CN111769361B - Precise preparation method of high-temperature-resistant foam A interlayer composite material radome - Google Patents

Precise preparation method of high-temperature-resistant foam A interlayer composite material radome Download PDF

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Publication number
CN111769361B
CN111769361B CN202010777730.8A CN202010777730A CN111769361B CN 111769361 B CN111769361 B CN 111769361B CN 202010777730 A CN202010777730 A CN 202010777730A CN 111769361 B CN111769361 B CN 111769361B
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core layer
temperature
radome
outer skin
inner skin
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CN111769361A (en
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俞玉澄
李伟
刘兵
李冰
皋利利
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Shanghai Radio Equipment Research Institute
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Shanghai Radio Equipment Research Institute
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    • 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
    • H01Q1/422—Housings not intimately mechanically associated with radiating elements, e.g. radome comprising two or more layers of dielectric material
    • H01Q1/424—Housings not intimately mechanically associated with radiating elements, e.g. radome comprising two or more layers of dielectric material comprising a layer of expanded material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B1/00—Layered products having a general shape other than plane
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/18—Layered products comprising a layer of synthetic resin characterised by the use of special additives
    • B32B27/20—Layered products comprising a layer of synthetic resin characterised by the use of special additives using fillers, pigments, thixotroping agents
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/28—Layered products comprising a layer of synthetic resin comprising synthetic resins not wholly covered by any one of the sub-groups B32B27/30 - B32B27/42
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/02—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by a sequence of laminating steps, e.g. by adding new layers at consecutive laminating stations
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/06—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B38/18—Handling of layers or the laminate
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/18—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by features of a layer of foamed material
    • B32B5/20—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by features of a layer of foamed material foamed in situ
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B2038/0052—Other operations not otherwise provided for
    • B32B2038/0084—Foaming
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2255/00—Coating on the layer surface
    • B32B2255/10—Coating on the layer surface on synthetic resin layer or on natural or synthetic rubber layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2255/00—Coating on the layer surface
    • B32B2255/26—Polymeric coating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2266/00—Composition of foam
    • B32B2266/02—Organic
    • B32B2266/0214—Materials belonging to B32B27/00
    • B32B2266/0278—Polyurethane
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/20—Properties of the layers or laminate having particular electrical or magnetic properties, e.g. piezoelectric
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/30—Properties of the layers or laminate having particular thermal properties
    • B32B2307/306—Resistant to heat
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2457/00—Electrical equipment

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Details Of Aerials (AREA)

Abstract

The invention discloses a precise preparation method of a high-temperature-resistant foam A interlayer composite material radome, which comprises the following steps: preparing a core layer fusible pattern by adopting a core layer forming die; preparing an inner skin prefabricated body on the outer surface of a male die of an antenna housing forming die; preparing an outer skin preform on the outer surface of the core layer investment pattern; closing the male die, the female die and the core layer investment pattern to obtain a closed radome forming die; curing and coring the molded antenna housing forming mold to obtain a foam core layer cavity; preparing a sandwich layer radome blank in the foam core layer cavity; and performing finish machining on the interlayer radome blank to obtain the high-temperature-resistant foam A interlayer composite material radome. The invention solves the problem of high processing difficulty of the traditional foam core layer and the inner and outer skins, improves the size precision and ensures the broadband wave-transmitting capacity of the sandwich antenna cover by respectively using the precise core layer investment pattern and the precise forming die as the reference of the foam core layer and the sandwich antenna cover.

Description

Precise preparation method of high-temperature-resistant foam A interlayer composite material radome
Technical Field
The invention relates to the technical field of composite material structure forming processes, in particular to a precise preparation method of a high-temperature-resistant foam A interlayer composite material radome.
Background
The antenna housing is an important component of an aerospace guidance system. With the continuous development of aerospace guidance systems, the comprehensive requirements of the antenna housing on the aspects of broadband wave-transmitting performance, mechanical performance, thermal performance, lightweight design and the like are increasingly improved. The interlayer A radome prepared based on the high-temperature-resistant resin foam and the composite material well meets the requirements, and becomes one of key implementation directions of the aerospace guidance system radome.
