CN107484404B - High-strength aviation anti-impact anti-seismic shielding case - Google Patents
High-strength aviation anti-impact anti-seismic shielding case Download PDFInfo
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- CN107484404B CN107484404B CN201710874114.2A CN201710874114A CN107484404B CN 107484404 B CN107484404 B CN 107484404B CN 201710874114 A CN201710874114 A CN 201710874114A CN 107484404 B CN107484404 B CN 107484404B
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K9/00—Screening of apparatus or components against electric or magnetic fields
- H05K9/0007—Casings
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K5/00—Casings, cabinets or drawers for electric apparatus
- H05K5/02—Details
- H05K5/0217—Mechanical details of casings
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/18—Construction of rack or frame
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K9/00—Screening of apparatus or components against electric or magnetic fields
- H05K9/0007—Casings
- H05K9/0009—Casings with provisions to reduce EMI leakage through the joining parts
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
Abstract
The invention discloses a high-strength aviation anti-impact anti-seismic shielding case, which relates to the technical field of aviation shielding case equipment, and comprises two side plates (1) and a rectangular frame (2) which are parallel to each other, wherein the rectangular frame (2) is arranged between the side plates (1) in parallel; the rectangular frame (2) comprises a closed cross beam (3) and a reinforced vertical beam (4), and the closed cross beam (3) and the reinforced vertical beam (4) are connected through riveting blocks to form the rectangular frame (2); the closed cross beam (3) comprises a cross beam main body (31), a round bottom hole (32) for installing a steel wire thread sleeve and a flat hole (33) for installing a riveting block (5) are formed in the cross beam main body (31), a special-shaped hole (34) for installing a nut strip (6) is formed in the cross beam main body (31), and the special-shaped hole (34) is located on the inner side of the cross beam main body (31). The invention has the advantages of ensuring the overall strength of the cross beam main body and the reinforced vertical beam and improving the working stability of the aviation anti-seismic shielding case.
Description
Technical Field
The invention relates to the technical field of aviation shielding case equipment, in particular to a high-strength aviation anti-impact anti-seismic shielding case.
Background
The airborne electronic equipment is an important component of the aircraft, and is often subjected to vibration and impact forces caused by factors such as an engine of the aircraft, aerodynamic turbulence outside the aircraft, flight attitude of the aircraft, take-off, landing, taxiing and the like in the use process. If the equipment is poor in self-resistance, faults can be generated due to the vibration and impact effects in the using process, so that the performance of the whole aircraft is affected. In general, there are two cases where a device is broken down, one is that resonance occurs at a certain frequency point, so that the amplitude of the device is increased, and finally the device is broken down beyond the limit acceleration of the device, and the other is that vibration and impact acceleration do not exceed the limit acceleration to which the device is subjected, but the device is broken down due to fatigue due to long-term vibration. The chassis is particularly important as a carrier of the electronic device, and in order to ensure the reliability of the electronic device, the chassis must be designed to resist vibration and shock. The vibration environment condition that airborne electronic equipment works is abominable, and the machine case is its main carrier, consequently need consolidate the machine case on the structure, adopts shock insulation buffer system to improve its vibration resistance simultaneously to improve whole airborne electronic equipment's reliability and life.
In the aviation anti-seismic shielding case in the prior art, the structural form is formed by adopting a cross beam, a cover plate, side plates and other component frameworks, the structural form is simple and practical, but the stability is relatively poor, because the number of instruments in the aviation anti-seismic shielding case is large, the positions to be connected are relatively large, when other components are required to be connected, the components are usually directly drilled and welded on the cross beam or the side plates, and when the number of holes of main stress points is large, the mechanical property of the whole case is affected, and huge hidden danger is brought to aviation flight safety.
Disclosure of Invention
The invention aims at: the invention provides a high-strength aviation anti-impact anti-seismic shielding case, which aims to solve the problems that in the prior art, the aviation shielding case is single in structural form, more in holes and easy to cause the reduction of structural strength of a case body and impact resistance of the case body.
