CN107972288A - A kind of mars exploration landing rover integral antenna housing and preparation method thereof - Google Patents

A kind of mars exploration landing rover integral antenna housing and preparation method thereof Download PDF

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Publication number
CN107972288A
CN107972288A CN201711155396.7A CN201711155396A CN107972288A CN 107972288 A CN107972288 A CN 107972288A CN 201711155396 A CN201711155396 A CN 201711155396A CN 107972288 A CN107972288 A CN 107972288A
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housing
laying
preparation
prepreg
carbon fiber
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CN107972288B (en
Inventor
崔超
潘玲英
郭鸿俊
李林雪
贺朝晖
王保林
赵伟栋
蒋文革
赵建设
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China Academy of Launch Vehicle Technology CALT
Aerospace Research Institute of Materials and Processing Technology
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China Academy of Launch Vehicle Technology CALT
Aerospace Research Institute of Materials and Processing Technology
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
    • B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/42—Housings not intimately mechanically associated with radiating elements, e.g. radome
    • H01Q1/425—Housings not intimately mechanically associated with radiating elements, e.g. radome comprising a metallic grid

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

The present invention provides a kind of mars exploration landing rover integral antenna housing and preparation method thereof, manufactured by casing forming mold, the preparation of carbon fiber/polyamide imines prepreg, housing laying, imidization, curing, the demoulding, mechanical processing, shell inner surface metal cladding and etc. realization.The present invention is using negative and positive combination die, the molding mode of high-temperature-resisting silicon rubber flexible-mould assisted, and Integratively formed using autoclave forming process, the housing of preparation has lightweight, resistance to 370 DEG C of high temperature, resistance to space environment, the characteristic of structural bearing multifunctional all；At the same time, the coupling technique of housing base and inner surface vacuum sputtering metal cladding is modified using nano silver particles, both antenna housing electro-magnetic screen function had been realized, the installing structure space of traditional antenna connecting cable occupancy is eliminated again, further reduce interface connection, while improving space availability ratio, the structure type of housing in turn simplify.

Description

A kind of mars exploration landing rover integral antenna housing and preparation method thereof
Technical field
The present invention relates to a kind of integral antenna housing and preparation method thereof, particularly a kind of mars exploration landing rover With integral antenna housing and preparation method thereof.
Background technology
Recently, the main battle ground that deep-space detection field is competitively contended as space race between each big country, survey of deep space are landed and are patrolled The characteristics of visual organ tends to high performance, highly integrated, remote work high reliability.At present, with mars exploration, saturn's exploration etc. For the farther apart from survey of deep space of representative, the requirement for the remote work high reliability of such survey of deep space landing rover Harsher, especially effectively transmission seems particularly important to aerial signal at a distance.Antenna housing is patrolled as protection detection landing The important component of visual organ antenna system normal work, should be resistant to harsh in survey of deep space landing rover flies to target way Space environment：Resistance to space radiation, high-low temperature resistant circulation, resistance to elemental oxygen, resistance to space matter damage, low deflation rate, low coagulate volatile matter Deng；High temperature (>=320 DEG C) and landing mission caused by bearing Aerodynamic Heating when landing rover arrives at target landing again The impact of dynamic loading.Meanwhile also to meet that antenna housing light weight, interior surface are conductive, the few requirement in assembly connection interface.
At present, the common antenna protection housing of spacecraft be mostly epoxy/glass steel class, cyanate ester/fiberglass class and Inorganic ceramic class material.The epoxy/glass steel class and cyanate ester of high-strength light/fiberglass class antenna protection housing temperature in use are not Higher than 200 DEG C, therefore restricted by its temperature in use and there is very big application limitation.In addition, epoxy/glass steel class and cyanate ester/ The resistance to space environment of fiberglass class composite material has its respective deficiency, and particularly tolerance space high/low temperature cycle performance is poor, its Scantling stability is poor.Inorganic ceramic class antenna housing can meet heatproof requirement, but weight is big, easy embrittlement, molding cycle Long, machine adds poor performance and mechanics to carry low shortcoming and restrict its application.Carbon fiber/polyamide imines antenna housing has excellent resistance to Hot and mechanical property, specific strength is high, and resistance to Space environmental property is excellent, but this deep space probe of carbon fiber/polyamide imines is used Multifunctional all antenna housing has no report at home.