At present, there are three main types of preparation methods for foam sandwich composite material antenna housing, specifically as follows:
firstly, an inner skin, an outer skin and a foam core layer are respectively prepared, and then the inner skin, the outer skin and the foam core layer are connected through connecting means such as gluing, screwing, riveting and the like to prepare the foam sandwich radome, as shown in patents of CN103660410A wave-transparent sandwich material for radomes, a manufacturing method and application thereof, CN105172281A wave-transparent cover with a long-time high-temperature resistant sandwich structure and the like.
Secondly, firstly preparing a foam core layer, then layering the inner surface and the outer surface of the foam core layer, and then carrying out integrated semi-co-curing to prepare the foam interlayer radome, as shown in patents of CN105922703A composite material radome preparation method of thin-wall foam interlayer structure, CN106739043A PMI foam interlayer aircraft radome and manufacturing method thereof, and the like.
And thirdly, respectively preparing an inner skin and an outer skin, then assembling and molding the inner skin and the outer skin, and preparing the foam interlayer radome in a reserved core cavity by in-situ foaming by taking the inner skin and the outer skin as a mold, as shown in CN109638445A, a high-temperature-resistant foam A interlayer composite material radome and a preparation method thereof.
At present, the common problem of the method I and the method II is that the contradiction between high requirements on the forming and processing precision of the foam core layer and the fragility and the large processing difficulty of the foam core layer is difficult to reconcile. In addition, the first method also has the problems of high requirements on the processing precision of the inner skin and the outer skin, glue seams or holes after assembly and the like; the second method also has the problem that the core layer is easy to damage when various operations such as layering, prepressing, mold closing and the like are carried out on the foam core layer.
Although the problems are successfully avoided by the in-situ foaming method, obvious assembly errors are easily introduced in the process of firstly preparing the inner skin and the outer skin and assembling the inner skin and the outer skin into the die, the concentricity and the coaxiality of the inner skin and the outer skin of the sandwich layer radome are influenced, and meanwhile, the thickness of the foam core layer has obvious errors.
Disclosure of Invention
The invention aims to provide a precise preparation method of a high-temperature-resistant foam A interlayer composite material radome. The method aims to solve the problems that the traditional foam core layer is high in processing difficulty and the requirement on the processing precision of the inner skin and the outer skin is high, the precision core layer investment pattern is used as a forming reference of the foam core layer, the precision forming mold is used as an appearance reference of the sandwich antenna cover, the problem that the processing difficulty of the high-temperature-resistant resin foam core layer is high is solved, the dimensional precision of each layer and the whole of the sandwich antenna cover is improved, and the broadband wave-transmitting capacity of the sandwich antenna cover is effectively guaranteed.
In order to achieve the purpose, the invention provides a precise preparation method of a high-temperature-resistant foam A interlayer composite material radome, which comprises the following steps:
step 1: preparing a core layer investment pattern by adopting a core layer forming die based on an injection molding process;
step 2: preparing an inner skin prefabricated body on the outer surface of a male die of an antenna housing forming die;
and step 3: preparing an outer skin preform on the outer surface of the core layer investment pattern;
and 4, step 4: closing a male die of the radome forming die, an inner skin prefabricated body on the outer surface of the male die, a core layer fusion mold, an outer skin prefabricated body on the surface of the core layer fusion mold and a female die of the radome forming die to obtain the closed radome forming die;
and 5: curing and coring the molded antenna housing forming mold to obtain a foam core layer cavity;
step 6: preparing a sandwich layer radome blank in a foam core layer cavity based on an in-situ foaming method;
and 7: and performing finish machining on the interlayer radome blank to obtain the high-temperature-resistant foam A interlayer composite material radome.
Most preferably, the preparation of the inner skin preform further comprises the steps of:
step 2.1: filling the inner skin fiber material on the outer surface of a male die of an antenna housing forming die;
step 2.2: coating the inner skin fiber material, and performing primary pre-compaction on the coated inner skin fiber material;
step 2.3: and removing the redundant glue solution on the inner skin fiber material subjected to the first pre-compaction for the first time to obtain an inner skin preform.