The invention adopts the following technical scheme for realizing the purposes:
comprises two parallel side plates (1) and a rectangular frame (2):
the rectangular frame (2) is arranged between the side plates (1) in parallel, the rectangular frame (2) comprises a closed cross beam (3) and a reinforced vertical beam (4), and the closed cross beam (3) and the reinforced vertical beam (4) are connected through a riveting block (5) to form the rectangular frame (2); two groups of rectangular frames (2) are arranged in a box body, and each group of rectangular frames (2) comprises two closed cross beams (3) and two reinforcing vertical beams 4;
the closed cross beam (3) comprises a cross beam main body (31), a round bottom hole (32) for installing a steel wire thread sleeve (321) and a flat hole (33) for installing a riveting block (5) are formed in the cross beam main body (31), a special-shaped hole (34) for installing a nut strip (6) is formed in the cross beam main body (31), and the special-shaped hole (34) is located at the inner side of the cross beam main body (31);
the reinforcing vertical beam (4) comprises an X-axis mounting plate (41) used for being connected with the closed cross beam (3), a Y-axis mounting plate (42) used for mounting a handle, and reinforcing rib plates (43) used for reinforcing the X-axis mounting plate (41) and the Y-axis mounting plate (42), wherein the X-axis mounting plate (41) is vertically connected with the Y-axis mounting plate (42), and the reinforcing rib plates (43) are respectively connected with the X-axis mounting plate (41) and the Y-axis mounting plate (42).
Preferably, spigot positioning grooves (35) for shielding electromagnetic interference are formed at both ends of the beam main body (31).
Preferably, the special-shaped hole (34) comprises a rectangular part (341) and an arc-shaped part (342), the rectangular part (341) is positioned on the inner side of the beam main body (31), and the distance from the rectangular part (341) to the inner side edge of the beam main body (31) is 5mm-6mm.
Preferably, the reinforcing vertical beam (4) further comprises a folding line type clamping groove (44) for installing the front baffle plate and the rear baffle plate, and the folding line type clamping groove (44) is installed on the inner side of the reinforcing rib plate (43).
Preferably, the closed cross beam (3) and the reinforced vertical beam (4) are manufactured by integrally extruding and forming six-series aluminum alloy.
The beneficial effects of the invention are as follows:
1. because the aviation anti-seismic shielding case has more internal components, various different components are required to be connected in the case, but the case in the prior art is usually provided with other components by directly punching holes on a sheet-shaped cross beam and a side plate; according to the box body structure, the common connecting pieces in the machine box are integrated into the closed cross beam and the reinforced vertical beam, so that the continuity of the upper side and the lower side of the cross beam main body and the reinforced vertical beam is guaranteed, the overall rigidity of the box body structure is guaranteed, the mechanical properties required by design are maintained, when other components are required to be connected to the cross beam main body and the reinforced vertical beam, the box body structure is installed through reserved various mounting holes, the drilling operation on the main stress areas of the cross beam main body and the reinforced vertical beam is not required, the overall strength of the cross beam main body and the reinforced vertical beam is guaranteed, and the working stability of the aviation anti-seismic shielding machine box is improved.
2. The electronic components in the box body are numerous, electromagnetic interference generated by the electronic components is large, and the unnecessary interference needs to be shielded in the flight process of an aviation aircraft, a large number of grounding copper bar wires are connected to the end part of the traditional cross beam, so that the electromagnetic interference can be effectively sealed in the box body, and when the aircraft vibrates, the grounding copper bars can follow vibration, and the electromagnetic interference is easy to loosen, so that the electromagnetic interference is leaked; according to the invention, the spigot locating groove is designed at the end part of the cross beam, the convex spigot and the concave spigot are matched and clamped, and an unnecessary connecting piece is not needed, so that the connecting part of the end part of the cross beam is more stable, is not easy to separate in vibration, and keeps the continuity of current, thereby effectively shielding electromagnetic interference, saving a grounding copper bar wire and improving the working stability of an aviation anti-seismic shielding case.
