CN104071358A - Supporting device of honeycomb plate - Google Patents
Supporting device of honeycomb plate Download PDFInfo
- Publication number
- CN104071358A CN104071358A CN201410229835.4A CN201410229835A CN104071358A CN 104071358 A CN104071358 A CN 104071358A CN 201410229835 A CN201410229835 A CN 201410229835A CN 104071358 A CN104071358 A CN 104071358A
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- China
- Prior art keywords
- bracing frame
- bending block
- bracing
- strutting arrangement
- embedded part
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Abstract
The invention provides a supporting device of a honeycomb plate. The supporting device of the honeycomb plate comprises a first supporting frame and a second supporting frame, wherein the top end surfaces of the first supporting frame and the second supporting frame are respectively connected with the honeycomb plate to be used for supporting the honeycomb plate, the side surfaces of the first supporting frame and the second supporting frame are respectively connected with an outer bearing plate to be used for dispersing the stress of the honeycomb plate onto the outer bearing plate, the first supporting frame and the second supporting frame are arranged to form an angle so as to disperse the stress of the honeycomb plate in different directions. The supporting device has the advantages that the first supporting frame and the second supporting frame are arranged to form an angle so as to support the honeycomb plate, so that the stress of the honeycomb plate in different directions can be dispersed, a local damage caused by the concentrated force loading to the honeycomb plate is avoided, and the vibration response of an outer instrument mounted on the honeycomb plate is reduced.
Description
Technical field
The present invention relates to space technology field, relate in particular to the bracing or strutting arrangement of a kind of space flight bending block.
Background technology
The structure of satellite organically links together the unit of each subsystem, instrument and parts, a good working foundation is provided to each subsystem, form a complete satellite, can bear rocket launching and the satellite and the rocket simultaneously and separate the examination of the mechanical environment producing.
The installation of the instrument and equipment on satellite has two kinds of modes conventionally: one is mounted on the cabin plate of satellite structure; Two are mounted on aluminum alloy or magnesium alloy bracket, and support is arranged on the plate of cabin again.Instrument and equipment or support are connected by the embedded part on bending block with bending block.The selection of the material of embedded part needs consideration, and the material of embedded part and the compatibility of cellular board material, to ensure the quality of solidification by cement.In design, general aluminium alloy is as the body of embedded part, then inlays steel-wire screw-socket, while having special requirement, also can select titanium alloy and stainless steel material directly to make the embedded part with connecting screw hole.At the position that is subject to larger concentrated force, for avoiding bending block local failure, can take local enhancement measure, local enhancement methods has conventionally: encrypt honeycomb core, fill rigid foam or local panel enhancing etc.
When the lower instrument and equipment of large-scale instrument and equipment or rigidity is installed on bending block, in the time of satellite launch powered-flight phase, the response meeting of instrument and equipment is larger, cause the concentrated force on bending block can be very large, bending block is local can be destroyed, instrument and equipment there will be loosening performance to be affected, and even occurs the damage phenomenon that comes off when serious.
Therefore the bracing or strutting arrangement of exploring the novel bending block that the instrument and equipment to vibration sensing is installed, by further effectively expanding the install instruments kind of equipment of satellite, will greatly improve the science using value of satellite.
Summary of the invention
Technical matters to be solved by this invention is, a kind of bracing or strutting arrangement of bending block is provided, and it not only can avoid the local failure of the bending block causing due to concentrated force load, but also can reduce the vibratory response that is arranged on the external instrument on described bending block.
In order to address the above problem, the invention provides a kind of bracing or strutting arrangement of bending block, comprise the first bracing frame and the second bracing frame, the top end face of described the first bracing frame and described the second bracing frame is connected with described bending block respectively, in order to support described bending block, the side of described the first bracing frame and described the second bracing frame is connected with outside force bearing plate respectively, in order to by the force dispersion of described bending block on described outside force bearing plate, described the first bracing frame and described the second bracing frame are an angle setting, to disperse the stressed of described bending block different directions.
Further, described the first bracing frame and vertical setting of described the second bracing frame, to disperse stressed in X and Y-direction of described bending block.
