CN110524915A - A kind of socket forming frock and socket forming method - Google Patents
A kind of socket forming frock and socket forming method Download PDFInfo
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- CN110524915A CN110524915A CN201910837307.XA CN201910837307A CN110524915A CN 110524915 A CN110524915 A CN 110524915A CN 201910837307 A CN201910837307 A CN 201910837307A CN 110524915 A CN110524915 A CN 110524915A
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- heat
- cabin
- composite material
- material component
- insulation composite
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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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
-
- 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
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/78—Moulding material on one side only of the preformed part
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- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The present invention relates to a kind of socket forming frocks and socket forming method.Tooling includes circumferential former, the lower cover plate positioned at the upper cover plate of the circumferential former upper end and positioned at the circumferential former lower end；It is provided on the lower cover plate for the first positioning datum with cabin cooperation positioning；The circumferential direction former, the upper cover plate and the lower cover plate complement each other to form the cavity for accommodating heat-insulation composite material component and cabin.Method includes preparing heat-insulation composite material component, trial assembly, surface treatment and socket molding.Socket molding tool structure is simple and practical, forms by the socket that heat-insulation composite material component and cabin may be implemented in the tooling.Heat-insulation composite material component and cabin parallel production may be implemented in this method, be not in the problem of causing product not to be available integrally since heat-insulation composite material component quality is unqualified in formed in situ, it is also shorter than traditional piecemeal adhering method period, human cost is low.
Description
Technical field
The present invention relates to heat-insulation composite material technical fields, more particularly to one kind to be used for heat-insulation composite material component and cabin
Body is socketed molding socket forming frock and a kind of heat-insulation composite material component and cabin is socketed molding method.
Background technique
As the increase of cruising speed, the extension of cruise time, aircraft will be held hypersonic aircraft in atmosphere
It is acted on by harsher air and heat load, surface temperature is more than metal cabin power limit.In order to guarantee aircraft contour structures
Completely, internal component works normally, and needs using the outer solar heat protection heat-barrier material for having both temperature-resistance thermal-insulation and bearing function.Tradition
In mode, heat-barrier material component is prepared using piecemeal, then it is affixed on one by one outside aircraft cabin, each component needs successively
Alignment or individually positioning, higher for the machined surface profile required precision of component and cabin, assembly process is complicated, difficulty is big, the period
It is long, and the investment of the numerous molds of quantity and tooling is needed, production efficiency is not high, and cost is difficult to decrease.
In order to solve the above-mentioned technical problem, inventor has developed the molding die and benefit of a kind of formed in situ in cabin
With the forming method of mold formed in situ heat-barrier material component in bay section, and by this developmental achievement application patent of invention, Shen
Please publication No. be CN109572003A.Formed in situ is led to by the way that fiber preform to be set with and be bonded on the outer wall of bay section
It crosses injection sol precursor and enables heat-barrier material component integrated molding in bay section, compared with traditional assembly method,
The property retention of product material is consistent, and typical product development cycle shortens.But due to above-mentioned formed in situ method be first will be fine
Then dimension precast body is put into mold again injecting glue and is combined into fibrous thermal composite element, injection process difficulty increases, for
Cabin state has certain restrictive condition, and the drawbacks of higher integrated molding method also displays at this time: heat-insulated compound
Material members are off quality to will lead to the failure of product integrated artistic, is not available, after needing to remove component from bay section
It just can proceed with compound.This limits the application of formed in situ technique to a certain extent.
In view of this, the present invention is specifically proposed.
Summary of the invention
In view of the deficiencies in the prior art or insufficient, the present invention provides one kind to be used for heat-insulation composite material component
Molding socket forming frock and a kind of heat-insulation composite material component are socketed with cabin and cabin is socketed molding method.
In order to solve the above-mentioned technical problems, the present invention provides following technical solutions:
One kind for heat-insulation composite material component and cabin to be socketed molding socket forming frock, including circumferential former,
Lower cover plate positioned at the upper cover plate of the circumferential former upper end and positioned at the circumferential former lower end；
It is provided on the lower cover plate for the first positioning datum with cabin cooperation positioning；
The circumferential direction former, the upper cover plate and the lower cover plate have been complemented each other to form for accommodating heat-insulation composite material
The cavity of component and cabin.
