CN114554818A - Conformal structure for enhancing electromagnetic tolerance performance and method thereof - Google Patents
Conformal structure for enhancing electromagnetic tolerance performance and method thereof Download PDFInfo
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- CN114554818A CN114554818A CN202210173900.0A CN202210173900A CN114554818A CN 114554818 A CN114554818 A CN 114554818A CN 202210173900 A CN202210173900 A CN 202210173900A CN 114554818 A CN114554818 A CN 114554818A
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- H05K9/00—Screening of apparatus or components against electric or magnetic fields
- H05K9/0073—Shielding materials
- H05K9/0081—Electromagnetic shielding materials, e.g. EMI, RFI shielding
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- H—ELECTRICITY
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- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
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- H05K9/0073—Shielding materials
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Abstract
The invention discloses a conformal structure for enhancing electromagnetic resistance and a method thereof, wherein the conformal structure for enhancing electromagnetic resistance comprises a cabin plate, an optical channel structure and an optical secondary surface mirror, the optical channel structure and the optical secondary surface mirror are arranged on the cabin plate, a multilayer heat insulation assembly is laid on the outer side of the cabin plate, a cabin through hole is arranged on a second aluminum honeycomb plate, hole plugging materials are fixedly bonded around the cabin through hole through a conductive adhesive tape, and the cabin plate, the cabin through hole, the optical channel structure and the optical secondary surface mirror are respectively grounded through a multilayer edge grounding structure. A method for enhancing natural strong electromagnetic tolerance force is characterized in that a cabin-through waveguide is arranged on a cabin-through hole; plugging the inner sides of cabin-passing holes; fixing the periphery of the hole plugging material on the deck plate; fixing the center of the hole plugging material on the cabin-passing waveguide; and (4) bonding the hole plugging material and the conductive adhesive tape on the outer side, and installing the multilayer heat insulation assembly. The invention improves the endurance capacity of the spacecraft in the natural strong electromagnetic environment based on the existing structure.
Description
Technical Field
The invention relates to the technical field of electromagnetic protection, in particular to a conformal structure for enhancing electromagnetic tolerance and a method thereof.
Background
The spacecraft can generate a charging and discharging phenomenon under the interaction of environments such as space plasma, high-energy electrons, space radiation and the like, namely, charges are gradually accumulated in a spacecraft system, a local electric field is gradually enhanced along with the rise of electric potential, and then the charges are discharged instantly when the charges are accumulated to breakdown field intensity to generate electrostatic discharge (ESD) pulse, so that the spacecraft is one of main natural strong electromagnetic environment factors faced by the spacecraft in orbit. Especially for high-value communication signals working on synchronous tracks, the charging and discharging effects of the environment are worse than those of the tracks near the outer radiation zone.
Therefore, in order to shield the pulse generated by the space electrostatic discharge and other complex electromagnetic environments, a complex shielding and grounding system is designed on the spacecraft. Traditional research believes that a filter layer with the thickness of 6um (microns) on a multilayer heat insulation assembly (mainly used for reducing radiation heat exchange) on the surface of a spacecraft can play a certain shielding effect, but on-orbit data show that recoverable faults of the spacecraft still fluctuate in a solar activity period. Meanwhile, new research shows that structures such as nylon nets in the multilayer heat insulation assembly can generate internal electrification under the action of higher-energy-level particles, so that electrostatic discharge is generated in the multilayer heat insulation assembly and enters the spacecraft through the coupling of cabin plate holes.
Therefore, the problems of the spacecraft in the prior art that the spacecraft is subjected to a strong electromagnetic environment and generates electrostatic discharge due to internal charging under the action of high-energy-level particles become the technical problems to be solved urgently.
Disclosure of Invention
The invention aims to provide a conformal structure for enhancing electromagnetic tolerance and a method thereof, which improve the tolerance of a spacecraft in a natural strong electromagnetic environment based on the existing structure.
In order to solve the technical problems, the technical scheme provided by the invention is as follows: the utility model provides a conformal structure of reinforcing electromagnetic tolerance performance, include the cabin board of constituteing by the concatenation of independent first aluminium honeycomb panel and second aluminium honeycomb panel, locate optical channel structure and optics secondary surface mirror on the cabin board, laid multilayer thermal-insulated subassembly in the outside of cabin board, be equipped with on second aluminium honeycomb panel and wear the cabin hole, it has hole plugging material to bond through the electrically conductive sticky tape around wearing the cabin hole, at the cabin board, wear the cabin hole, optical channel structure and optics secondary surface mirror are through multilayer edge ground structure ground connection respectively.
