
6. The composite material bearing structure suitable for spacecraft bay sections according to claim 1, wherein said shear cone (3) is made of titanium alloy material, and said split nut angle box (1), said split nut angle box cover (2), said split spring angle box (5) and said upper end frame (6) are made of composite material.
7. The composite material bearing structure suitable for spacecraft bay sections according to claim 1, wherein said split nut corner box (1), split nut corner box cover (2) and upper end frame (6) form a closed cavity.
8. Composite material carrying structure suitable for spacecraft bay sections according to claim 2, characterised in that the separation nut corner box base plate (101) is provided with nut holes.
9. The composite material bearing structure adapted for use between spacecraft separation nacelle sections according to claim 8, wherein the inner diameter of the nut bore is equal to the outer diameter of the shear cone sleeve (3).
10. The composite material bearing structure adapted for use between spacecraft separation nacelle sections according to claim 1, wherein the split nut angle boxes (1) are plural.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010197369.1A CN111409875A (en) | 2020-03-19 | 2020-03-19 | Composite material bearing structure suitable for space vehicle separation cabin section |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010197369.1A CN111409875A (en) | 2020-03-19 | 2020-03-19 | Composite material bearing structure suitable for space vehicle separation cabin section |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111409875A true CN111409875A (en) | 2020-07-14 |
Family
ID=71489121
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010197369.1A Pending CN111409875A (en) | 2020-03-19 | 2020-03-19 | Composite material bearing structure suitable for space vehicle separation cabin section |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111409875A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112610574A (en) * | 2020-12-14 | 2021-04-06 | 西安鑫垚陶瓷复合材料有限公司 | Metal reinforcing component for ceramic matrix composite material support and support assembling method |
Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105659882B (en) * | 2009-09-29 | 2013-05-08 | 北京空间飞行器总体设计部 | Space interlock compresses relieving mechanism |
| EP2671803A2 (en) * | 2012-06-07 | 2013-12-11 | The Boeing Company | System and method for interconnecting dual manifested spacecraft |
| CN103963997A (en) * | 2014-05-06 | 2014-08-06 | 上海卫星工程研究所 | Small satellite polygonal force bearing barrel |
| CN104401508A (en) * | 2014-10-27 | 2015-03-11 | 北京空间飞行器总体设计部 | Cross bracing main structure for spacecraft |
| CN204223195U (en) * | 2014-10-31 | 2015-03-25 | 北京宇航系统工程研究所 | Discrete point type satellite adapter |
| CN204279982U (en) * | 2014-09-26 | 2015-04-22 | 中国运载火箭技术研究院 | A kind of at orbit aerocraft tank connecting device |
| CN204788080U (en) * | 2015-06-12 | 2015-11-18 | 北京宇航系统工程研究所 | Eight claw roof beam overall structure of large -scale thin wall |
| CN204881355U (en) * | 2015-06-19 | 2015-12-16 | 北京宇航系统工程研究所 | Compound explosion bolt box structure |
| CN105253331A (en) * | 2015-09-10 | 2016-01-20 | 北京空间飞行器总体设计部 | Force-limited compaction releasing mechanism |
| CN106152885A (en) * | 2016-07-06 | 2016-11-23 | 大连理工大学 | A kind of new and effective lightweight space flight blasting bolt box |
| CN107323698A (en) * | 2017-05-18 | 2017-11-07 | 上海卫星工程研究所 | Satellite-rocket docking uses the load barrel structure of composite end frame |
| CN107543014A (en) * | 2017-09-06 | 2018-01-05 | 北京空间飞行器总体设计部 | A kind of two valve thin shell type high stable integral structures |
| CN108534615A (en) * | 2018-03-13 | 2018-09-14 | 北京宇航系统工程研究所 | Blasting bolt protective device for slowing down operational fragment and blasting bolt system |
| CN107253337B (en) * | 2017-08-16 | 2019-04-12 | 哈尔滨工业大学 | A kind of blasting bolt box and preparation method thereof |
| CN109823576A (en) * | 2019-02-20 | 2019-05-31 | 上海卫星工程研究所 | Bearer connection structure for planetary landing device |
| CN109911246A (en) * | 2019-02-20 | 2019-06-21 | 上海卫星工程研究所 | Spacecraft composite structure is connected suitable for point type |
| CN110228608A (en) * | 2019-05-24 | 2019-09-13 | 上海宇航系统工程研究所 | A kind of point type connection separator being adapted to side hanging satellite |
| CN209818634U (en) * | 2019-01-22 | 2019-12-20 | 蓝箭航天空间科技股份有限公司 | Energy-absorbing shock-absorbing structure of point type separation |
-
2020
- 2020-03-19 CN CN202010197369.1A patent/CN111409875A/en active Pending