3. The nut strip is a common connecting piece of the aviation shielding case, and various components are arranged in the aviation shielding case through the nut strip; the nut strips are arranged in the special-shaped holes on the inner side of the beam main body, when components are required to be connected, the nut strips are arranged through tapping and drilling, when the tapping and drilling are carried out, the spacing between the special-shaped holes and the inner side of the beam main body is not easy to control, and when the spacing is too large, the nut strips are not easy to drill through, and the spacing is too small, so that the structural strength is influenced; the distance from the rectangular part of the box body to the inner side edge of the beam main body is 5mm-6mm, the range value is suitable for most of aviation tapping screws, the drilling can be performed easily, the structural strength is not affected, meanwhile, when certain small parts are connected, the box body is not required to be connected with a nut strip, only the box body is required to be installed in the area through the self tapping screws, two purposes of a structure are achieved, and the box is more flexible and efficient to use.
4. The existing chassis is usually characterized in that a side plate is used as a vertical stress piece, and is welded or riveted on the side plate by utilizing a cross beam to form a stress frame, so that although materials are saved, the chassis frame needs to bear larger acceleration due to the impact of airflow disturbance and the like in aviation flight, and the side plate has limited mechanical properties and can play a certain role in shock resistance, but the side plate has risks of bending, damage and loosening due to vibration and resonance; the case is provided with the T-shaped reinforcing vertical beam structure, and the reinforcing rib plate is additionally arranged at the joint weak position of the reinforcing vertical beam structure, so that the reinforcing rib plate can effectively limit the vibration amplitude of the X-axis mounting plate and the Y-axis mounting plate when the case body vibrates, and the frame is more stable; meanwhile, the reinforced vertical beam structure can be matched with the closed cross beam to form a more stable frame structure, and the shock resistance of the box body is improved.
5. The electronic components in the box body are numerous, electromagnetic interference generated by the electronic components is more, and the aviation aircraft needs to shield the unnecessary interference in the flight process, and the traditional components of the box body are welded or riveted, especially at the corner gaps of the box body, the corner gaps are deformed due to the effects of vibration and resonance, and the electromagnetic interference easily leaks out of the gaps, so that the flight safety is affected; according to the invention, the reinforcing rib plate is designed into an L shape, the hollow channel is enclosed with the X-axis mounting plate and the Y-axis mounting plate, the hollow channel reserved at the corner of the box body can form double-layer safety with the side wall of the box body, and even if a gap exists at the corner of the box body, the side wall of the hollow channel can effectively prevent electromagnetic interference from leaking, so that the shielding performance of equipment is improved.
6. Because components in the aviation shielding box are numerous, the rear cover plate and the front cover plate of the box body are required to be convenient to detach and replace, the rear cover plate and the front cover plate of the box body in the prior art are connected with the box body frame through bolts, the bolts are required to be opened firstly for detaching the box body frame, and the bolts are connected with the box body frame when the aircraft vibrates when encountering airflow, the cover plate and the frame are easy to collide, and the box body is changed when serious, and the box body is not easy to detach; the folding line type clamping grooves are formed in the inner side of the reinforcing rib plate, and the rear cover plate and the front cover plate can be mounted conveniently and quickly by utilizing the two opposite folding line type clamping grooves to form the mounting positions.
7. The closed cross beam and the reinforced vertical beam are manufactured by integrally extruding and forming six-series aluminum alloy, and the integral extrusion and forming are adopted to ensure that the structure of the reinforced vertical beam is more stable, the mechanical property is more superior, and the impact resistance of equipment is improved.
Drawings
FIG. 1 is an overall block diagram of a high strength aviation anti-shock anti-seismic shielding case of the present invention;
FIG. 2 is a front view of the present invention;
FIG. 3 is a bottom view of the present invention;
FIG. 4 is a schematic view of a closed cross-beam structure;
FIG. 5 is a schematic view of a closed cross beam installation;
FIG. 6 is a schematic view of a reinforced mullion structure;
reference numerals: 1-side plates; 2-rectangular frames; 3-closing the cross beam; 31-a beam body; 32-a circular bottom hole; 321-a wire thread sleeve; 33-a flat hole; 34-a special-shaped hole; 341-rectangular section; 342-arc; 35-spigot positioning grooves; 4-reinforcing vertical beams; 41-X axis mounting plate; a 42-Y axis mounting plate; 43-reinforcing rib plates; 44-a folded line type clamping groove; 5-riveting blocks; 6-nut strips; 7-a bottom plate; 8-a component mounting groove; 9-connecting the middle section of the component with the beam; 11-handle.