Further, described the first bracing frame and the second bracing frame are all symmetrical arranged in pairs.
Further, at least one in described the first bracing frame and the second bracing frame comprises side rib, and described side rib connects described top end face and described side.
Further, be provided with embedded part framework in described bending block, described embedded part framework is connected with outside satellite main structure, and external instrument is connected with described embedded part framework, the tensile strength of described embedded part framework attachment face on bending block for increasing described external instrument.
Further, described embedded part framework adopts carbon fiber to make.
Further, at least one in described the first bracing frame and the second bracing frame employing carbon fiber, metal or metal alloy made.
Further, at least one top and side of described the first bracing frame and the second bracing frame is provided with engraved structure, to alleviate the quality of described the first bracing frame and the second bracing frame.
The invention has the advantages that, adopt the first bracing frame and the second bracing frame to be an angle setting and support described bending block, thereby can disperse the stressed of described bending block different directions, avoid the local failure of the bending block causing due to concentrated force load, reduce the vibratory response that is arranged on the external instrument on described bending block.
Brief description of the drawings
Figure 1A is that the bracing or strutting arrangement of a kind of bending block of the present invention is arranged on the structural representation of looking up on bending block;
Figure 1B is the structural representation of the bracing or strutting arrangement of a kind of bending block of the present invention;
Fig. 2 is the structural representation of the first bracing frame;
Fig. 3 is the structural representation of the second bracing frame.
Fig. 4 is the structural representation of embedded part framework.
Detailed description of the invention
The detailed description of the invention of the bracing or strutting arrangement below in conjunction with accompanying drawing to a kind of bending block provided by the invention elaborates.
Referring to Figure 1A, Figure 1B, Fig. 2 and Fig. 3, the bracing or strutting arrangement of a kind of bending block 3 of the present invention comprises the first bracing frame 1 and the second bracing frame 2.The region of described bending block 3 can be greater than, be equal to or less than the region that described the first bracing frame 1 and the second bracing frame 2 surround, and to this, the present invention is restriction not.In this detailed description of the invention, be greater than region that described the first bracing frame 1 and the second bracing frame 2 surround taking the region of described bending block 3 and content of the present invention be described as example.
The top end face 10 of described the first bracing frame is connected with described bending block 3 respectively with the top end face 20 of described the second bracing frame, in order to support described bending block 3.Generally, external instrument (not indicating in accompanying drawing) has two kinds of connection modes with bending block, a kind of connection mode is that external instrument (not indicating in accompanying drawing) is directly installed on bending block 3, and another kind of connection mode is that external instrument passes through support (not indicating in accompanying drawing) and is connected with bending block 3.After external instrument or support are connected on bending block 3, the power that imposes on bending block 3 is born by the first bracing frame 1 and the second bracing frame 2.In this detailed description of the invention, the top end face 10 of described the first bracing frame and the top end face 20 of described the second bracing frame are fixing with described bending block 3 by attaching parts 11 and attaching parts 21 respectively.
The side 12 of described the first bracing frame and the side 22 of described the second bracing frame are connected with outside force bearing plate (not indicating in accompanying drawing) respectively, in order to by the force dispersion of described bending block 3 extremely on described outside force bearing plate.In this detailed description of the invention, the side 12 of described the first bracing frame and the side 22 of described the second bracing frame are fixed with outside force bearing plate by attaching parts 13 and attaching parts 23 respectively.After external instrument or support are connected on bending block 3, the power that imposes on bending block 3 is born by the first bracing frame 1 and the second bracing frame 2.The power that described the first bracing frame 1 and the second bracing frame 2 bear passes to the side 12 of described the first bracing frame and the side 22 of described the second bracing frame by the top end face 10 of described the first bracing frame and the top end face 20 of described the second bracing frame.Because the side 12 of described the first bracing frame and the side 22 of described the second bracing frame are connected with described outside force bearing plate, so the power that described the first bracing frame 1 and the second bracing frame 2 bear is distributed on outside force bearing plate by the side 12 of described the first bracing frame and the side 22 of described the second bracing frame, thereby can avoid the local failure of the bending block 3 causing due to concentrated force load, and can reduce the vibratory response that is arranged on the external instrument on described bending block 3.