The content of the invention
It is an object of the invention to：Overcome the deficiencies of the prior art and provide a kind of mars exploration landing rover one Change antenna housing and preparation method thereof, the antenna housing of preparation has lightweight, resistance to 370 DEG C of high temperature, resistance to space environment, structural bearing The characteristic of multifunctional all；Meanwhile it is modified housing base and inner surface vacuum sputtering metal cladding using nano silver particles Coupling technique, had not only realized antenna housing electro-magnetic screen function, but also eliminated the installing structure of traditional antenna connecting cable occupancy Space, further reduces interface connection, while improving space availability ratio, in turn simplify the structure type of housing.
The above-mentioned purpose of the present invention is achieved by following technical solution：A kind of mars exploration landing rover is used Integral antenna housing, including：Housing, the coat of metal, assembling mounting hole and air vent；Housing is square structure, and middle part is inside Depression forms some layers of ledge structure, the shell inner surface plating coat of metal, and assembling mounting hole, ledge structure is distributed with shell rim Air vent is distributed with side elevation.
The material of the coat of metal is densification continuous aluminium coat, copper coating, silvering or the gold plate of acidification.
The coat of metal is plated on housing by the method that chemical plating, impulse jet technique coating or vacuum sputtering plate.
A kind of mars exploration landing rover integral antenna housing preparation method, comprises the following steps：
Step 1: according to the shape of housing, casing forming mold is manufactured, and casing forming mold is carried out at high-temperature oxydation Reason and airtight inspection so that the surface roughness of the forming face of casing forming mold is maintained in the range of 3.0~3.3；
The mould molding mould includes main body formpiston, piecemeal former and " L-type " auxiliary silicon rubber soft mode, two piecemeal the moon Mould is symmetrical on interface, and the inner space that main body formpiston is formed after coordinating with two piecemeal formers is consistent with shell structure；“L Type " auxiliary silicon rubber soft mode is respectively at piecemeal former interior step face；
Step 2: preparing carbon fiber/polyamide imines prepreg, carbon fiber/polyamide imines prepreg is polyimide resin Fibre reinforced fabric after glue dipping；Specifically preparation method is：Conductive nano is used to polyimide resin glue Particle is modified, and the weight ratio of polyimide resin and nano conducting powders is 10:(1.5~3), by modified polyamides Imide resin glue is with fibre reinforced fabric according to (1.5~2.8):1 quality proportioning is impregnated；Dipping is complete Afterwards, after room temperature hangs 8~12h, nylon grid film of the covering with air guide channel；
Step 3: carbon fiber/polyamide imines prepreg overlay is carried out in main body male mold surfaces, by " L-type " auxiliary silicon rubber Glue soft mode is installed in each piecemeal former, is compressed main body formpiston with each piecemeal former, is obtained the precast body of housing；
Step 4: remove polyimide resin glue unnecessary in housing precast body；
Step 5: housing precast body is cured；
Step 6: removing each piecemeal former, " L-type " auxiliary silicon rubber soft mode and main body formpiston successively, casing blank is obtained Part；
Step 7: the appearance and size of casing blank part, assembling mounting hole and air vent are processed using numerically-controlled machine tool；
Step 8: uniformly plating the coat of metal in shell inner surface, the thickness for plating the coat of metal is 2~3 μm, is maintained at true Do not fallen off under empty anaerobic state, vacuum degree control is in 95~100Pa, the Ω of the sheet resistance value of the coat of metal≤5.
In the step 1, the material of " L-type " auxiliary silicon rubber soft mode cures for hydroxy-end capped silicon rubber and silazane The proportioning of the composite material that agent is prepared by condensation cross-linking reaction, hydroxy-end capped silicon rubber and silazane curing agent is 100:3 ~100:5, preparation method is：First, hydroxy-end capped silicon rubber and silazane curing agent are continuously stirred under vacuum conditions 10~15min；Then, 2~6h of insulation vulcanize completely at 150 DEG C~200 DEG C in an oven；Finally, sampling carries out heat point Experimental test is solved, thermal decomposition experimental test result meets：Thermally decompose initial temperature >=400 DEG C.
In the step 2, fibre reinforced fabric is plain weave, twill or satin weave, fiber areal densities for 100~ 200g/m2, during braiding, the carbon fibre tow of warp-wise and broadwise is consistent；Nano conducting powders are nano silver particles or nanometer Ferroso-ferric oxide particle.