By adopting the technical scheme, the cabin plate formed by splicing the first aluminum honeycomb plate and the second aluminum honeycomb plate forms the innermost shielding layer of the satellite cabin body, the multilayer heat insulation assembly forms the outermost shielding layer of the satellite cabin body, the optical channel structure provides grounding for the thermal control OSR plate assembly, the cabin penetrating holes are blocked, the blocking of the gaps of the cabin penetrating holes is provided, electromagnetic waves are prevented from being coupled into the satellite, the grounding of the optical channel structure provides grounding for the external optical channels of various optical sensors, the possibility of coupling the electromagnetic waves of the optical channels is reduced, all the shielding and grounding are finally connected to the satellite internal connection place of the satellite, and the equipotential of the satellite outer layer is guaranteed. Based on the structure of the existing general satellite, the conformal shielding concept is provided, the conformal shielding structure has the advantages of low cost, simple structure, strong implementability and the like, and the endurance capability of the satellite in the natural strong electromagnetic environment can be improved based on the prior art. According to the invention, a Faraday cage shielding structure of the spacecraft can be formed by depending on the combination of the existing spacecraft cabin plate and the multilayer heat insulation assembly, and the anti-interference capability of the spacecraft in a natural strong electromagnetic environment can be improved.
Further, multilayer edge ground structure includes hollow copper rivet, many times folding aluminium foil strip and earth connection that takes shape, and hollow copper rivet passes through the gasket and is fixed in the aluminium foil strip on the thermal-insulated subassembly of multilayer, and the surface coating of aluminium foil strip has the thermal-insulated subassembly facial mask of multilayer, and earth connection ground connection behind aluminium foil strip and the hollow copper rivet. The conductive hollow copper rivets and the aluminum foil strips are grounded to the multi-layer heat insulation assembly through the grounding wire, so that a good grounding effect and a shielding effect are achieved.
Further, the pin is bonded on the surfaces of the first aluminum honeycomb plate and the second aluminum honeycomb plate through vulcanized silicone rubber.
Further, the multi-layered heat insulation assembly includes first and second heat insulation boards of a multi-layered structure, and first and second conductive adhesive materials are adhered to the inner and outer sides of the first and second heat insulation boards (103-2), respectively.
Further, the optical secondary surface mirror is a thermal control OSR sheet assembly, and the thermal control OSR sheet assembly is bonded to the deck plate through a conductive adhesive. The optical secondary surface mirror is grounded mainly by using conductive adhesive, and the OSR is adhered to the cabin plate through the conductive adhesive, so that the optical secondary surface mirror is grounded.
Further, a cabin-penetrating waveguide, a cabin-penetrating pipeline assembly, a first cabin-penetrating cable or a second cabin-penetrating cable are arranged in the cabin-penetrating hole in a penetrating mode, hole plugging materials are filled at the peripheries of the cabin-penetrating waveguide, the cabin-penetrating pipeline assembly, the first cabin-penetrating cable or the second cabin-penetrating cable, and the hole plugging materials are bonded and fixed through conductive adhesive tapes. The cabin-through holes are divided into cabin-through waveguide holes, cabin-through pipeline assembly holes and cabin-through cable holes through cabin-through waveguides, cabin-through pipeline assembly holes and cabin-through cable holes, wherein the cabin-through waveguide hole plugs are used for plugging holes of a spacecraft communication waveguide entrance and exit board, the main plugging material is a metal mesh or a metal foil, the metal mesh or the metal foil is fixed and grounded through a conductive adhesive tape, the conductive adhesive tape is adhered to metal on the outer side of a waveguide pipeline, and the adhering width of the conductive adhesive tape is not less than 5 cm; the cabin-crossing pipeline assembly hole plugging is used for plugging holes of a cabin outlet plate of a propulsion pipeline of a spacecraft, the main material of the plugging is a metal mesh or a metal foil, the metal mesh or the metal foil is fixed and grounded through a conductive adhesive tape, the conductive adhesive tape is adhered to the outer part of a heat insulation layer of the propulsion pipeline, and the adhering width of the conductive adhesive tape is not less than 5 cm; the cabin-crossing cable hole plugging is used for plugging holes of a high-frequency cable and a low-frequency cable of a spacecraft, which enter and exit a cabin plate, the main material of plugging is a metal mesh or a metal foil, the metal mesh or the metal foil is fixed and grounded through a conductive adhesive tape, the conductive adhesive tape is adhered to a cable metal shielding mesh, and the adhering width of the conductive adhesive tape is not less than 5 cm.