Most preferably, the preparation of the outer skin preform further comprises the steps of:
step 3.1: filling and coating the outer skin fiber material on the outer surface of the core layer investment pattern;
step 3.2: coating the outer skin fiber material, and performing secondary pre-compaction on the coated outer skin fiber material;
step 3.3: and removing the redundant glue solution on the second precompacted outer skin fiber material for the second time to obtain the outer skin prefabricated body.
Most preferably, closing the mold further comprises the steps of:
step 4.1: slowly pressing the inner skin preform to the inner surface of the core layer investment mold, and ensuring that the inner skin preform is attached to the inner surface of the core layer investment mold;
step 4.2: slowly pressing the outer skin prefabricated part to the inner surface of a female die of the radome forming die, and ensuring that the outer skin prefabricated part is attached to the inner surface of the female die;
step 4.3: and (3) completing die assembly of a male die and a female die of the radome forming die, and positioning the core layer investment pattern in a middle interlayer of the inner skin prefabricated body and the outer skin prefabricated body.
Most preferably, curing and coring further comprises the steps of:
step 5.1: pre-curing and heating the inner skin prefabricated body and the outer skin prefabricated body to obtain a pre-cured inner skin prefabricated body and a pre-cured outer skin prefabricated body;
step 5.2: curing and heating the pre-cured inner skin prefabricated body and the pre-cured outer skin prefabricated body to obtain an inner skin and an outer skin;
step 5.3: and melting and heating the core layer melting mold of the intermediate sandwich layer of the inner skin and the outer skin to prepare a foam core layer cavity.
Most preferably, the pre-cure heating comprises the steps of:
step 5.1.1: heating the inner skin prefabricated body and the outer skin prefabricated body to raise the temperature, and raising the temperature of the inner skin prefabricated body and the temperature of the outer skin prefabricated body to a first temperature;
step 5.1.2: keeping the first temperature unchanged, and pressurizing and exhausting the inner skin preform and the outer skin preform heated to the first temperature according to a compression molding process to obtain a pre-cured inner skin preform and a pre-cured outer skin preform.
Most preferably, the temperature of the inner skin and the outer skin is raised to the second temperature.
Most preferably, the melting and heating comprises the steps of:
step 5.3.1: heating the core layer melting mold of the intermediate interlayer of the inner skin and the outer skin for the first time, and raising the temperature of the inner skin, the outer skin and the core layer melting mold to a third temperature;
step 5.3.2: keeping the third temperature unchanged, melting the core layer by a melting mold, and forming a core layer cavity by the intermediate interlayer;
step 5.3.3: heating the core layer cavity for the second time, and raising the temperature of the core layer cavity to a fourth temperature to obtain a heated core layer cavity;
step 5.3.4: and cooling the heated core layer cavity, and irrigating the cooled core layer cavity to prepare the foam core layer cavity.
Most preferably, the preparation of the sandwich radome blank further comprises the steps of:
step 6.1: adding the mixed solution into a foam core layer cavity;
step 6.2: heating the foam core layer cavity added with the mixed solution based on an in-situ foaming method to prepare a foam core layer;
step 6.3: and preparing a sandwich layer radome blank according to the foam core layer.
Most preferably, the finishing further comprises the steps of:
step 7.1: the interlayer radome blank is removed from the radome forming die;
step 7.2: and (4) carrying out molding process auxiliary cutting processing on the removed interlayer radome blank to prepare the high-temperature-resistant foam A interlayer composite material radome.
By applying the method, the problems that the traditional foam core layer is high in processing difficulty and the requirement on the processing precision of the inner skin and the outer skin is high are solved, the precision core layer investment pattern is used as the forming reference of the foam core layer, the precision forming mold is used as the appearance reference of the interlayer radome, the problem that the processing difficulty of the high-temperature-resistant resin foam core layer is high is solved, the dimensional precision of each layer and the whole interlayer radome is improved, and the broadband wave-transmitting capacity of the interlayer radome is effectively guaranteed.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the precise preparation method of the high-temperature-resistant foam A interlayer composite material radome, the core layer investment pattern is prepared by using the pattern material with good processability and mechanical property, so that the problems of high processing difficulty and low precision of the high-temperature-resistant resin foam core layer and frangibility of the foam core layer in the operation processes of layering, assembling, mold closing and the like are effectively avoided.