In the step 3, when main body male mold surfaces carry out housing prepreg overlay, by the way of gradient type laying Overall to spread 22 layers altogether, layers 1 and 2 laying use quality ratio is 2.8:1 carbon fiber/polyamide imines prepreg is spread Layer, the 3rd layer and the 4th layer of laying use quality ratio are 2.4:1 carbon fiber/polyamide imines prepreg carries out laying, the 5th layer and the 6 layers of laying use quality ratio are 2:1 carbon fiber/polyamide imines prepreg carries out laying, the 7th~22 layer of laying use quality ratio 1.8:1 carbon fiber/polyamide imines prepreg carries out laying, during laying, ensures that every layer of carbon fiber/polyamide imines prepreg is fine It is consistent to tie up direction, vacuum bag sealing pre-compacted is carried out 1 time for 4 layers per laying.
In the step 4, the technique for removing unnecessary polyimide resin glue is：Heating rate is 15~45 DEG C/h, Pre-compacted temperature is 80~170 DEG C, and soaking time is 5min~15min, and pressure is 0.2~0.8MPa, and gel content control exists 40%~60%, vacuum gauge pressure≤- 0.095MPa.
In the step 5, curing process is：Heating rate is 30~60 DEG C/h, and pressed temperature is 200~260 DEG C, Gu It is 320~400 DEG C to change temperature, and soaking time is 2~6h, and pressure is 0.8~1.2MPa, vacuum gauge pressure≤- 0.095MPa.
In the step 6, temperature control during piecemeal former form removal is under 40~60 DEG C of environment, during main body formpiston form removal Temperature control under 20~35 DEG C of environment.
The present invention has the following advantages that compared with prior art：
(1) present invention utilizes autoclave molding using negative and positive combination die, the molding mode of high-temperature-resisting silicon rubber flexible-mould assisted Technique is Integratively formed, and the housing of preparation has lightweight, resistance to 370 DEG C of high temperature, resistance to space environment, structural bearing multi-functional one The characteristic of body；
(2) present invention is modified the coupling skill of housing base and inner surface vacuum sputtering metal cladding using nano silver particles Art, had not only realized antenna housing electro-magnetic screen function, but also eliminated the installing structure space of traditional antenna connecting cable occupancy, into One step reduces interface connection, while improving space availability ratio, in turn simplify the structure type of housing；
(3) present invention improves shell inner surface light with by the way of resin content prepreg gradient laying from low to high Cleanliness, thickness is uniform, fine and close continuous when ensure that antenna housing interior surface metal cladding.
Brief description of the drawings
Fig. 1 is inventive antenna housing sectional view；
Fig. 2 is inventive antenna shell top view；
Fig. 3 is the schematic diagram of the casing forming mold of the present invention.
Embodiment
The present invention is described in further detail with specific embodiment below in conjunction with the accompanying drawings：
The present invention provides a kind of mars exploration landing rover integral antenna housing preparation method, by housing into Type mold manufacturing, the preparation of carbon fiber/polyamide imines prepreg, housing laying, imidization, curing, the demoulding, mechanical processing, housing Inner surface metal cladding and etc. realization.The present invention uses negative and positive combination die, the molding mode of high-temperature-resisting silicon rubber flexible-mould assisted, Integratively formed using autoclave forming process, the housing of preparation has lightweight, resistance to 370 DEG C of high temperature, resistance to space environment, knot Structure carries the characteristic of multifunctional all；It is meanwhile gold-plated using nano silver particles modification housing base and inner surface vacuum sputtering Belong to the coupling technique of layer, not only realized antenna housing electro-magnetic screen function, but also eliminate the peace of traditional antenna connecting cable occupancy Structure space is put, interface connection is further reduced, while improving space availability ratio, in turn simplify the structure type of housing.
It is as shown in Figure 1 antenna housing profile, Fig. 2 show antenna housing top view.As seen from the figure, a kind of Mars is visited Landing rover integral antenna housing is surveyed, is multi-step Varying-thickness thin-walled semi open model loose structure, including：Housing 1, gold Belong to coating 2, assembling mounting hole 3 and air vent 4.Wherein, 1 inner surface of the housing plating coat of metal 2, is then swashed on housing 1 Light projective iteration mechanical processing assembling mounting hole 3 and air vent 4.The material of housing 1 is composite material.