On described bending block 3, described the first bracing frame 1 is an angle setting with described the second bracing frame 2, to disperse the stressed of described bending block 3 different directions, thereby further avoids the local failure of the bending block 3 causing due to concentrated force load.Preferably, in this detailed description of the invention, described the first bracing frame 1 and the vertical setting of the second bracing frame 2, to disperse stressed in X and Y-direction of described bending block 3.
Further, described the first bracing frame 1 and the second bracing frame 2 are all symmetrical arranged in pairs, better to support described bending block 3, and increase the area of contact of described the first bracing frame 1 and the second bracing frame 2 and bending block 3, with the local failure of the bending block 3 further avoiding causing due to concentrated force load.For example, in this detailed description of the invention, two the first bracing frames 1 are symmetrical arranged, and two the second bracing frames 2 are symmetrical arranged.
Further, at least one in described the first bracing frame 1 and the second bracing frame 2 comprises side rib 14.In this detailed description of the invention, described the first bracing frame 1 comprises two side ribs 14.Described side rib 14 connects described top end face 10 and described side 12.The quantity of described side rib is determined according to designer's demand, and the present invention is not limited this.Described side rib 14 is further transferred to described side 12 by stressed described top end face 10, and is distributed on outside force bearing plate by described side 12, reduces described top end face 10 stressed, increases the firm degree of described the first bracing frame 1.
Further, at least one top and side of described the first bracing frame 1 and the second bracing frame 2 is provided with engraved structure 24, to alleviate the quality of described the first bracing frame 1 and the second bracing frame 2.In this detailed description of the invention, the top of described the second bracing frame 2 and side are provided with engraved structure 24, to alleviate the quality of described the second bracing frame 2.The present invention is provided with engraved structure 24 at least one top and side of the first bracing frame 1 and the second bracing frame 2, under the prerequisite of intensity that does not change the first bracing frame 1 and the second bracing frame 2, alleviate the quality of described the first bracing frame 1 and the second bracing frame 2, thereby can alleviate to a certain extent described the first bracing frame 1 and the burden of the second bracing frame 2 to satellite.
Further, referring to Fig. 4, in described bending block 3, be provided with embedded part framework 4.Described embedded part framework 4 is for strengthening the tensile strength of the attachment face of external instrument (accompanying drawing does not indicate) on bending block 3.Be provided with the first connecting bore 41 being connected with outside satellite main structure at described embedded part framework 4 edges, described embedded part framework 4 is connected with outside main structure (not indicating in accompanying drawing) by the first connecting bore 41.Described outside satellite main structure refers to the members such as other structure-bearing plate of satellite or support.On the framework of described embedded part framework 4, be provided with the second connecting bore 42, described external instrument is connected with described embedded part framework 4 by the second connecting bore 42.
Further, described embedded part framework 4 adopts carbon fiber to make.Adopt that the embedded part framework 4 made of carbon fiber is lightweight, rigidity is high and it is little to be out of shape, and can strengthen the tensile strength of the attachment face of external instrument (not indicating in accompanying drawing) on bending block 3, thereby can avoid the local failure of the bending block 3 causing due to concentrated force load, reduce the vibratory response that is arranged on the external instrument on bending block 3.
Further, described the first bracing frame 1 and the second bracing frame 2 adopt at least one in carbon fiber, metal or metal alloy to make.For example, in this detailed description of the invention, described the first bracing frame 1 adopts carbon fiber to make, and described the second bracing frame 2 adopts aluminum alloy to make.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the premise without departing from the principles of the invention; can also make some improvements and modifications, these improvements and modifications also should be considered as protection scope of the present invention.
Claims (8)
1. the bracing or strutting arrangement of a bending block, it is characterized in that, comprise the first bracing frame and the second bracing frame, the top end face of described the first bracing frame and described the second bracing frame is connected with described bending block respectively, in order to support described bending block, the side of described the first bracing frame and described the second bracing frame is connected with outside force bearing plate respectively, in order to by the force dispersion of described bending block on described outside force bearing plate, described the first bracing frame and described the second bracing frame are an angle setting, to disperse the stressed of described bending block different directions.