Preferably, the first positioning datum includes dowel hole or positioning spigot.
Preferably, it is provided on the lower cover plate for the second positioning datum with the circumferential former cooperation positioning；With
It is provided on the upper cover plate for the third positioning datum with the circumferential former cooperation positioning.
Preferably, second positioning datum includes dowel hole or positioning spigot；With
The third positioning datum includes dowel hole or positioning spigot.
A kind of heat-insulation composite material component and cabin are socketed molding method, using the socket molding provided by the invention
Tooling carries out, and described method includes following steps:
(1) the step of preparing heat-insulation composite material component, the heat-insulation composite material component, which has to cooperate with cabin, to be positioned
The first technological datum and with it is described socket forming frock in circumferential former cooperation positioning the second technological datum；
(2) the step of trial assembly: heat-insulation composite material component being set on cabin for molding, utilizes the first technique base
Quasi- alignment, positioning, adjustment；
(3) the step of being surface-treated: the outer surface of cabin for molding and the inner mold face of heat-insulation composite material component are carried out
Surface treatment makes to be compounded with the boundary material with cementability on the outer surface and the inner mold face；With
(4) the step of socket molding: the lower cover plate in preforming cabin and socket forming frock being cooperated and is positioned, and then will
Heat-insulation composite material component is set in the outside of preforming cabin, is determined during suit using first technological datum
Position forms heat-insulation composite material component/cabin preformed member, is socketed circumferential former in the outside of the preformed member, set is taken over
Positioned in journey using second technological datum, then in place by circumferential former and upper cover plate and lower cover plate assembly, finally plus
It is cured to solidify boundary material and realize the compound of heat-insulation composite material component and cabin.
Preferably, the bonding agent or be compounded in institute that the boundary material is brushing on the outer surface and the inner mold face
State the resin glue film on outer surface and the inner mold face.
Preferably, the first technological datum include can with cabin end face or the axial end face that be aligned of recess or boss, can be with cabin
The body plane of symmetry or the circumferential plane of symmetry or other surface-type features of feature alignment.
Preferably, the second technological datum includes the type face location feature that can be bonded with the circumferential former matching and/or determines
Position reference characteristic.
Preferably, the heat-insulation composite material component is combined using fiber preform impregnating resin glue.
Preferably, the preparation method of the heat-insulation composite material component includes: to mold fiber preform in molding die
In, pressurization injection resin precursor glue, by solidifying, drying, obtains heat-insulation composite material component after compound dipping is abundant.
Beneficial effect
Above-mentioned technical proposal of the invention has the advantages that
Socket molding tool structure provided by the invention is simple and practical, and heat-insulation composite material structure may be implemented by the tooling
The socket of part and cabin forms.
This method provided by the invention first prepares heat-insulation composite material component, then by heat-insulation composite material component with
Cabin socket, then be bonded compound by socket forming frock, this method is not in formed in situ because of heat-insulated composite wood
Material component quality is unqualified and leads to the underproof problem of integrated artistic, also, manpower shorter than traditional piecemeal adhering method period
It is at low cost.
This method provided by the invention is novel, is a kind of new, practicable compound heat-insulation material in cabin
The method of material.
This method provided by the invention is simple, easy to operate, environmental pollution is small.
This method provided by the invention can be used for forming the bay section heat-barrier material of rule and non-regular shape, in aviation
It is with a wide range of applications in the environment of aerospace industry.
Detailed description of the invention
Fig. 1 is the structural schematic diagram for being socketed forming frock.
In figure: 1: circumferential former；2: upper cover plate；3: lower cover plate；4: heat-insulation composite material component；5: cabin.