A kind of mars exploration landing rover integral antenna housing preparation method, comprises the following steps：
Step 1: casing forming mold manufactures；
As shown in figure 3, casing forming mold is manufactured using steel, including main body formpiston 7, piecemeal former 8 and " L-type " auxiliary Silicon rubber soft mode 9 forms, and for the curing of housing 1, " L-type " auxiliary silicon rubber soft mode 9 is located at main body formpiston 7 and piecemeal former 8 Step face contact position, exterior piecemeal former 8 are pressed on main body formpiston 7, and each piecemeal former 8 is free state, no pin, The limit methods such as screw are fixedly connected, by that freely movable exterior piecemeal former 8 and internal " L-type " can aid in silicon rubber soft mode Load is transmitted in 9 common realization pressurizations；Wherein, " L-type " auxiliary silicon rubber soft mode 9 cures for hydroxy-end capped silicon rubber and silazane The reaction of agent condensation cross-linking prepares blocking post-processing and forms, and the proportioning of hydroxy-end capped silicon rubber and silazane curing agent is 100:3 ~100:5, two kinds of component vacuum environments continuously stir 10~15min, then keep the temperature 2~6h at 150 DEG C~200 DEG C in an oven Vulcanize completely, sampling carries out thermal decomposition experimental test, and thermal decomposition initial temperature >=400 DEG C can use." L-type " auxiliary silicon The linear expansion coefficient of rubber soft mode 9 is according to 150~250 × 10-6Calculate, consider temperature change section (room temperature~400 DEG C), Deflection after product size and housing cure, carries out the size design of soft mode.
Main body formpiston 7 and piecemeal former 8 need to be passed through at high-temperature oxydation using 45# steel, Q235 steel or invar steel making, mould Manage and be maintained at 3.0~3.3 by airtight inspection, molding die working surface roughness, need to meet product surface appearance requirement.
Step 2: prepared by carbon fiber/polyamide imines prepreg；
Carbon fiber/polyamide imines prepreg is the fibre reinforced fabric after polyimide resin glue dipping；Carbon Fiber reinforcement fabric can be plain weave, twill or satin weave, and fiber areal densities are 100~200g/m2, during braiding, warp-wise and The carbon fibre tow of broadwise is consistent；The polyimide resin glue of prepreg is modified using nano conducting powders, is received Rice conducting particles can be nano silver particles or nano ferriferrous oxide particle, and polyimide resin and nano conducting powders Weight ratio is 10:(1.5~3), then modified polyimide resin glue is impregnated with fibre reinforced fabric, The quality proportioning of modified polyimide resin glue and fibre reinforced fabric is (1.5~2.8):1；Dipping is complete Room temperature hangs nylon grid film of the covering with air guide channel after 8~12h afterwards.
Step 3: carrying out laying on housing body formpiston using carbon fiber/polyamide imines prepreg, housing 1 is obtained Precast body；
With main body formpiston 7, piecemeal former 8, L-type " auxiliary silicon rubber soft mode 9 be laying mould, using carbon fiber/polyamide Asia Amine prepreg carries out 1 prepreg overlay of housing on 7 surface of main body formpiston, integrally spreads 22 layers altogether by the way of gradient type laying, Layers 1 and 2 laying use quality ratio is 2.8:1 carbon fiber/polyamide imines prepreg progress laying, the 3rd layer and the 4th layer Laying use quality ratio is 2.4:1 carbon fiber/polyamide imines prepreg carries out laying, the 5th layer and the 6th layer of laying use quality Than for 2:1 carbon fiber/polyamide imines prepreg carries out laying, and remaining laying use quality is than 1.8:1 carbon fiber/polyamide is sub- Amine prepreg carries out laying, and when laying ensures that every layer of carbon fiber/polyamide imines prepreg machine direction is consistent, per 4 layers of laying Carry out vacuum bag sealing pre-compacted 1 time, obtain 1 precast body of housing.
Step 4: imidization；
The unnecessary polyimide resin glue of 1 precast body of housing is removed, imidization technique is：15-45 DEG C of heating rate/h, Pre-compacted temperature is 80-170 DEG C, keeps the temperature 5min-15min, pressure 0.2-0.8MPa, and gel content is controlled in 40%-60%, vacuum Gauge pressure≤- 0.095MPa.
Step 5: 1 precast body of housing is cured；
Curing process is 30-60 DEG C of heating rate/h, and pressed temperature is 200-260 DEG C, and solidification temperature is 320-400 DEG C, Keep the temperature 2-6h, pressure 0.8-1.2MPa, vacuum gauge pressure≤- 0.095MPa.
Step 6: the demoulding；
Piecemeal former, " L-type " auxiliary silicon rubber soft mode and main body formpiston are removed successively, obtain 1 blank of housing；Piecemeal is cloudy Under 40-60 DEG C of environment, temperature control during main body formpiston form removal makes temperature control during mould form removal under 20-35 DEG C of environment The internal stress for curing obtained 1 blank of housing slowly discharges, and reduces risk of distortion.