2. the bracing or strutting arrangement of a kind of bending block according to claim 1, is characterized in that, described the first bracing frame and vertical setting of described the second bracing frame, to disperse stressed in X and Y-direction of described bending block.
3. the bracing or strutting arrangement of a kind of bending block according to claim 1, is characterized in that, described the first bracing frame and the second bracing frame are all symmetrical arranged in pairs.
4. the bracing or strutting arrangement of a kind of bending block according to claim 1, is characterized in that, at least one in described the first bracing frame and the second bracing frame comprises side rib, and described side rib connects described top end face and described side.
5. the bracing or strutting arrangement of a kind of bending block according to claim 1, it is characterized in that, in described bending block, be provided with embedded part framework, described embedded part framework is connected with outside satellite main structure, external instrument is connected with described embedded part framework, the tensile strength of described embedded part framework attachment face on bending block for increasing described external instrument.
6. the bracing or strutting arrangement of a kind of bending block according to claim 5, is characterized in that, described embedded part framework adopts carbon fiber to make.
7. the bracing or strutting arrangement of a kind of bending block according to claim 1, is characterized in that, at least one in described the first bracing frame and the second bracing frame employing carbon fiber, metal or metal alloy made.
8. the bracing or strutting arrangement of a kind of bending block according to claim 1, is characterized in that, at least one top and side of described the first bracing frame and the second bracing frame is provided with engraved structure, to alleviate the quality of described the first bracing frame and the second bracing frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410229835.4A CN104071358A (en) | 2014-05-28 | 2014-05-28 | Supporting device of honeycomb plate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410229835.4A CN104071358A (en) | 2014-05-28 | 2014-05-28 | Supporting device of honeycomb plate |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104071358A true CN104071358A (en) | 2014-10-01 |
Family
ID=51593041
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410229835.4A Pending CN104071358A (en) | 2014-05-28 | 2014-05-28 | Supporting device of honeycomb plate |
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| CN (1) | CN104071358A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111874558A (en) * | 2020-07-30 | 2020-11-03 | 航天特种材料及工艺技术研究所 | High-rigidity light-weight composite material bracket and manufacturing method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6012680A (en) * | 1997-06-27 | 2000-01-11 | Mcdonnell Douglas Corporation | Passive lateral vibration isolation system for a spacecraft launch vehicle |
| US6148740A (en) * | 1998-11-04 | 2000-11-21 | Daimlerchrysler Aerospace Ag | Load carrying lightweight pallet for spacecraft |
| KR100775989B1 (en) * | 2006-12-26 | 2007-11-15 | 한국항공우주연구원 | Supporting apparatus of sar of satellite |
| CN103075629A (en) * | 2011-10-26 | 2013-05-01 | 上海卫星工程研究所 | Large-sized embedded complicated small-deformation framework cellular board |
| CN103287588A (en) * | 2013-04-25 | 2013-09-11 | 上海卫星工程研究所 | High-carrying-capacity embedded frame composite material structural slab |
-
2014
- 2014-05-28 CN CN201410229835.4A patent/CN104071358A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6012680A (en) * | 1997-06-27 | 2000-01-11 | Mcdonnell Douglas Corporation | Passive lateral vibration isolation system for a spacecraft launch vehicle |
| US6148740A (en) * | 1998-11-04 | 2000-11-21 | Daimlerchrysler Aerospace Ag | Load carrying lightweight pallet for spacecraft |
| KR100775989B1 (en) * | 2006-12-26 | 2007-11-15 | 한국항공우주연구원 | Supporting apparatus of sar of satellite |
| CN103075629A (en) * | 2011-10-26 | 2013-05-01 | 上海卫星工程研究所 | Large-sized embedded complicated small-deformation framework cellular board |
| CN103287588A (en) * | 2013-04-25 | 2013-09-11 | 上海卫星工程研究所 | High-carrying-capacity embedded frame composite material structural slab |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111874558A (en) * | 2020-07-30 | 2020-11-03 | 航天特种材料及工艺技术研究所 | High-rigidity light-weight composite material bracket and manufacturing method thereof |
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Application publication date: 20141001 |