Specific embodiment
To make the object, technical solutions and advantages of the present invention clearer, below in conjunction with the embodiment of the present invention, to this hair
Bright technical solution is clearly and completely described.Obviously, described embodiment is a part of the embodiments of the present invention, and
The embodiment being not all of.Based on the embodiments of the present invention, those of ordinary skill in the art are not making creative work
Under the premise of every other embodiment obtained, shall fall within the protection scope of the present invention.
The present invention provides a kind of for heat-insulation composite material component 4 and cabin 5 to be socketed molding set in first aspect
Forming frock is connect, with reference to Fig. 1, the socket forming frock includes circumferential former 1, the upper cover positioned at 1 upper end of the circumferential former
Plate 2 and lower cover plate 3 positioned at circumferential 1 lower end of former；
It is provided on the lower cover plate 3 for the first positioning datum with the cooperation positioning of cabin 5；
The circumferential direction former 1, the upper cover plate 2 and the lower cover plate 3 have complemented each other to form heat-insulated compound for accommodating
The cavity of material members 4 and cabin 5.
Socket molding tool structure provided by the invention is simple and practical, and heat-insulation composite material structure may be implemented by the tooling
The socket of part 4 and cabin 5 forms.
In some preferred embodiments, first positioning datum includes dowel hole or positioning spigot.
In some preferred embodiments, it is provided on the lower cover plate 3 for being positioned with the circumferential cooperation of former 1
The second positioning datum；It is provided on the upper cover plate 2 for the third positioning datum with the circumferential cooperation of former 1 positioning.
It is highly preferred that second positioning datum includes dowel hole or positioning spigot；The third positioning datum includes dowel hole
Or positioning spigot.
More fully, socket forming frock provided by the invention includes circumferential former 1, is located on the circumferential former 1
The upper cover plate 2 at end and lower cover plate 3 positioned at circumferential 1 lower end of former；It is provided on the lower cover plate 3 for matching with cabin 5
The first positioning datum of positioning is closed, first positioning datum includes dowel hole or positioning spigot；The circumferential direction former 1, institute
It states upper cover plate 2 and the lower cover plate 3 complements each other to form cavity for accommodating heat-insulation composite material component 4 and cabin 5；Institute
State the second positioning datum being provided on lower cover plate 3 for the circumferential cooperation of former 1 positioning；It is arranged on the upper cover plate 2
Have for the third positioning datum with the circumferential cooperation of former 1 positioning；Second positioning datum includes dowel hole or determines
Position seam allowance；The third positioning datum includes dowel hole or positioning spigot.
The present invention provides a kind of heat-insulation composite material component in second aspect and cabin is socketed molding method, the side
Method includes the steps that the step of the step of the step of preparing heat-insulation composite material component, trial assembly, surface treatment and socket molding.Tool
Body, which comprises
(1) the step of preparing heat-insulation composite material component, the heat-insulation composite material component, which has to cooperate with cabin, to be positioned
The first technological datum and with it is described socket forming frock in circumferential former cooperation positioning the second technological datum；
(2) the step of trial assembly: heat-insulation composite material component being set on cabin for molding, utilizes the first technique base
Quasi- alignment, positioning, adjustment；
(3) the step of being surface-treated: the outer surface of cabin for molding and the inner mold face of heat-insulation composite material component are carried out
Surface treatment makes to be compounded with the boundary material with cementability on the outer surface and the inner mold face；With
(4) the step of socket molding: the lower cover plate in preforming cabin and socket forming frock being cooperated and is positioned, and then will
Heat-insulation composite material component is set in the outside of preforming cabin, is determined during suit using first technological datum
Position forms heat-insulation composite material component/cabin preformed member, is socketed circumferential former in the outside of the preformed member, set is taken over
Positioned in journey using second technological datum, then in place by circumferential former and upper cover plate and lower cover plate assembly, finally plus
It is cured to solidify boundary material and realize the compound of heat-insulation composite material component and cabin.
This method provided by the invention first prepares heat-insulation composite material component, then by heat-insulation composite material component with
Cabin socket, then be bonded compound by socket forming frock, this method is not in formed in situ because of heat-insulated composite wood
Material component quality is unqualified and leads to the underproof problem of integrated artistic, also, manpower shorter than traditional piecemeal adhering method period
It is at low cost.