Step 7: mechanical processing；
Appearance and size using laser projection system to housing 1, assembles mounting hole 3 and air vent 4 is positioned, and presses successively Digital control processing is carried out according to the order of assembling mounting hole 3, air vent 4 and appearance and size, it can be hard that mechanical processing, which selects cutter, Alloy cutter or diamond cutter, cutter rotating speed are controlled in 1100-2900r/min, feeding speed 70-200mm/min, feed Measure as 0.2-0.7mm, any type of coolant must not be used.
Step 8: 1 inner surface of housing plates the coat of metal 2；
The coat of metal 2 is uniformly plated in 1 inner surface of housing, its thickness is 2~3 μm, should be maintained under vacuum anaerobic state Do not fall off, vacuum degree control is in 95~100Pa, the Ω of the sheet resistance value of the coat of metal 2≤5.
Manufactured by casing forming mold, the preparation of carbon fiber/polyamide imines prepreg, housing laying, imidization, curing, The demoulding, mechanical processing, shell inner surface metal cladding and etc. realization.The present invention is using negative and positive combination die, high-temperature-resisting silicon rubber The molding mode of flexible-mould assisted, Integratively formed using autoclave forming process, the housing of preparation has lightweight, resistance to 370 DEG C high temperature, resistance to space environment, the characteristic of structural bearing multifunctional all；Meanwhile it is modified housing base using nano silver particles With the coupling technique of inner surface vacuum sputtering metal cladding, antenna housing electro-magnetic screen function was not only realized, but also eliminate tradition The installing structure space that antenna connecting cable takes, further reduces interface connection, while improving space availability ratio, and it is simple The structure type of housing is changed.
Embodiment 1：
A kind of mars exploration landing rover integral antenna housing preparation method, includes the following steps：
Step 1: casing forming mold manufactures；
As shown in figure 3, casing forming mold is manufactured using steel, including main body formpiston 7, piecemeal former 8 and " L-type " auxiliary Silicon rubber soft mode 9, for the curing of housing 1, " L-type " auxiliary silicon rubber soft mode 9 is located at 8 step of main body formpiston 7 and piecemeal former Shape face contact position, exterior piecemeal former 8 are pressed on main body formpiston 7, and each piecemeal former 8 is free state, no pin, screw It is fixedly connected Deng limit method, by that freely movable exterior piecemeal former 8 and internal " L-type " silicon rubber soft mode 9 can be aided in common Load is transmitted with realizing to pressurize；Wherein, " L-type " auxiliary silicon rubber soft mode 9 is hydroxy-end capped silicon rubber and silazane curing agent Condensation cross-linking reaction prepares blocking post-processing and forms, and the proportioning of hydroxy-end capped silicon rubber and silazane curing agent is 100:3, two Kind of component vacuum environment continuously stirs 10min, and then insulation 2h vulcanize completely at 160 DEG C in an oven, and sampling carries out heat Decomposition run is tested, and thermal decomposition initial temperature >=400 DEG C can use.The linear expansion coefficient of " L-type " auxiliary silicon rubber soft mode 9 is pressed According to 200 × 10-6Calculate, consider after temperature change section (room temperature~400 DEG C), 1 size of housing and housing 1 cure and deform Amount, carries out the size design of soft mode.
Main body formpiston 7 and piecemeal former 8 use invar steel making, and casing forming mold need to pass through high temperature oxidation process and lead to Airtight inspection is crossed, casing forming mold working surface roughness is maintained at 3.0, need to meet product surface appearance requirement.
Step 2: prepared by carbon fiber/polyamide imines prepreg；
Carbon fiber/polyamide imines prepreg is the fibre reinforced fabric after polyimide resin glue dipping；Carbon Fiber reinforcement fabric is satin weave, fiber areal densities 200g/m2, during braiding, the carbon fibre tow of warp-wise and broadwise is kept Unanimously；The polyimide resin glue of prepreg is modified using nano conducting powders, and nano conducting powders are nanometer silver granuel Son, and the weight ratio of polyimide resin and nano conducting powders is 10:2, then by modified polyimide resin glue with Fibre reinforced fabric is impregnated, the quality of modified polyimide resin glue and fibre reinforced fabric Match as 2.8:1、2.4：1、2:1 and 1.8:1 four kinds of specifications；Covering carries air guide channel after the completely rear room temperature of dipping hangs 12h Nylon grid film.