2. According to the precise preparation method of the high-temperature-resistant foam A interlayer composite material radome, the precision core layer investment pattern is used as the forming size standard of the foam core layer, the precision forming mold is used as the appearance size standard of the interlayer radome, the size precision of each layer and the whole interlayer radome is greatly improved, the broadband wave-transmitting capacity of the interlayer radome is effectively guaranteed, and the method is particularly suitable for products with extremely high requirements on the broadband wave-transmitting performance.
Drawings
Fig. 1 is a schematic flow chart of a precise preparation method of a high-temperature-resistant foam a interlayer composite material radome provided by the invention;
FIG. 2 is a schematic diagram of the assembly of a male mold, a female mold and a core pattern provided by the present invention;
fig. 3 is a schematic diagram of a foam core layer prepared according to the present invention.
Detailed Description
The invention will be further described by the following specific examples in conjunction with the drawings, which are provided for illustration only and are not intended to limit the scope of the invention.
The invention provides a precise preparation method of a high-temperature-resistant foam A interlayer composite material radome, which comprises the following steps as shown in figure 1:
step 1: preparing a core layer fusible pattern 4 by adopting a core layer forming die based on an injection molding process; wherein, the preparation of the core layer investment pattern 4 further comprises the following steps:
step 1.1: preparing a core layer investment blank by using a core layer forming die and adopting an injection molding process;
step 1.2: and processing and repairing the core layer investment blank to prepare the core layer investment 4 of the high-temperature-resistant foam A interlayer composite material radome.
The mold material used for preparing the core layer investment pattern 4 has good mechanical strength, thermal stability, processability and low shrinkage rate, and has good fluidity after being melted. The mould material can select different systems of thermoplastic polyurethane according to the curing temperature characteristic and the temperature resistance of the high-temperature resistant resin, and the softening point, the melting point and the shrinkage rate of the mould material are modified and designed, so that the requirement that the resin curing starting temperature is less than the mould material softening point, less than the resin typical curing temperature, less than the mould material melting point, less than the mould material decomposition temperature and less than the resin temperature resistance is met.
In the embodiment, the core layer investment pattern 4 is made of aromatic polyether type thermoplastic polyurethane, and cured silicon-containing aryne resin powder filler is added to reduce the shrinkage rate of the core layer pattern material, wherein the mass fraction of the silicon-containing aryne resin powder filler is controlled to be 5-25%; the processing and repairing are to control the error of the external dimension of the core layer melting mold 4 within plus or minus 0.05 mm.
Step 2: preparing an inner skin preform 5 on the outer surface of a male die 7 of an antenna housing forming die; wherein, the preparation of the inner skin preform 5 further comprises the following steps:
step 2.1: filling the inner skin fiber material on the outer surface of a male die 7 of the antenna housing forming die;
step 2.2: wrapping the periphery of the inner skin fiber material by adopting vacuum bag wrapping, and performing primary pre-compaction on the wrapped inner skin fiber material;
step 2.3: and (3) removing the redundant glue solution on the internal skin fiber material subjected to the first pre-compaction for the first time to obtain the internal skin preform 5 positioned on the outer surface of the male die 7 of the radome forming die.
The inner skin fiber material is an inner skin prepreg or an inner skin fiber reinforcement body brushed with high-temperature-resistant resin; in this embodiment, the inner skin fiber material is a quartz fiber reinforcement made of brushing liquid silicon-containing aryne resin; the inner skin prefabricated body 5 is made of quartz fiber reinforced silicon-containing aryne resin.
And step 3: preparing an outer skin preform 6 on the outer surface of the core layer investment pattern 4; wherein, the preparation of the outer skin preform 6 further comprises the following steps:
step 3.1: filling and coating the outer skin fiber material on the outer surface of the core layer melting mold 4;
step 3.2: wrapping the periphery of the outer skin fiber material by adopting vacuum bag wrapping, and performing secondary pre-compaction on the wrapped outer skin fiber material;
step 3.3: and (4) removing the redundant glue solution on the outer skin fiber material subjected to the secondary pre-compaction for the second time to obtain an outer skin preform 6 positioned on the outer surface of the core layer melting mold 4.