Furthermore, the optical channel structure comprises an optical channel shell, optical glass and a transparent conductive film, wherein the optical glass is arranged on the outer layer of the optical channel shell, and the transparent conductive film is arranged between the optical channel shell and the optical glass. Optical channel grounding relies primarily on a transparent conductive film attached to the surface of the optical lens, which may be formed using indium tin oxide or etched conductive mesh.
Further, the transparent conductive film is composed of an optical substrate, and an optical channel for filling a conductive material is provided on a surface of the optical substrate.
In order to solve the above technical problems, the present invention provides a technical solution further comprising: a method of enhancing electromagnetic withstand capability comprising
Installing a cabin-penetrating waveguide, a cabin-penetrating pipeline assembly, a first cabin-penetrating cable or a second cabin-penetrating cable on the cabin-penetrating hole;
cutting hole plugging materials on the corresponding cabin penetrating holes to plug the inner sides of the cabin penetrating holes;
fixing the periphery of the hole plugging material on the cabin plate through a conductive adhesive tape;
fixing the center of the hole plugging material on the cabin-penetrating waveguide, the cabin-penetrating pipeline assembly, the first cabin-penetrating cable or the second cabin-penetrating cable through the conductive adhesive tape;
and (4) bonding the hole plugging material and the conductive adhesive tape on the outer side, and installing the multilayer heat insulation assembly.
By adopting the technical scheme, the cabin-passing hole is plugged, the gap of the cabin-passing hole is plugged, electromagnetic waves are prevented from being coupled into the satellite, and the good grounding effect is ensured by the aid of the conductivity of the conductive adhesive tape through bonding of the conductive adhesive tape.
Further, when a second cabin penetrating cable is plugged, firstly, cutting off the cable outer insulating layer of the second cabin penetrating cable at the cabin penetrating part to expose the metal shielding layer of the second cabin penetrating cable;
cutting hole plugging materials on the corresponding cabin penetrating holes to plug the inner sides of the cabin penetrating holes;
fixing the periphery of the hole plugging material on the cabin plate through a conductive adhesive tape;
fixing the center of the hole plugging material on a shielding layer of the second cabin-penetrating cable through a conductive adhesive tape;
and (4) bonding the hole plugging material and the conductive adhesive tape on the outer side, and installing the multilayer heat insulation assembly.
The invention has the beneficial effects that: based on the design ideas of the existing spacecraft such as an aluminum honeycomb panel and a multilayer heat insulation assembly, the tolerance capability of the existing spacecraft to the natural strong electromagnetic environment is enhanced, and the spacecraft has the characteristics of simple structure, low cost, strong inheritance and the like, and can meet the natural strong electromagnetic environment tolerance requirement of the future spacecraft.
Drawings
FIG. 1 is a schematic diagram of a conformal structure for enhancing electromagnetic withstand performance according to the present invention;
FIG. 2 is a schematic structural diagram of a multi-layer edge grounding structure according to the present invention;
FIG. 3 is a schematic view of the attachment of the multi-layer insulation assembly of the present invention;
FIG. 4 is a schematic view of the overlapping pattern of the multi-layer insulation assembly of the present invention;
FIG. 5 is a schematic diagram of the grounding structure of the optical secondary surface mirror according to the present invention;
FIG. 6 is a schematic structural view of a through-the-cabin waveguide hole plugging manner according to the present invention;
FIG. 7 is a schematic structural view of a plugging manner of a hole of a cabin-passing pipeline assembly according to the present invention;
FIG. 8 is a schematic structural view of a plugging manner of a through-cabin cable hole according to the present invention;
FIG. 9 is a schematic structural view of another plugging mode of a through-cabin cable hole according to the invention;
FIG. 10 is a schematic perspective view of a cross-cabin waveguide hole plugging method according to the present invention;
FIG. 11 is a schematic diagram of the grounding scheme of the optical via structure of the present invention;
FIG. 12 is a schematic diagram of one embodiment of the grounding of an etched conductive mesh-based optical via structure of the present invention.