Step 3: carrying out laying on main body formpiston 7 using carbon fiber/polyamide imines prepreg, the prefabricated of housing 1 is obtained Body；
With main body formpiston 7, piecemeal former 8, L-type " auxiliary silicon rubber soft mode 9 be laying mould, using carbon fiber/polyamide Asia Amine prepreg carries out 1 prepreg overlay of housing on 7 surface of main body formpiston, integrally spreads 22 layers altogether by the way of gradient type laying, Layers 1 and 2 laying use quality ratio is 2.8:1 carbon fiber/polyamide imines prepreg progress laying, the 3rd layer and the 4th layer Laying use quality ratio is 2.4:1 carbon fiber/polyamide imines prepreg carries out laying, the 5th layer and the 6th layer of laying use quality Than for 2:1 carbon fiber/polyamide imines prepreg carries out laying, and remaining laying use quality is than 1.8:1 carbon fiber/polyamide is sub- Amine prepreg carries out laying, and when laying ensures that every layer of carbon fiber/polyamide imines prepreg machine direction is consistent, per 4 layers of laying Carry out vacuum bag sealing pre-compacted 1 time, obtain 1 precast body of housing.
Step 4: imidization；
The unnecessary polyimide resin glue of 1 precast body of housing is removed, imidization technique is：Heating rate is 15 DEG C/h, Pre-compacted temperature is 80 DEG C, keeps the temperature 5min, pressure 0.2MPa, gel content control is 40%, vacuum gauge pressure≤- 0.095MPa.
Step 5: 1 precast body of housing is cured；
Curing process is 60 DEG C/h of heating rate, and pressed temperature is 200 DEG C, and solidification temperature is 400 DEG C, keeps the temperature 6h, pressure 0.8MPa, vacuum gauge pressure≤- 0.095MPa.
Step 6: the demoulding；
Piecemeal former, " L-type " auxiliary silicon rubber soft mode and main body formpiston are removed successively, obtain 1 blank of housing；Piecemeal is cloudy Under 40 DEG C of environment, temperature control during main body formpiston form removal makes to cure temperature control during mould form removal under 25 DEG C of environment To the internal stress of 1 blank of housing slowly discharge, reduce risk of distortion.
Step 7: mechanical processing；
Appearance and size using laser projection system to housing 1, assembles mounting hole 3 and air vent 4 is positioned, and presses successively Digital control processing is carried out according to the order of assembling mounting hole 3, air vent 4 and appearance and size, it can be hard that mechanical processing, which selects cutter, Alloy cutter or diamond cutter, the control of cutter rotating speed are in 1100r/min, feeding speed 70mm/min, the depth of cut 0.2mm, must not use any type of coolant.
Step 8: 1 inner surface of housing plates the coat of metal 2；
The coat of metal 2 is uniformly plated in 1 inner surface of housing, its thickness is 2.5 μm, should be maintained under vacuum anaerobic state not Come off, vacuum degree control is in 100Pa, the Ω of the sheet resistance value of the coat of metal 2≤5.
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.

Claims (10)

  1. A kind of 1. mars exploration landing rover integral antenna housing, it is characterised in that including：Housing (1), the coat of metal (2), mounting hole (3) and air vent (4) are assembled；Housing (1) is square structure, if middle part is recessed inwardly to form dried layer Step-edge Junction Structure, housing (1) inner surface plating coat of metal (2), housing (1) edge distribution have an assembling mounting hole (3), on ledge structure side elevation Air vent (4) is distributed with.
  2. A kind of 2. mars exploration landing rover integral antenna housing according to claim 1, it is characterised in that：Institute The material for stating the coat of metal (2) is densification continuous aluminium coat, copper coating, silvering or the gold plate of acidification.
  3. 3. a kind of mars exploration landing rover integral antenna housing according to claim 1 or 2, its feature exist In：The coat of metal (2) is plated on housing (1) by the method that chemical plating, impulse jet technique coating or vacuum sputtering plate.