The outer skin fiber material is outer skin prepreg or an outer skin fiber reinforcement body brushed with high-temperature-resistant resin; in this embodiment, the outer skin fiber material is a quartz fiber reinforcement made of brushing liquid silicon-containing aryne resin; the outer skin prefabricated body 6 is made of quartz fiber reinforced silicon-containing aryne resin.
And 4, step 4: closing a male die 7 of the radome forming die, an inner skin prefabricated body 5 on the outer surface of the male die 7, a core layer melting mold 4, an outer skin prefabricated body 6 on the surface of the core layer melting mold 4 and a female die 8 of the radome forming die to obtain the closed radome forming die; as shown in fig. 2, the mold closing further comprises the following steps:
step 4.1: slowly pressing the inner skin preform 5 on the outer surface of the male die 7 of the radome forming die to the inner surface of the core layer melting mold 4, and ensuring that the inner skin preform 5 on the outer surface of the male die 7 is attached to the inner surface of the core layer melting mold 4;
step 4.2: slowly pressing the outer skin prefabricated body 6 on the outer surface of the core layer melting mold 4 to the inner surface of a female mold 8 of an antenna housing forming mold, and ensuring that the outer skin prefabricated body 6 on the outer surface of the core layer melting mold 4 is attached to the inner surface of the female mold 8;
step 4.3: and (3) completing the die assembly of a male die 7 and a female die 8 of the radome forming die, and positioning the core layer melting mold 4 in the interlayer between the inner skin prefabricated body 5 and the outer skin prefabricated body 6.
And 5: and transferring the antenna housing forming die after die assembly to a molding press for curing and coring to obtain a solidified foam core layer cavity after coring. Wherein curing and coring further comprises the steps of:
step 5.1: and (3) pre-curing and heating the inner skin prefabricated body 5 and the outer skin prefabricated body 6 in the matched antenna housing forming mold to obtain the pre-cured inner skin prefabricated body and the pre-cured outer skin prefabricated body in the matched antenna housing forming mold.
Wherein, the pre-curing heating comprises the following steps:
step 5.1.1: heating the inner skin prefabricated body 5 and the outer skin prefabricated body 6 in the antenna housing forming die after die assembly, and raising the temperature of the inner skin prefabricated body 5 and the temperature of the outer skin prefabricated body 6 to a first temperature T1(ii) a In the present embodiment, the first temperature T1Is 140 to 160 ℃;
step 5.1.2: maintaining the first temperature T1Keeping the temperature for 2h, heating to the first temperature T according to the compression molding process1And a first temperature T1And pressurizing and exhausting the outer skin prefabricated body to obtain a pre-cured inner skin prefabricated body and a pre-cured outer skin prefabricated body.
Step 5.2: curing and heating the pre-cured inner skin prefabricated part and the pre-cured outer skin prefabricated part in the matched antenna housing forming mold to obtain an inner skin 1 and an outer skin 2 in the matched antenna housing forming mold; wherein the temperature of the inner skin 1 and the outer skin 2 is raised to a second temperature T2The reaction is kept for 2 h.
In the embodiment, the inner skin 1 and the outer skin 2 are made of quartz fiber reinforced silicon-containing aryne resin composite materials; second temperature T2Is 170-190 ℃.
Step 5.3: melting and heating the core layer melting mold 4 of the interlayer between the inner skin 1 and the outer skin 2 to prepare a foam core layer cavity; wherein, the melting and heating comprises the following steps:
step 5.3.1: heating the core layer melting mold 4 of the interlayer between the inner skin 1 and the outer skin 2 for the first time, and raising the temperature of the inner skin 1, the outer skin 2 and the core layer melting mold 4 to a third temperature T3(ii) a In the present embodiment, the third temperature T3Is 210 to 240 ℃;
step 5.3.2: maintaining the third temperature T3And the core layer 4 of the intermediate sandwich between the inner skin 1 and the outer skin 2 is melted without changing for 4 hours, and the intermediate sandwich forms a core layer cavity;
step 5.3.3: heating the residual core layer melting mold 4 in the core layer cavity for the second time, and raising the temperature of the core layer cavity to a fourth temperature T4And keeping the core-layer pattern for 1 hour, and heating and decomposing the residual core-layer pattern 4 to obtain a heated core-layer pattern cavity; in the present embodiment, the fourth temperature T4300-320 ℃;
step 5.3.4: cooling the heated core-layer cavity, irrigating the cooled core-layer cavity by using a cleaning agent, removing the residual core-layer melting mold 4 after heating decomposition, and preparing a foam core-layer cavity; in this example, the cleaning agent is acetone.