Method provided by the invention is novel, is a kind of new, practicable composite heat-insulated material in cabin
Method.
This method provided by the invention is simple, easy to operate, environmental pollution is small.
This method provided by the invention can be used for forming the bay section heat-barrier material of rule and non-regular shape, in aviation
It is with a wide range of applications in the environment of aerospace industry.
In some preferred embodiments, the boundary material is to brush on the outer surface and the inner mold face
Bonding agent or the resin glue film being compounded on the outer surface and the inner mold face.It should be noted that the bonding agent and institute
Existing bonding agent commonly used in the art and resin glue film can be selected by stating resin glue film.
The precision positioned between heat-insulation composite material component and cabin can be improved by the first technological datum, some excellent
In the embodiment of choosing, first technological datum includes that the first technological datum includes the axis that can be aligned with cabin end face or recess
To end face or boss, the circumferential plane of symmetry or other surface-type features that can be aligned with the cabin plane of symmetry or feature.
In some preferred embodiments, the second technological datum includes that can match the type face being bonded with the circumferential former
Location feature and/or positioning datum feature.
In some preferred embodiments, the heat-insulation composite material component uses fiber preform impregnating resin glue
It is combined.The heat-barrier material is compound can also to select the existing thermally protective materials of the prior art, heat-insulated heat insulation material etc..
Such as, the preparation method of the heat-insulation composite material component includes: the pressurization injection tree by fiber preform molding in molding die
Rouge presoma glue, by solidifying, drying, obtains heat-insulation composite material component after compound dipping is abundant.
More fully, socket forming method provided by the invention includes:
(1) the step of preparing heat-insulation composite material component, the heat-insulation composite material component, which has to cooperate with cabin, to be positioned
The first technological datum and with it is described socket forming frock in circumferential former cooperation positioning the second technological datum；It is described every
Hot composite element is combined using fiber preform impregnating resin glue.Preferably, the heat-insulation composite material component
Preparation method include: to mold fiber preform in molding die, pressurization injection resin precursor glue, compound dipping fills
After point, by solidifying, drying, heat-insulation composite material component is obtained.
(2) the step of trial assembly: heat-insulation composite material component being set on cabin for molding, utilizes the first technique base
Quasi- alignment, positioning, adjustment.First technological datum include can with cabin end face or the axial end face that be aligned of recess or boss,
The circumferential plane of symmetry or other surface-type features that can be aligned with the cabin plane of symmetry or feature.
(3) the step of being surface-treated: the outer surface of cabin for molding and the inner mold face of heat-insulation composite material component are carried out
Surface treatment makes to be compounded with the boundary material with cementability on the outer surface and the inner mold face.The boundary material is to apply
Brush is in the bonding agent on the outer surface and the inner mold face or the resin glue being compounded on the outer surface and the inner mold face
Film.
(4) the step of socket molding: the lower cover plate in preforming cabin and socket forming frock being cooperated and is positioned, and then will
Heat-insulation composite material component is set in the outside of preforming cabin, is positioned during suit using the location feature, shape
At heat-insulation composite material component/cabin preformed member, circumferential former, benefit during socket are socketed in the outside of the preformed member
It is positioned with second technological datum, second technological datum includes that can match the type face being bonded with the circumferential former
Location feature and/or positioning datum feature, then circumferential former and upper cover plate and lower cover plate are assembled in place, last cure under pressure makes
Boundary material solidifies and realizes the compound of heat-insulation composite material component and cabin.
It is the embodiment that the present invention enumerates below.
It illustrates, the orientation or positional relationship of the instructions such as term " on ", "lower", "inner" is based on the figure
Orientation or positional relationship is merely for convenience of description of the present invention and simplification of the description, rather than the element of indication or suggestion meaning must
There must be specific orientation, be constructed and operated in a specific orientation, therefore be not considered as limiting the invention.
Embodiment 1
It present embodiments provides a kind of for heat-insulation composite material component and cabin to be socketed molding socket forming frock.