Description of reference numerals: 101 cabin plate, 101-1 first aluminum honeycomb plate, 101-2 second aluminum honeycomb plate, 103 multilayer heat insulation component, 103-1 first heat insulation plate, 103-2 second heat insulation plate, 103-3 multilayer heat insulation component mask, 104 is thermal control OSR plate component, 105 conductive adhesive, 106 cabin penetrating pipeline combination, 106-1 cabin penetrating pipeline, 106-2 cabin penetrating pipeline protective layer, 107 cabin penetrating waveguide, 108 first cabin penetrating cable, 108-1 first cable core, 108-2 first cable dielectric layer, 108-3 first cable metal shielding layer, 109 second cabin penetrating cable, 109-1 second cable core, 109-2 second cable dielectric layer, 109-3 second cable metal shielding layer, 109-4 second cable outer insulation layer, 110 cabin penetrating hole, 201 pin, 201-1 hollow copper rivet, 201-2 gasket, 201-3 aluminum foil strips, 201-4 grounding wires, 201-5 vulcanized silicone rubber, 203-1 first conductive adhesive materials, 203-2 second conductive adhesive materials, 204 conductive adhesive tapes, 205 hole sealing materials, 301 optical channel shells, 302 optical glass, 303 transparent conductive films, 303-1 optical substrates and 303-2 optical channels.
Detailed Description
The invention is further described with reference to the following figures and detailed description.
Referring to fig. 1 to 12, the invention discloses a conformal structure for enhancing electromagnetic resistance, which includes a deck 101 formed by splicing a first aluminum honeycomb panel 101-1 and a second aluminum honeycomb panel 101-2, an optical channel structure and an optical secondary surface mirror, wherein the deck 101 is formed by splicing the first aluminum honeycomb panel 101-1 and the second aluminum honeycomb panel 101-2, a multi-layer heat insulation assembly 103 is laid on the outer side of the deck 101, a cabin through hole 110 is arranged on the second aluminum honeycomb panel 101-2, a hole blocking material 205 is fixedly bonded around the cabin through hole 110 through a conductive adhesive tape 204, and the deck 101, the cabin through hole 110, the optical channel structure and the optical secondary surface mirror are respectively grounded through a multi-layer edge grounding structure.
The multi-layer edge grounding structure comprises a hollow copper rivet 201-1, an aluminum foil strip 201-3 formed by multiple folding and a grounding wire 201-4, wherein the hollow copper rivet 201-1 fixes the aluminum foil strip 201-3 on the multi-layer heat insulation assembly 103 through a gasket 201-2, the surface of the aluminum foil strip 201-3 is coated with a multi-layer heat insulation assembly surface film 103-3, and the grounding wire 201-4 is grounded after being connected with the aluminum foil strip 201-3 and the hollow copper rivet 201-1. Wherein, the multilayer heat insulation assembly 103 is fixed on the surface of the cabin plate 101 through a pin 201, and a gasket 201-2 is arranged between the pin 201 and the multilayer heat insulation assembly 103 in a cushioning way.
The pins 201 are adhered to the surfaces of the first aluminum honeycomb panel 101-1 and the second aluminum honeycomb panel 101-2 through vulcanized silicone rubber 201-5.
The multi-layered heat insulation assembly 103 includes a first heat insulation board 103-1 and a second heat insulation board 103-2 having a multi-layered structure, and a first conductive adhesive material 203-1 and a second conductive adhesive material 203-2 are adhered to the inner and outer sides of the first heat insulation board 103-1 and the second heat insulation board 103-2, respectively.
The optical secondary surface mirror is a thermally controlled OSR sheet assembly 104, and the thermally controlled OSR sheet assembly 104 is bonded to the deck plate 101 by a conductive adhesive 105.
A cabin-passing waveguide 107, a cabin-passing pipeline assembly 106, a first cabin-passing cable 108 or a second cabin-passing cable 109 are arranged in the cabin-passing hole 110 in a penetrating mode, hole plugging materials 205 are filled at the peripheries of the cabin-passing waveguide 107, the cabin-passing pipeline assembly 106, the first cabin-passing cable 108 or the second cabin-passing cable 109, and the hole plugging materials 205 are bonded and fixed through conductive adhesive tapes 204.
The optical channel structure comprises an optical channel housing 301, an optical glass 302 and a transparent conductive film 303, wherein the optical glass 302 is arranged at the outer layer of the optical channel housing 301, and the transparent conductive film 303 is arranged between the optical channel housing 301 and the optical glass 302.
The transparent conductive film 303 is formed of an optical substrate 303-1, and an optical channel for filling a conductive material is provided on the surface of the optical substrate 303-1.