First temperature T1Second temperatureDegree T2A third temperature T3And a fourth temperature T4Designing according to the physicochemical characteristics of high-temperature-resistant resin and selected mould material; in the present embodiment, the resin curing initiation temperature ≦ T1Soft point of molding material < typical curing temperature of resin ═ T2Melting point of < mold material ≤ T3< mold material decomposition temperature < T4The resin resists temperature.
Step 6: preparing a sandwich layer radome blank in a foam core layer cavity based on an in-situ foaming method; the preparation method of the sandwich radome blank further comprises the following steps:
step 6.1: after the cleaning agent is completely volatilized, adding the mixed solution into the foam core layer cavity; wherein the mixed solution is a mixed powder of high-temperature-resistant resin and a foaming agent; the mass fraction of the foaming agent is controlled between 0.5% and 5%.
Step 6.2: as shown in fig. 3, the interlayer radome mold added with the mixed solution is moved into an oven to be heated, and a foam core layer 3 is prepared based on an in-situ foaming method; in the present embodiment, the material of the foam core layer 3 is silicon-containing aryne resin foam; the foaming temperature conditions are respectively 140-160 ℃, 15min or 170-190 ℃ and 2h or 210-240 ℃ and 4 h.
Step 6.3: and preparing a sandwich layer radome blank according to the foam core layer 3, closing the oven, and cooling the sandwich layer radome blank and the radome forming die to room temperature.
And 7: performing finish machining on the interlayer radome blank to obtain a high-temperature-resistant foam A interlayer composite radome; wherein, the finish machining also comprises the following steps:
step 7.1: the interlayer radome blank is removed from the radome forming die;
step 7.2: and (4) carrying out molding process auxiliary cutting processing on the removed interlayer radome blank to prepare the high-temperature-resistant foam A interlayer composite material radome.
In this embodiment, the total wall thickness error, the inner and outer skin wall thickness error, and the foam core layer wall thickness error of the high temperature resistant foam a sandwich composite material radome can be controlled within ± 0.05 mm.
The working principle of the invention is as follows:
preparing a core layer investment blank by using a core layer forming die, and processing and repairing the core layer investment blank to prepare a core layer investment of the sandwich radome; preparing an inner skin prefabricated body on the outer surface of a male die of an antenna housing forming die; preparing an outer skin preform on the outer surface of the core layer investment pattern; closing a male die, a female die and a core layer investment pattern of the radome forming die to obtain a closed radome forming die; transferring the antenna housing forming die after die assembly to a molding press for curing and coring to obtain a foam core layer cavity cured after coring; preparing a sandwich layer radome blank in a foam core layer cavity based on an in-situ foaming method; and performing finish machining on the interlayer radome blank to obtain the high-temperature-resistant foam A interlayer composite material radome.
In conclusion, the precise preparation method of the high-temperature-resistant foam A interlayer composite material radome solves the problems that the traditional foam core layer is difficult to process and the requirements on the processing precision of the inner skin and the outer skin are high, the precise core layer investment mold is used as the forming reference of the foam core layer, and the precise forming mold is used as the appearance reference of the sandwich radome, so that the problem that the high-temperature-resistant resin foam core layer is difficult to process is solved, the dimensional precision of each layer and the whole body of the sandwich radome is improved, and the broadband wave-transmitting capacity of the sandwich radome is effectively ensured.
While the present invention has been described in detail with reference to the preferred embodiments, it should be understood that the above description should not be taken as limiting the invention. Various modifications and alterations to this invention will become apparent to those skilled in the art upon reading the foregoing description. Accordingly, the scope of the invention should be determined from the following claims.