The socket forming frock includes circumferential former, positioned at the upper cover plate of the circumferential former upper end and positioned at the ring
To the lower cover plate of former lower end.It is provided on the lower cover plate for the dowel hole with cabin cooperation positioning.The lower cover plate
On be provided with for the dowel hole with the circumferential former cooperation positioning.Be provided on the upper cover plate for the circumferential direction
The dowel hole of former cooperation positioning.The circumferential direction former, the upper cover plate and the lower cover plate have been complemented each other to form and have been used for
Accommodate the cavity of heat-insulation composite material component and cabin.
Embodiment 2
It present embodiments provides a kind of for heat-insulation composite material component and cabin to be socketed molding socket forming frock.
The socket forming frock includes circumferential former, positioned at the upper cover plate of the circumferential former upper end and positioned at the ring
To the lower cover plate of former lower end.It is provided on the lower cover plate for the positioning spigot with cabin cooperation positioning.The lower cover plate
On be provided with for the positioning spigot with the circumferential former cooperation positioning.Be provided on the upper cover plate for the circumferential direction
The positioning spigot of former cooperation positioning.The circumferential direction former, the upper cover plate and the lower cover plate have been complemented each other to form and have been used for
Accommodate the cavity of heat-insulation composite material component and cabin.
Embodiment 3
It present embodiments provides a kind of heat-insulation composite material component and cabin is socketed molding method.
This method is carried out using the socket forming frock that embodiment 1 provides.
This method specifically comprises the following steps:
(1) the step of preparing heat-insulation composite material component: the heat-insulation composite material component is impregnated using fiber preform
Resin adhesive liquid is combined, and specifically includes: by fiber preform molding in molding die, pressurization injection resin precursor glue
Liquid, by solidifying, drying, obtains heat-insulation composite material component after compound dipping is abundant.Wherein, heat-insulated used in the present embodiment
Composite element is negative with the first technological datum with cabin cooperation positioning and with the circumferential direction in the socket forming frock
Second technological datum of mould cooperation positioning, the first technological datum include the axial end face or convex that can be aligned with cabin end face or recess
Platform, the circumferential plane of symmetry that can be aligned with the cabin plane of symmetry or feature, the second technological datum include that can match with the circumferential former
The type face location feature of fitting.
(2) the step of trial assembly: heat-insulation composite material component being set on cabin for molding, utilizes the first technique base
Quasi- alignment, positioning, adjustment.
(3) the step of being surface-treated: the outer surface of cabin for molding and the inner mold face of heat-insulation composite material component are carried out
Surface treatment makes to be compounded with the boundary material with cementability on the outer surface and the inner mold face.The boundary material is tree
Rouge glue film.
(4) the step of socket molding: the lower cover plate in preforming cabin and socket forming frock being cooperated and is positioned, and then will
Heat-insulation composite material component is set in the outside of preforming cabin, is determined during suit using first technological datum
Position forms heat-insulation composite material component/cabin preformed member, is socketed circumferential former in the outside of the preformed member, set is taken over
Positioned in journey using second technological datum, then in place by circumferential former and upper cover plate and lower cover plate assembly, finally plus
It is cured to solidify boundary material and realize the compound of heat-insulation composite material component and cabin.Cabin and heat-insulation composite material component
Bonding securely, is not fallen off.
Embodiment 4
It present embodiments provides a kind of heat-insulation composite material component and cabin is socketed molding method.
This method is carried out using the socket forming frock that embodiment 2 provides.
This method specifically comprises the following steps:
(1) the step of preparing heat-insulation composite material component: the heat-insulation composite material component is impregnated using fiber preform
Resin adhesive liquid is combined, and specifically includes: by fiber preform molding in molding die, pressurization injection resin precursor glue
Liquid, by solidifying, drying, obtains heat-insulation composite material component after compound dipping is abundant.Wherein, heat-insulated used in the present embodiment
Composite element is negative with the first technological datum with cabin cooperation positioning and with the circumferential direction in the socket forming frock
Second technological datum of mould cooperation positioning, the first technological datum include the axial end face or convex that can be aligned with cabin end face or recess
Platform, the circumferential plane of symmetry that can be aligned with the cabin plane of symmetry or feature, the second technological datum include that can match with the circumferential former
The type face location feature of fitting.