The invention also discloses a method for enhancing the natural strong electromagnetic tolerance, which comprises the following steps
Installing a cabin-passing waveguide 107, a cabin-passing pipeline assembly 106, a first cabin-passing cable 108 or a second cabin-passing cable 109 on the cabin-passing hole 110;
cutting hole plugging materials 205 and placing the cut hole plugging materials on the corresponding cabin penetrating holes 110 to plug the inner sides of the cabin penetrating holes 110;
fixing the periphery of the hole plugging material 205 on the deck board 101 through a conductive adhesive tape 204;
fixing the center of the hole plugging material 205 on the cabin-penetrating waveguide 107, the cabin-penetrating pipeline assembly 106, the first cabin-penetrating cable 108 or the second cabin-penetrating cable 109 through the conductive adhesive tape 204;
the hole plugging material 205 and the conductive tape 204 on the outer side are bonded, and the multi-layer thermal insulation assembly 103 is installed.
In another embodiment, when the second through-the-cabin cable 109 is plugged, the cable outer insulating layer 109-4 of the second through-the-cabin cable 109 of the through-the-cabin part is cut off firstly, so that the metal shielding layer 109-3 is exposed;
cutting hole plugging materials 205 and placing the cut hole plugging materials on the corresponding cabin penetrating holes 110 to plug the inner sides of the cabin penetrating holes 110;
fixing the periphery of the hole plugging material 205 on the deck board 101 through a conductive adhesive tape 204;
the center of the hole plugging material 205 is fixed on the shielding layer 109-3 of the second through-the-cabin cable 109 by the conductive tape 204;
the hole plugging material 205 and the conductive tape 204 on the outer side are bonded, and the multi-layer thermal insulation assembly 103 is installed.
The following description is further provided for a conformal structure with enhanced electromagnetic tolerance according to the present invention with reference to the accompanying drawings and the detailed description.
Fig. 1 is a schematic view of a conformal structure for enhancing electromagnetic resistance according to the present invention, in which a first aluminum honeycomb panel 101-1 and a second aluminum honeycomb panel 101-2 are independent from each other, and are spliced to form a panel 101, so as to form a shell structure of a satellite, thereby forming an innermost shielding structure of a satellite system. The conductive adhesive tape 204 can be copper, aluminum-based adhesive tape and the like, and is plugged by sealing gaps of the cabin plate, so that electromagnetic waves are prevented from being coupled into the cabin body, and the bonding width is generally 5 cm. The multi-layer insulation assembly 103 is fixed on the surface of the deck 101, and mainly plays a role in thermal control, and also can play a part in shielding. The deck plate 101 is provided with through-deck holes 110, which are mainly used for structural weight reduction and process operation. The through-cabin holes 110 are sealed by using a hole sealing material 205 consisting of tantalum foil or metal mesh. And (3) adhering a conductive adhesive tape 204 along the periphery of the hole plugging material 205, fixing the hole plugging material 205 on the deck board 101, and further plugging the edge.
FIG. 2 is a schematic structural diagram of a multi-layer edge grounding structure of the present invention, a hollow copper rivet 201-1 can compress the grounding structure on the multi-layer thermal insulation assembly 103, and a gasket 201-2 is disposed on the inner side of the hollow copper rivet 201-1 to cooperate with the hollow copper rivet 201-1 to compress the multi-layer thermal insulation assembly 103. The aluminum foil strip 201-3 is folded for multiple times, so that the surface area is increased, and the aluminum foil strip is in contact with each layer of structure in the middle of the multi-layer heat insulation assembly 103, so that the good grounding of the whole multi-layer heat insulation assembly 103 is realized. The multi-layer insulation assembly 103 and the cabin of the satellite are electrically connected and grounded by using a grounding wire 201-4, wherein the grounding wire 201-4 can use a wire or a strap. The multi-layer thermal insulation component surface film 103-3 is generally a single-side aluminized polyimide film, and indium tin oxide is coated on the outer side of the multi-layer thermal insulation component surface film to coat the surface of the aluminum foil strip 201-3. Multi-layer insulation assembly 103 includes multiple sets of nylon mesh and aluminized polyester film therein.
FIG. 3 is a schematic view of the fixing of the multi-layered thermal insulation assembly of the present invention, wherein a first conductive adhesive material 203-1 and a second conductive adhesive material 203-2 are adhered to the inner and outer sides of the multi-layered thermal insulation assembly 103, respectively. The hollow copper rivets 201-1 are adhered to the surface of the deck plate 101 through vulcanized silicone rubber 201-5.