Claims (5)

1. A precise preparation method of a high-temperature-resistant foam A interlayer composite material radome is characterized by comprising the following steps:
step 1: preparing a core layer investment pattern by adopting a core layer forming die based on an injection molding process;
step 2: preparing an inner skin prefabricated body on the outer surface of a male die of an antenna housing forming die;
and step 3: preparing an outer skin preform on the outer surface of the core layer investment pattern;
and 4, step 4: closing a male die of the radome forming die, the inner skin prefabricated body, the core layer melting mold, the outer skin prefabricated body and a female die of the radome forming die to obtain the closed radome forming die;
and 5: curing and coring the molded antenna housing forming mold to obtain a foam core layer cavity;
step 6: preparing a sandwich layer radome blank in the foam core layer cavity based on an in-situ foaming method;
and 7: performing finish machining on the interlayer radome blank to obtain a high-temperature-resistant foam A interlayer composite material radome;
the preparation of the inner skin preform further comprises the following steps:
step 2.1: filling the inner skin fiber material on the outer surface of a male die of an antenna housing forming die;
step 2.2: coating the inner skin fiber material, and performing primary pre-compaction on the coated inner skin fiber material; step 2.3: removing the redundant glue solution on the inner skin fiber material subjected to the first pre-compaction for the first time to obtain the inner skin prefabricated body; the curing and coring further comprises the steps of:
step 5.1: pre-curing and heating the inner skin prefabricated body and the outer skin prefabricated body to obtain a pre-cured inner skin prefabricated body and a pre-cured outer skin prefabricated body;
step 5.2: curing and heating the pre-cured inner skin prefabricated body and the pre-cured outer skin prefabricated body to obtain an inner skin and an outer skin;
step 5.3: melting and heating the core layer melting mold of the intermediate sandwich layer of the inner skin and the outer skin to prepare the foam core layer cavity;
the pre-curing heating comprises the following steps:
step 5.1.1: heating the inner skin prefabricated body and the outer skin prefabricated body to raise the temperature, wherein the temperature of the inner skin prefabricated body and the temperature of the outer skin prefabricated body are raised to a first temperature of 140-160 ℃;
step 5.1.2: keeping the first temperature unchanged, and according to a compression molding process, pressurizing and exhausting the inner skin preform and the outer skin preform heated to the first temperature to obtain the pre-cured inner skin preform and the pre-cured outer skin preform;
the temperature of the inner skin and the outer skin is raised to a second temperature of 170-190 ℃;
the melting and heating comprises the following steps:
step 5.3.1: heating a core layer melting mold of the intermediate interlayer of the inner skin and the outer skin for the first time, wherein the temperature of the inner skin, the temperature of the outer skin and the temperature of the core layer melting mold are increased to a third temperature of 210-240 ℃;
step 5.3.2: keeping the third temperature unchanged, melting the core layer by an investment mold, and forming a core layer cavity by the intermediate interlayer;
step 5.3.3: heating the core layer cavity for the second time, wherein the temperature of the core layer cavity is raised to a fourth temperature of 300-320 ℃, and the heated core layer cavity is obtained;
step 5.3.4: and cooling the heated core layer cavity, and irrigating the cooled core layer cavity to prepare the foam core layer cavity.
2. The precise preparation method of the high temperature resistant foam a sandwich composite radome of claim 1, wherein the preparation of the outer skin preform further comprises the steps of:
step 3.1: filling an outer skin fiber material on the outer surface of the core layer investment pattern;
step 3.2: coating the outer skin fiber material, and performing secondary pre-compaction on the coated outer skin fiber material;
step 3.3: and removing the redundant glue solution on the outer skin fiber material subjected to the secondary pre-compaction for the second time to obtain the outer skin prefabricated body.
3. The precise manufacturing method of the high temperature resistant foam a sandwich composite radome of claim 1, wherein the mold closing further comprises the following steps:
step 4.1: slowly pressing the inner skin preform to the inner surface of the core layer investment mold, and ensuring that the inner skin preform is attached to the inner surface of the core layer investment mold;
step 4.2: slowly pressing the outer skin prefabricated part to the inner surface of a female die of an antenna housing forming die, and ensuring that the outer skin prefabricated part is attached to the inner surface of the female die;
step 4.3: and after the male die and the female die of the radome forming die are closed, the core layer investment pattern is positioned in the interlayer between the inner skin prefabricated body and the outer skin prefabricated body.