Patent Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105659882B (en) * | 2009-09-29 | 2013-05-08 | 北京空间飞行器总体设计部 | Space interlock compresses relieving mechanism |
| EP2671803A2 (en) * | 2012-06-07 | 2013-12-11 | The Boeing Company | System and method for interconnecting dual manifested spacecraft |
| CN103963997A (en) * | 2014-05-06 | 2014-08-06 | 上海卫星工程研究所 | Small satellite polygonal force bearing barrel |
| CN204279982U (en) * | 2014-09-26 | 2015-04-22 | 中国运载火箭技术研究院 | A kind of at orbit aerocraft tank connecting device |
| CN104401508A (en) * | 2014-10-27 | 2015-03-11 | 北京空间飞行器总体设计部 | Cross bracing main structure for spacecraft |
| CN204223195U (en) * | 2014-10-31 | 2015-03-25 | 北京宇航系统工程研究所 | Discrete point type satellite adapter |
| CN204788080U (en) * | 2015-06-12 | 2015-11-18 | 北京宇航系统工程研究所 | Eight claw roof beam overall structure of large -scale thin wall |
| CN204881355U (en) * | 2015-06-19 | 2015-12-16 | 北京宇航系统工程研究所 | Compound explosion bolt box structure |
| CN105253331A (en) * | 2015-09-10 | 2016-01-20 | 北京空间飞行器总体设计部 | Force-limited compaction releasing mechanism |
| CN106152885A (en) * | 2016-07-06 | 2016-11-23 | 大连理工大学 | A kind of new and effective lightweight space flight blasting bolt box |
| CN107323698A (en) * | 2017-05-18 | 2017-11-07 | 上海卫星工程研究所 | Satellite-rocket docking uses the load barrel structure of composite end frame |
| CN107253337B (en) * | 2017-08-16 | 2019-04-12 | 哈尔滨工业大学 | A kind of blasting bolt box and preparation method thereof |
| CN107543014A (en) * | 2017-09-06 | 2018-01-05 | 北京空间飞行器总体设计部 | A kind of two valve thin shell type high stable integral structures |
| CN108534615A (en) * | 2018-03-13 | 2018-09-14 | 北京宇航系统工程研究所 | Blasting bolt protective device for slowing down operational fragment and blasting bolt system |
| CN209818634U (en) * | 2019-01-22 | 2019-12-20 | 蓝箭航天空间科技股份有限公司 | Energy-absorbing shock-absorbing structure of point type separation |
| CN109823576A (en) * | 2019-02-20 | 2019-05-31 | 上海卫星工程研究所 | Bearer connection structure for planetary landing device |
| CN109911246A (en) * | 2019-02-20 | 2019-06-21 | 上海卫星工程研究所 | Spacecraft composite structure is connected suitable for point type |
| CN110228608A (en) * | 2019-05-24 | 2019-09-13 | 上海宇航系统工程研究所 | A kind of point type connection separator being adapted to side hanging satellite |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112610574A (en) * | 2020-12-14 | 2021-04-06 | 西安鑫垚陶瓷复合材料有限公司 | Metal reinforcing component for ceramic matrix composite material support and support assembling method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9718566B2 (en) | Stackable satellites and method of stacking same | |
| JP7145975B2 (en) | Efficient satellite architecture concepts for single or stacked multiple launches | |
| US20180201396A1 (en) | Multiple space vehicle launch system | |
| CN112591144B (en) | Laminated satellite array configuration and transmitting method thereof | |
| CN110466801B (en) | Aircraft cabin structure | |
| US20210179197A1 (en) | Side sill structure for vehicle | |
| CN111409875A (en) | Composite material bearing structure suitable for space vehicle separation cabin section | |
| CN111023913A (en) | Carrier rocket final-stage structure | |
| CN109911246B (en) | Composite material structure suitable for point-type connection spacecraft | |
| CN109050989A (en) | A kind of double star point type adapter | |
| WO1999000299A1 (en) | Passive lateral vibration isolation system for a spacecraft launch vehicle | |
| CN109941459A (en) | A kind of satellite configuration and satellite | |
| CN112857154A (en) | Solid power instrument cabin of carrier rocket | |
| US11628921B2 (en) | Aircraft fuselage and module for absorbing crash energy in a lower deck, used for transporting passengers, of an aircraft | |
| CN102556352A (en) | Adapter and method for installing monuments | |
| KR100775989B1 (en) | Supporting apparatus of sar of satellite | |
| CN204776080U (en) | Double star parallels emitter of asymmetric overall arrangement | |
| US10391918B2 (en) | Load bearing rail and tie-down ring assembly | |
| CN211696095U (en) | Carrier rocket final-stage structure | |
| US6038736A (en) | Hinge for deployable truss | |
| CN111470069B (en) | Lower end frame structure suitable for satellite bearing cylinder | |
| US20220106064A1 (en) | Launch vehicle dispenser attach structure and method | |
| US11242161B1 (en) | Cube-shaped primary structure module | |
| CN218718094U (en) | Earless moving supporting plate nut component | |
| US20210284318A1 (en) | Pivot fittings back up beam architecture |
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: 20200714 |