FIG. 4 is a schematic view showing a structure of a multi-layered heat insulation assembly according to the present invention, in which a multi-layered heat insulation assembly 103 includes a first heat insulation board 103-1 and a second heat insulation board 103-2 bonded to each other, and a first conductive adhesive material 203-1 and a second conductive adhesive material 203-2 are respectively bonded to the inner and outer sides of the two boards. The first conductive adhesive material 203-1 is made of the same material as the multi-layer thermal insulation assembly surface film 103-3 and is adhered to the outer side, and the second conductive adhesive material 203-2 is adhered to the inner side, wherein the adhering width is generally 5 cm.
Fig. 5 is a schematic structural diagram of the grounding mode of the optical secondary surface mirror according to the present invention, and the thermal control OSR sheet assembly 104 is an important thermal control material for the surface of a spacecraft, and has high emissivity and low solar absorption ratio. The conductive paste 105 is typically a mixture of an AB-type silicone rubber based adhesive and silver powder to electrically connect the thermal control OSR chip assembly 104 to the deck board 101.
Fig. 6 is a schematic structural diagram of a through-cabin waveguide hole plugging manner according to the present invention, in which a through-cabin waveguide 107 is used to transmit microwave signals inside and outside a cabin, a through-cabin hole 110 is reserved on the surface of a cabin board 101 for the through-cabin waveguide 107, after the through-cabin waveguide 107 is installed, the inside of the hole is plugged, and a hole plugging material 205, i.e., a tantalum foil or a metal mesh, is cut and placed on the corresponding hole 110, wherein the outside is not less than 5cm of the hole outer envelope. The periphery of the hole plugging material 205 was fixed to the deck 101 by a conductive tape 204, the center of the hole plugging material 205 was fixed to the cross-hatch waveguide 107 by the conductive tape 204, and no gap was checked, wherein the tape width was generally not less than 5 cm. After the inner side is finished, the hole plugging material 205 and the conductive tape 204 on the outer side are adhered by the same method, and the corresponding multi-layer heat insulation assembly 103 is installed.
Fig. 7 is a schematic structural view of a hole plugging manner of the cabin-penetrating pipeline assembly according to the present invention, the cabin-penetrating pipeline assembly 106 is composed of a cabin-penetrating pipeline 106-1 and a cabin-penetrating pipeline protection layer 106-2, the cabin-penetrating pipeline 106-1 sends out attitude and orbit control system propellant to the outside of the cabin, the cabin-penetrating pipeline protection layer 106-2 is used for insulating the cabin-penetrating pipeline 106-1, a cabin-penetrating hole 110 is reserved on the surface of a cabin plate 101 for the cabin-penetrating pipeline assembly 106, after the cabin-penetrating pipeline is installed, the inside of the hole is plugged, and a hole plugging material 205, i.e., tantalum foil or metal mesh, is cut and placed on the corresponding hole, wherein the outside is not less than 5cm of an envelope of the hole. The periphery of the hole plugging material 205 is fixed on the deck 101 by the conductive adhesive tape 204, the center of the hole plugging material 205 is fixed on the cabin-penetrating pipe insulation layer 106-2 by the conductive adhesive tape 204, and no gap is checked, wherein the width of the adhesive tape is generally not less than 5 cm. After the inner side is finished, the hole plugging material 205 and the conductive tape 204 on the outer side are adhered by the same method, and the corresponding multi-layer heat insulation assembly 103 is installed.
Fig. 8 is a schematic structural diagram of a hole plugging manner of a cabin-penetrating cable according to the present invention, in which a first cabin-penetrating cable 108 is composed of a first cable core 108-1, a first cable dielectric layer 108-2 and a first cable metal shielding layer 108-3, the first cable core 108-1 is generally made of a metal material such as copper, the first cable dielectric layer 108-2 is a cable dielectric layer for insulation, and the first cable metal shielding layer 108-3 is used for shielding an outer layer of the cable; the cabin plate 101 surface reserves a cabin penetrating hole 110 for a first cabin penetrating cable 108, after the cabin penetrating cable is installed, the inner side of the hole is firstly sealed, a hole sealing material 205, namely tantalum foil or metal mesh, is cut and placed on the corresponding hole, wherein the outer side is not less than 5cm of the outer envelope of the hole. The periphery of the hole plugging material 205 is fixed on the cabin plate 101 through the conductive adhesive tape 204, the center of the hole plugging material 205 is fixed on the shielding layer 108-3 of the through-cabin cable through the conductive adhesive tape 204, and the close fit is checked, wherein the width of the adhesive tape is generally not less than 5 cm. After the inner side is finished, the hole plugging material 205 and the conductive tape 204 on the outer side are adhered by the same method, and the corresponding multi-layer heat insulation assembly 103 is installed.