Detailed Description
For a better understanding of the present invention, reference is made to the following description of the invention, taken in conjunction with the accompanying drawings, 1-6, and the examples below.
Example 1
As shown in fig. 1, the embodiment provides a high-strength aviation anti-impact anti-seismic shielding case, which comprises two parallel side plates 1 and a rectangular frame 2, wherein the rectangular frame 2 is arranged between the side plates 1 in parallel; the rectangular frame 2 comprises a closed cross beam 3 and a reinforced vertical beam 4, and the closed cross beam 3 and the reinforced vertical beam 4 are connected through a riveting block 5 to form the rectangular frame 2; one box comprises two groups of rectangular frames 2, and each group of rectangular frames 2 comprises two closed cross beams 3 and two reinforcing vertical beams 4.
For more clear explanation of the structure of this embodiment, the closed cross beam 3 of this embodiment includes a cross beam main body 31, a circular bottom hole 32 for installing a wire thread sleeve 321 and a flat hole 33 for installing a riveting block 5 are formed on the cross beam main body 31, and a special hole 34 for installing a nut strip 6 is formed on the inner side of the cross beam main body 31, and the special hole 34 is located on the inner side of the cross beam main body 31. As shown in fig. 6, which is a sectional view of the installation part of the rectangular frame 2 and the side plate 1 in this embodiment, through holes matched with the riveting blocks 5 are formed on the side plate 1, and the riveting blocks 5 and the flat holes 33 are used to connect the closed cross beam 3, the reinforced vertical beam 4 and the side plate 1 together. Further, in order to realize the function of shielding the box, this embodiment still includes bottom plate 7, and the both ends of bottom plate 7 are connected with two sets of rectangle frame 2 is perpendicular respectively, still are provided with multiunit components and parts mounting groove 8 that are used for installing components and parts side by side on the bottom plate 7, and the middle part of box still is provided with the components and parts middle section tie-beam 9 parallel with closed crossbeam 3, and components and parts middle section tie-beam 9 is for installing the less components and parts of overall dimension. The middle section connecting beam 9 of the component is riveted at the middle part of the side plate 1 through a riveting piece.
The working principle of this embodiment is as follows: because the aviation anti-seismic shielding case has more internal components, various different components are required to be connected in the case, but the case in the prior art is usually provided with other components by directly punching holes on a sheet-shaped cross beam and a side plate; the box structure of this embodiment, it is inside sealing crossbeam 3 and strengthening vertical beam 4 to integrate the connecting piece that is used commonly used in the quick-witted incasement, ensure the continuity on both sides about crossbeam main part 31 and strengthening vertical beam 4, thereby ensure its overall rigidity, maintain the required mechanical properties of design, when needs connect other parts on crossbeam main part 31 and strengthening vertical beam 4, utilize reserved various mounting holes install can, need not to carry out drilling operation to crossbeam main part 41 and strengthening vertical beam 4 main atress region, ensured the overall strength of crossbeam main part 31 and strengthening vertical beam 4, improved aviation antidetonation shielding machine case's job stabilization nature.
Example 2
This example was optimized on the basis of example 1 as follows: the two ends of the beam body 31 of the present embodiment are provided with the spigot positioning grooves 35 for shielding electromagnetic interference, the spigot positioning grooves 35 are divided into male and female spigots, and the shielding effect of the sides is enhanced by using the canine teeth staggered form.
The working principle of this embodiment is as follows: the electronic components in the box body are numerous, electromagnetic interference generated by the electronic components is large, and the unnecessary interference needs to be shielded in the flight process of an aviation aircraft, a large number of grounding copper bar wires are connected to the end part of the traditional cross beam, so that the electromagnetic interference can be effectively sealed in the box body, and when the aircraft vibrates, the grounding copper bars can follow vibration, and the electromagnetic interference is easy to loosen, so that the electromagnetic interference is leaked; according to the invention, the spigot locating groove 35 is designed at the end part of the cross beam, the male spigot and the female spigot are matched and clamped, and an unnecessary connecting piece is not needed, so that the connecting part of the end part of the cross beam is more stable, is not easy to separate in vibration, and keeps the continuity of current, thereby effectively shielding electromagnetic interference, saving a grounding copper bar wire and improving the working stability of an aviation anti-seismic shielding case.