  4. 4. a kind of mars exploration landing rover integral antenna housing preparation method, it is characterised in that comprise the following steps：
    Step 1: according to the shape of housing (1), casing forming mold is manufactured, and casing forming mold is carried out at high-temperature oxydation Reason and airtight inspection so that the surface roughness of the forming face of casing forming mold is maintained in the range of 3.0~3.3；
    The mould molding mould includes main body formpiston (7), piecemeal former (8) and " L-type " aid in silicon rubber soft mode (9), two Piecemeal former (8) is symmetrical on interface, the inner space that main body formpiston (7) is formed after coordinating with two piecemeal formers (8) with Housing (1) structure is consistent；" L-type " auxiliary silicon rubber soft mode (9) is respectively at piecemeal former (8) interior step face；
    Step 2: preparing carbon fiber/polyamide imines prepreg, carbon fiber/polyamide imines prepreg is polyimide resin glue Fibre reinforced fabric after dipping；Specifically preparation method is：Nano conducting powders are used to polyimide resin glue It is modified, and the weight ratio of polyimide resin and nano conducting powders is 10:(1.5~3), by modified polyimides Resin adhesive liquid is with fibre reinforced fabric according to (1.5~2.8):1 quality proportioning is impregnated；After dipping is complete, room After temperature hangs 8~12h, nylon grid film of the covering with air guide channel；
    Step 3: carrying out carbon fiber/polyamide imines prepreg overlay on main body formpiston (7) surface, " L-type " is aided in into silicon rubber Soft mode (9) is installed in each piecemeal former (8), is compressed main body formpiston (7) with each piecemeal former (8), is obtained the prefabricated of housing (1) Body；
    Step 4: remove polyimide resin glue unnecessary in housing (1) precast body；
    Step 5: housing (1) precast body is cured；
    Step 6: removing each piecemeal former (8), " L-type " auxiliary silicon rubber soft mode (9) and main body formpiston (7) successively, housing is obtained (1) blank；
    Step 7: the appearance and size of housing (1) blank, assembling mounting hole (3) and air vent (4) are carried out using numerically-controlled machine tool Processing；
    Step 8: uniformly plating the coat of metal (2) in housing (1) inner surface, the thickness of the plating coat of metal (2) is 2~3 μm, is protected Hold and do not fallen off under vacuum anaerobic state, vacuum degree control is in 95~100Pa, the Ω of the sheet resistance value of the coat of metal (2)≤5.
  5. 5. a kind of mars exploration landing rover integral antenna housing preparation method according to claim 4, it is special Sign is：In the step 1, the material of " L-type " auxiliary silicon rubber soft mode (9) is consolidated for hydroxy-end capped silicon rubber with silazane The proportioning of the composite material that agent is prepared by condensation cross-linking reaction, hydroxy-end capped silicon rubber and silazane curing agent is 100: 3~100:5, preparation method is：First, hydroxy-end capped silicon rubber and silazane curing agent are continuously stirred under vacuum conditions 10~15min；Then, 2~6h of insulation vulcanize completely at 150 DEG C~200 DEG C in an oven；Finally, sampling carries out heat point Experimental test is solved, thermal decomposition experimental test result meets：Thermally decompose initial temperature >=400 DEG C.
  6. 6. a kind of mars exploration landing rover integral antenna housing preparation method according to claim 4 or 5, its It is characterized in that：In the step 2, fibre reinforced fabric is plain weave, twill or satin weave, fiber areal densities for 100~ 200g/m2, during braiding, the carbon fibre tow of warp-wise and broadwise is consistent；Nano conducting powders are nano silver particles or nanometer Ferroso-ferric oxide particle.
  7. 7. a kind of mars exploration landing rover integral antenna housing preparation method according to claim 6, it is special Sign is：In the step 3, when main body male mold surfaces carry out housing (1) prepreg overlay, using the side of gradient type laying Formula integrally spreads 22 layers altogether, and layers 1 and 2 laying use quality ratio is 2.8:1 carbon fiber/polyamide imines prepreg is spread Layer, the 3rd layer and the 4th layer of laying use quality ratio are 2.4:1 carbon fiber/polyamide imines prepreg carries out laying, the 5th layer and the 6 layers of laying use quality ratio are 2:1 carbon fiber/polyamide imines prepreg carries out laying, the 7th~22 layer of laying use quality ratio 1.8:1 carbon fiber/polyamide imines prepreg carries out laying, during laying, ensures that every layer of carbon fiber/polyamide imines prepreg is fine It is consistent to tie up direction, vacuum bag sealing pre-compacted is carried out 1 time for 4 layers per laying.
  8. 8. a kind of mars exploration landing rover integral antenna housing preparation method according to claim 7, it is special Sign is：In the step 4, the technique for removing unnecessary polyimide resin glue is：Heating rate is 15~45 DEG C/h, Pre-compacted temperature is 80~170 DEG C, and soaking time is 5min~15min, and pressure is 0.2~0.8MPa, and gel content control exists 40%~60%, vacuum gauge pressure≤- 0.095MPa.
  9. 9. a kind of mars exploration landing rover integral antenna housing preparation method according to claim 7 or 8, its It is characterized in that：In the step 5, curing process is：Heating rate is 30~60 DEG C/h, and pressed temperature is 200~260 DEG C, Gu It is 320~400 DEG C to change temperature, and soaking time is 2~6h, and pressure is 0.8~1.2MPa, vacuum gauge pressure≤- 0.095MPa.