Fig. 9 is a schematic structural view of another hole plugging manner of the through-cabin cable according to the present invention, in which a second through-cabin cable 109 is composed of a second cable core 109-1, a second cable dielectric layer 109-2, a second cable metallic shielding layer 109-3, and a second cable outer insulating layer 109-4, the second cable core 109-1 is generally made of a metallic material such as copper, the second cable dielectric layer 109-2 is used for insulation, the second cable metallic shielding layer 109-3 is used for cable outer layer shielding, the second cable outer insulating layer 109-4 is a cable outermost layer insulating material, a hole 110 is reserved on the surface of the deck 101 for the second through-cabin cable 109, after the through-cabin cable is installed, 1 first cuts the cable outer insulating layer 109-4 of the through-cabin portion to directly expose the metallic shielding mesh 109-3, and 2 second plugs the inside of the hole, the hole blocking material 205, i.e. tantalum foil or metal mesh, is cut and placed over the corresponding hole, wherein the outer side is not less than 5cm of the outer envelope of the hole. The periphery of the hole plugging material 205 is fixed on the aluminum honeycomb panel 101 by the conductive adhesive tape 204, the center of the hole plugging material 205 is fixed on the shielding layer 109-3 of the cross-cabin cable by the conductive adhesive tape 204-2, and the close fit is checked, wherein the width of the adhesive tape is generally not less than 5 cm. After the inner side is finished, the hole sealing material 205 and the conductive tape 204 on the outer side are adhered by the same method, and the corresponding multi-layer thermal insulation module 103 is installed.
Fig. 10 is a schematic perspective view of a plugging manner of a cabin-passing waveguide hole according to the present invention, wherein the left side is a schematic view before plugging, and the right side is a schematic view after plugging, and a hole plugging material 205 shaped like a Chinese character 'hui' is cut and bonded and fixed by an inner conductive tape 204 and an outer conductive tape 204.
Fig. 11 is a schematic diagram of the grounding mode of the optical channel structure of the present invention, in which the optical channel housing 301 is the housing of the optical sensor lens, the optical glass 302 is the outermost glass of the optical sensor lens, and the transparent conductive film 303 is formed by etching or plating, so as to form a continuous conductor on the glass surface and prevent the natural strong electromagnetic pulse from coupling into the optical channel.
Fig. 12 is a schematic diagram of a specific form of grounding of the optical via structure based on the etched conductive mesh of the present invention, in which the transparent conductive film 303 is composed of an optical substrate 303-1, the optical via is a via etched on the substrate surface 303-1, and the interior is filled with a conductive material such as silver.
Through the combination of the above means, the Faraday cage shielding structure of the spacecraft can be formed by depending on the combination of the existing spacecraft cabin plate and the multilayer heat insulation assembly, and the anti-interference capability of the spacecraft in a natural strong electromagnetic environment can be improved.
In summary, the actual samples of the present invention are prepared according to the description and the drawings, and after a plurality of usage tests, the effect of the usage tests proves that the present invention can achieve the expected purpose, and the practical value is undoubted. The above-mentioned embodiments are only for convenience of illustration and not intended to limit the invention in any way, and those skilled in the art will appreciate that the invention is capable of being practiced by other than the specific embodiments, and that various modifications and equivalent arrangements can be made without departing from the spirit and scope of the invention.
Claims (10)
1. The utility model provides a conformal structure of reinforcing electromagnetic resistance performance, include cabin board (101) of constituteing by independent first aluminium honeycomb panel (101-1) and second aluminium honeycomb panel (101-2) concatenation, locate optical channel structure and the optics secondary surface mirror on cabin board (101), laid multilayer thermal-insulated subassembly (103) in the outside of cabin board (101), be equipped with cabin hole (110) of wearing on second aluminium honeycomb panel (101-2), it has hole shutoff material (205) to bond through electrically conductive sticky tape (204) around cabin hole (110) to be fixed with, at cabin board (101), cabin hole (110), optical channel structure and optics secondary surface mirror ground connection through multilayer marginal grounding structure respectively.
2. The electromagnetic immunity enhancing conformal structure of claim 1, wherein: the multilayer edge grounding structure comprises hollow copper rivets (201-1), aluminum foil strips (201-3) formed by multiple folding and grounding wires (201-4), the hollow copper rivets (201-1) fix the aluminum foil strips (201-3) on the multilayer heat insulation assembly (103) through gaskets (201-2), the surface of the aluminum foil strips (3) is coated with a multilayer heat insulation assembly surface film (103-3), and the grounding wires (201-4) are connected with the aluminum foil strips (201-3) and the hollow copper rivets (201-1) and then grounded.