Example 3
This example was optimized on the basis of example 1 as follows: the shaped hole 34 of the present embodiment includes a rectangular portion 341 and an arc portion 342, the rectangular portion 341 is located on the inner side of the beam main body 31, and the distance between the rectangular portion 341 and the inner side edge of the beam main body 31 is most preferably 5mm, and may be any value between 5mm and 6mm.
The working principle of this embodiment is as follows: the nut strip 6 is a common connecting piece of the aviation shielding case, and various components are arranged in the aviation shielding case through the nut strip 6; the nut strip 6 is arranged in the special-shaped hole 34 on the inner side of the beam main body 31, when components are required to be connected, the nut strip is arranged through tapping and drilling, when the tapping and drilling are carried out, the distance between the special-shaped hole 34 and the inner side of the beam main body 31 is not easy to control, the distance is too large, the nut strip is not easy to drill through, the distance is too small, and the structural strength is influenced; the distance from the rectangular part 341 of the box body to the inner side edge of the beam main body 31 is 5mm-6mm, the range value is suitable for most of aviation tapping screws, the drilling can be easily carried out, the structural strength is not affected, meanwhile, when certain small parts are connected, the box body does not need to be connected with a nut strip 6, only the box body is installed in the area through the self tapping screws, two purposes of a structure are achieved, and the box is more flexible and efficient to use.
Example 4
This example was optimized on the basis of any of examples 1-3 as follows: the reinforcing vertical beam 4 of the present embodiment includes an X-axis mounting plate 41 for connecting with the closed cross beam 3, a Y-axis mounting plate 42 for mounting the handle 11, and reinforcing ribs 43 for reinforcing the X-axis mounting plate 41 and the Y-axis mounting plate 42, the X-axis mounting plate 41 being connected perpendicularly to the Y-axis mounting plate 42, the reinforcing ribs 43 being connected to the X-axis mounting plate 41 and the Y-axis mounting plate 42, respectively.
Further, the reinforcing vertical beam 4 of the present embodiment further includes a fold line type clamping groove 44 for installing the front and rear shutters, and the fold line type clamping groove 44 is installed inside the reinforcing rib plate 43.
The working principle of this embodiment is as follows: the electronic components in the box body are numerous, electromagnetic interference generated by the electronic components is more, and the aviation aircraft needs to shield the unnecessary interference in the flight process, and the traditional components of the box body are welded or riveted, especially at the corner gaps of the box body, the corner gaps are deformed due to the effects of vibration and resonance, and the electromagnetic interference easily leaks out of the gaps, so that the flight safety is affected; according to the invention, the reinforcing rib plate 43 is designed into an L shape, and the hollow channel is enclosed with the X-axis mounting plate 41 and the Y-axis mounting plate 42, so that the hollow channel reserved at the corner of the box body can form double-layer insurance with the side wall of the box body, and even if a gap exists at the corner of the box body, the side wall of the hollow channel can effectively prevent electromagnetic interference from leaking, and the shielding performance of equipment is improved. Because components in the aviation shielding box are numerous, the rear cover plate and the front cover plate of the box body are required to be convenient to detach and replace, the rear cover plate and the front cover plate of the box body in the prior art are connected with the box body frame through bolts, the bolts are required to be opened firstly for detaching the box body frame, and the bolts are connected with the box body frame when the aircraft vibrates when encountering airflow, the cover plate and the frame are easy to collide, and the box body is changed when serious, and the box body is not easy to detach; according to the invention, the folding line type clamping grooves 44 are arranged on the inner side of the reinforcing rib plate 43, and the two opposite folding line type clamping grooves 44 are utilized to form the installation position, so that the installation of the rear cover plate and the front cover plate can be realized through sliding, and the installation is convenient and quick.
Example 4
This example was optimized on the basis of any of examples 1-3 as follows: the closed cross beam 3 and the reinforced vertical beam 4 are manufactured by integrally extruding and forming six-series aluminum alloy. The structure of the reinforced vertical beam is more stable by adopting integral extrusion, the mechanical property is more superior, and the impact resistance of the equipment is improved.