  10. 10. a kind of mars exploration landing rover integral antenna housing preparation method according to claim 9, it is special Sign is：In the step 6, temperature control during piecemeal former (8) form removal under 40~60 DEG C of environment, tear open by main body formpiston (7) Temperature control during mould is under 20~35 DEG C of environment.
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CN109857138A (en) * 2019-01-28 2019-06-07 北京卫星环境工程研究所 Quick Method of Adjustment based on the multiple coupled size chain mechanism of the non-referenced structure of spacecraft
CN110549644A (en) * 2019-09-06 2019-12-10 长沙晶优新材料科技有限公司 Antenna cover plate and profiling prefabricated member thereof
CN111430902A (en) * 2020-03-20 2020-07-17 上海阿莱德实业股份有限公司 Preparation method of sandwich antenna housing integrating antenna and antenna housing prepared by preparation method
CN112026204A (en) * 2020-08-18 2020-12-04 四川九洲电器集团有限责任公司 Compression molding method and pre-compaction mold for antenna housing
CN112590249A (en) * 2020-12-03 2021-04-02 湖北三江航天江北机械工程有限公司 Cable cover integral forming method
CN112697637A (en) * 2020-12-22 2021-04-23 湖北航天化学技术研究所 Method for measuring volatile content of heat insulation layer material for solid rocket engine
CN114750433A (en) * 2022-03-25 2022-07-15 中国电子科技集团公司第三十八研究所 RTM (resin transfer molding) mold and molding method for double-edge variable-section thin-wall composite material antenna cylinder

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CN203013919U (en) * 2013-01-07 2013-06-19 深圳市鼎耀科技有限公司 Airborne satellite navigation multi-frequency antenna
CN104513447A (en) * 2013-09-30 2015-04-15 深圳光启创新技术有限公司 Electrical-conductive composite material and preparation method thereof
CN107134642A (en) * 2017-04-21 2017-09-05 航天材料及工艺研究所 A kind of resistance to 450 DEG C of quartz/composite polyimide material antenna house and preparation method

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CN203013919U (en) * 2013-01-07 2013-06-19 深圳市鼎耀科技有限公司 Airborne satellite navigation multi-frequency antenna
CN104513447A (en) * 2013-09-30 2015-04-15 深圳光启创新技术有限公司 Electrical-conductive composite material and preparation method thereof
CN107134642A (en) * 2017-04-21 2017-09-05 航天材料及工艺研究所 A kind of resistance to 450 DEG C of quartz/composite polyimide material antenna house and preparation method

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109857138A (en) * 2019-01-28 2019-06-07 北京卫星环境工程研究所 Quick Method of Adjustment based on the multiple coupled size chain mechanism of the non-referenced structure of spacecraft
CN109857138B (en) * 2019-01-28 2021-10-01 北京卫星环境工程研究所 Rapid installation and adjustment method based on spacecraft non-reference structure multi-coupling dimension chain mechanism
CN110549644A (en) * 2019-09-06 2019-12-10 长沙晶优新材料科技有限公司 Antenna cover plate and profiling prefabricated member thereof
CN111430902A (en) * 2020-03-20 2020-07-17 上海阿莱德实业股份有限公司 Preparation method of sandwich antenna housing integrating antenna and antenna housing prepared by preparation method
CN112026204A (en) * 2020-08-18 2020-12-04 四川九洲电器集团有限责任公司 Compression molding method and pre-compaction mold for antenna housing
CN112590249A (en) * 2020-12-03 2021-04-02 湖北三江航天江北机械工程有限公司 Cable cover integral forming method
CN112697637A (en) * 2020-12-22 2021-04-23 湖北航天化学技术研究所 Method for measuring volatile content of heat insulation layer material for solid rocket engine
CN112697637B (en) * 2020-12-22 2023-06-30 湖北航天化学技术研究所 Method for measuring volatile component content of heat insulation layer material for solid rocket engine
CN114750433A (en) * 2022-03-25 2022-07-15 中国电子科技集团公司第三十八研究所 RTM (resin transfer molding) mold and molding method for double-edge variable-section thin-wall composite material antenna cylinder
CN114750433B (en) * 2022-03-25 2023-09-05 中国电子科技集团公司第三十八研究所 Double-edge variable-section thin-wall composite material antenna tube RTM (real time kinematic) die and forming method

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