3. The electromagnetic immunity enhancing conformal structure of claim 1, wherein: the pins (201) are bonded on the surfaces of the first aluminum honeycomb plate (101-1) and the second aluminum honeycomb plate (101-2) through vulcanized silicone rubber (201-5).
4. The electromagnetic immunity enhancing conformal structure of claim 2, wherein: the multi-layered heat insulation assembly (103) includes a first heat insulation board (103-1) and a second heat insulation board (103-2) having a multi-layered structure, and a first conductive adhesive material (203-1) and a second conductive adhesive material (203-2) are adhered to the inner side and the outer side of the first heat insulation board (103-1) and the second heat insulation board (103-2), respectively.
5. The electromagnetic immunity enhancing conformal structure of claim 2, wherein: the optical secondary surface mirror is a thermal control OSR sheet component (104), and the thermal control OSR sheet component (104) is bonded on the cabin plate (101) through a conductive adhesive (105).
6. The electromagnetic immunity enhancing conformal structure of claim 1, wherein: a cabin-passing waveguide (107), a cabin-passing pipeline assembly (106), a first cabin-passing cable (108) or a second cabin-passing cable (109) are arranged in the cabin-passing hole (110) in a penetrating mode, hole plugging materials (205) are filled at the peripheries of the cabin-passing waveguide (107), the cabin-passing pipeline assembly (106), the first cabin-passing cable (108) or the second cabin-passing cable (109), and the hole plugging materials (205) are bonded and fixed through conductive adhesive tapes (204).
7. The conformal structure of claim 5, wherein said conformal structure further comprises: the optical channel structure comprises an optical channel shell (301), optical glass (302) and a transparent conductive film (303), wherein the optical glass (302) is arranged on the outer layer of the optical channel shell (301), and the transparent conductive film (303) is arranged between the optical channel shell (301) and the optical glass (302).
8. The electromagnetic immunity enhancing conformal structure of claim 7, wherein: the transparent conductive film (303) is composed of an optical substrate (303-1), and an optical channel (303-2) for filling a conductive material is arranged on the surface of the optical substrate (303-1).
9. A method of enhancing electromagnetic withstand performance, characterized by: comprises that
A cabin penetration waveguide (107), a cabin penetration pipeline assembly (106), a first cabin penetration cable (108) or a second cabin penetration cable (109) are arranged on the cabin penetration hole (110);
cutting hole plugging materials (205) to be arranged on the corresponding cabin penetrating holes (110) to plug the inner sides of the cabin penetrating holes (110);
fixing the periphery of the hole plugging material (205) on the deck (101) through a conductive adhesive tape (204);
fixing the center of the hole plugging material (205) on the cabin-passing waveguide (107), the cabin-passing pipeline assembly (106), the first cabin-passing cable (108) or the second cabin-passing cable (109) through the conductive adhesive tape (204);
and (3) bonding the hole blocking material (205) on the outer side and the conductive adhesive tape (204) to install the multilayer heat insulation assembly (103).
10. The method of enhancing electromagnetic withstand capability of claim 9, wherein:
when a second cabin penetrating cable (109) is plugged, firstly, cutting off a cable outer insulating layer (109-4) of the second cabin penetrating cable (109) at a cabin penetrating part to expose a metal shielding layer (109-3) of the second cabin penetrating cable;
cutting hole plugging materials (205) and placing the cut hole plugging materials on the corresponding cabin penetrating holes (110) to plug the inner sides of the cabin penetrating holes (110);
fixing the periphery of the hole plugging material (205) on the deck (101) through a conductive adhesive tape (204);
fixing the center of the hole plugging material (205) on a shielding layer (109-3) of the second cabin penetrating cable (109) through a conductive adhesive tape (204);
and (3) bonding the hole blocking material (205) on the outer side and the conductive adhesive tape (204) to install the multilayer heat insulation assembly (103).
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| CN110920802A (en) * | 2019-11-15 | 2020-03-27 | 沪东中华造船(集团)有限公司 | Waveguide movable clamping piece, waveguide penetrating device and method for installing waveguide |
| CN113060303A (en) * | 2021-03-18 | 2021-07-02 | 中国人民解放军国防科技大学 | Integrated spacecraft cabin plate containing structural lithium battery |
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| CN203512060U (en) * | 2013-06-18 | 2014-04-02 | 北京空间飞行器总体设计部 | Radiation capsule used for star sensor |
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| CN114554818B (en) | 2024-05-28 |
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