The above description is only a preferred embodiment of the present invention, and the patent protection scope of the present invention is defined by the claims, and all equivalent structural changes made by the specification and the drawings of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. The utility model provides a high strength aviation protection against shock antidetonation shielding machine case, includes two curb plates (1) and rectangle frame (2) that are parallel to each other, its characterized in that:
the rectangular frame (2) is arranged between the side plates (1) in parallel, the rectangular frame (2) comprises a closed cross beam (3) and a reinforced vertical beam (4), and the closed cross beam (3) and the reinforced vertical beam (4) are connected through a riveting block (5) to form the rectangular frame (2); two groups of rectangular frames (2) are arranged in a box body, and each group of rectangular frames (2) comprises two closed cross beams (3) and two reinforced vertical beams (4);
the closed cross beam (3) comprises a cross beam main body (31), a round bottom hole (32) for installing a steel wire thread sleeve (321) and a flat hole (33) for installing a riveting block (5) are formed in the cross beam main body (31), a special-shaped hole (34) for installing a nut strip (6) is formed in the cross beam main body (31), and the special-shaped hole (34) is located at the inner side of the cross beam main body (31);
the reinforcing vertical beam (4) comprises an X-axis mounting plate (41) used for being connected with the closed cross beam (3), a Y-axis mounting plate (42) used for mounting a handle, and reinforcing rib plates (43) used for reinforcing the X-axis mounting plate (41) and the Y-axis mounting plate (42), wherein the X-axis mounting plate (41) is vertically connected with the Y-axis mounting plate (42), and the reinforcing rib plates (43) are respectively connected with the X-axis mounting plate (41) and the Y-axis mounting plate (42).
2. The high strength aircraft anti-shock and anti-seismic shielding cage of claim 1, wherein: two ends of the beam main body (31) are provided with spigot positioning grooves (35) for shielding electromagnetic interference.
3. The high strength aircraft anti-shock and anti-seismic shielding cage of claim 1, wherein: the special-shaped hole (34) comprises a rectangular portion (341) and an arc-shaped portion (342), the rectangular portion (341) is located on the inner side of the beam main body (31), and the distance from the rectangular portion (341) to the inner side edge of the beam main body (31) is 5mm-6mm.
4. The high strength aircraft anti-shock and anti-seismic shielding cage of claim 1, wherein: the reinforcing vertical beam (4) further comprises a folding line type clamping groove (44) for installing the front baffle plate and the rear baffle plate, and the folding line type clamping groove (44) is installed on the inner side of the reinforcing rib plate (43).
5. The high strength aircraft anti-shock and anti-seismic shielding cage of claim 1, wherein: the closed cross beam (3) and the reinforced vertical beam (4) are manufactured by integrally extruding, forming and manufacturing six-series aluminum alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710874114.2A CN107484404B (en) | 2017-09-25 | 2017-09-25 | High-strength aviation anti-impact anti-seismic shielding case |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710874114.2A CN107484404B (en) | 2017-09-25 | 2017-09-25 | High-strength aviation anti-impact anti-seismic shielding case |
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| CN107484404A CN107484404A (en) | 2017-12-15 |
| CN107484404B true CN107484404B (en) | 2023-09-12 |
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| CN108323139A (en) * | 2017-12-25 | 2018-07-24 | 苏州江南航天机电工业有限公司 | A kind of novel van-type combination screening arrangement |
| CN109633285A (en) * | 2018-11-14 | 2019-04-16 | 中国空空导弹研究院 | A kind of missile-borne data chain device vibration-testing electromagnetism dark box device |
| CN109665122A (en) * | 2018-12-21 | 2019-04-23 | 吉林省大千电子科技有限公司 | Satellite communication power supply signal comprehensive electromagnetic protective shell |
| CN110996607B (en) * | 2019-11-21 | 2020-10-30 | 北京通畅电信规划设计院有限公司 | Indoor network covers uses antidetonation frame |
| CN111954425B (en) * | 2020-08-20 | 2021-10-26 | 广东电网有限责任公司梅州供电局 | Blade server installation method and installation device |
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