4. The precise process for preparing a high temperature resistant foam a sandwich composite radome of claim 1 wherein the preparing of the sandwich radome blank further comprises the steps of:
step 6.1: adding the proportioned mixed solution into the foam core layer cavity;
step 6.2: heating the foam core layer cavity added with the mixed solution based on an in-situ foaming method to prepare a foam core layer;
step 6.3: and preparing the sandwich radome blank according to the foam core layer.
5. The precise manufacturing method of the high temperature resistant foam a sandwich composite radome of claim 1, wherein the finishing further comprises the steps of:
step 7.1: releasing the interlayer radome blank from the radome forming die;
step 7.2: and (4) carrying out molding process auxiliary cutting processing on the removed interlayer radome blank to prepare the high-temperature-resistant foam A interlayer composite material radome.
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Publication number Priority date Publication date Assignee Title
CN113771116A (en) * 2021-09-18 2021-12-10 成都凯迪精工科技有限责任公司 Machining method of PMI foam filling part
CN114179396B (en) * 2021-12-17 2023-07-18 江西洪都航空工业集团有限责任公司 Forming method and die suitable for irregular U-shaped composite material foam sandwich structural member

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105881922A (en) * 2014-12-31 2016-08-24 航天神舟飞行器有限公司 Novel high-impacting-resistance type unmanned aerial vehicle airframe structure
CN105922703A (en) * 2016-04-21 2016-09-07 中国人民解放军国防科学技术大学 Preparation method for composite material antenna cover with thin-wall foam sandwich structure
CN106346683A (en) * 2016-12-01 2017-01-25 江西洪都航空工业集团有限责任公司 Manufacturing method of large-sized aviation composite material foam plastic sandwich structural member
CN109454895A (en) * 2018-10-22 2019-03-12 上海阿莱德实业股份有限公司 A kind of millimeter wave antenna cover quick molding method and the antenna house using this method production
CN109638445A (en) * 2018-10-26 2019-04-16 上海无线电设备研究所 A kind of high temperature resistant foam A interlayer composite material antenna house and preparation method thereof
KR20190068999A (en) * 2017-12-11 2019-06-19 한화큐셀앤드첨단소재 주식회사 Manufacturing method of sandwich panel having foam foam as core
WO2020028851A1 (en) * 2018-08-03 2020-02-06 Kymeta Corporation Composite stack-up for flat panel metamaterial antenna
CN110948908A (en) * 2019-12-06 2020-04-03 宁波曙翔新材料股份有限公司 Forming method of resin-based radome with single-layer sandwich foam prefabricated body

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110867659A (en) * 2019-12-06 2020-03-06 宁波曙翔新材料股份有限公司 Wave-transparent antenna housing
CN110948907A (en) * 2019-12-06 2020-04-03 宁波曙翔新材料股份有限公司 Method for forming resin-based radome with multilayer sandwich foam prefabricated bodies

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105881922A (en) * 2014-12-31 2016-08-24 航天神舟飞行器有限公司 Novel high-impacting-resistance type unmanned aerial vehicle airframe structure
CN105922703A (en) * 2016-04-21 2016-09-07 中国人民解放军国防科学技术大学 Preparation method for composite material antenna cover with thin-wall foam sandwich structure
CN106346683A (en) * 2016-12-01 2017-01-25 江西洪都航空工业集团有限责任公司 Manufacturing method of large-sized aviation composite material foam plastic sandwich structural member
KR20190068999A (en) * 2017-12-11 2019-06-19 한화큐셀앤드첨단소재 주식회사 Manufacturing method of sandwich panel having foam foam as core
WO2020028851A1 (en) * 2018-08-03 2020-02-06 Kymeta Corporation Composite stack-up for flat panel metamaterial antenna
CN109454895A (en) * 2018-10-22 2019-03-12 上海阿莱德实业股份有限公司 A kind of millimeter wave antenna cover quick molding method and the antenna house using this method production
CN109638445A (en) * 2018-10-26 2019-04-16 上海无线电设备研究所 A kind of high temperature resistant foam A interlayer composite material antenna house and preparation method thereof
CN110948908A (en) * 2019-12-06 2020-04-03 宁波曙翔新材料股份有限公司 Forming method of resin-based radome with single-layer sandwich foam prefabricated body

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