(2) the step of trial assembly: heat-insulation composite material component being set on cabin for molding, utilizes the first technique base
Quasi- alignment, positioning, adjustment.
(3) the step of being surface-treated: the outer surface of cabin for molding and the inner mold face of heat-insulation composite material component are carried out
Surface treatment makes to be compounded with the boundary material with cementability on the outer surface and the inner mold face.The boundary material is viscous
Connect agent.
(4) the step of socket molding: the lower cover plate in preforming cabin and socket forming frock being cooperated and is positioned, and then will
Heat-insulation composite material component is set in the outside of preforming cabin, is determined during suit using first technological datum
Position forms heat-insulation composite material component/cabin preformed member, is socketed circumferential former in the outside of the preformed member, set is taken over
Positioned in journey using second technological datum, then in place by circumferential former and upper cover plate and lower cover plate assembly, finally plus
It is cured to solidify boundary material and realize the compound of heat-insulation composite material component and cabin.Cabin and heat-insulation composite material component
Bonding securely, is not fallen off.
Finally, it should be noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；Although
Present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that: it still may be used
To modify the technical solutions described in the foregoing embodiments or equivalent replacement of some of the technical features；
And these are modified or replaceed, technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution spirit and
Range.
Claims (10)
1. one kind is for being socketed molding socket forming frock for heat-insulation composite material component and cabin, which is characterized in that including
Circumferential former, the lower cover plate positioned at the upper cover plate of the circumferential former upper end and positioned at the circumferential former lower end；
It is provided on the lower cover plate for the first positioning datum with cabin cooperation positioning；
The circumferential direction former, the upper cover plate and the lower cover plate have been complemented each other to form for accommodating heat-insulation composite material component
With the cavity of cabin.
2. socket forming frock according to claim 1, which is characterized in that the first positioning datum includes dowel hole or determines
Position seam allowance.
3. socket forming frock according to claim 1, which is characterized in that be provided on the lower cover plate for it is described
Second positioning datum of circumferential former cooperation positioning；With
It is provided on the upper cover plate for the third positioning datum with the circumferential former cooperation positioning.
4. socket forming frock according to claim 3, which is characterized in that second positioning datum includes dowel hole
Or positioning spigot；With
The third positioning datum includes dowel hole or positioning spigot.
5. a kind of heat-insulation composite material component and cabin are socketed molding method, which is characterized in that appointed using Claims 1-4
One socket forming frock carries out, and described method includes following steps:
(1) the step of preparing heat-insulation composite material component, the heat-insulation composite material component have the with cabin cooperation positioning
One technological datum and the second technological datum positioned with the circumferential former cooperation in the socket forming frock；
(2) the step of trial assembly: heat-insulation composite material component being set on cabin for molding, utilizes the first technological datum pair
Together, it positions, adjust；
(3) outer surface of cabin for molding and the inner mold face of heat-insulation composite material component the step of being surface-treated: are subjected to surface
Processing makes to be compounded with the boundary material with cementability on the outer surface and the inner mold face；With
(4) the step of socket molding: the lower cover plate in preforming cabin and socket forming frock being cooperated and is positioned, then will be heat-insulated
Composite element is set in the outside of preforming cabin, is positioned during suit using first technological datum, shape
At heat-insulation composite material component/cabin preformed member, circumferential former, benefit during socket are socketed in the outside of the preformed member
It is positioned, then circumferential former and upper cover plate and lower cover plate is assembled in place, last cure under pressure with second technological datum
Solidify boundary material and realizes the compound of heat-insulation composite material component and cabin.
6. according to the method described in claim 5, it is characterized in that, the boundary material is to brush in the outer surface and described
Bonding agent on inner mold face or the resin glue film being compounded on the outer surface and the inner mold face.
7. according to the method described in claim 6, it is characterized in that, first technological datum includes can be with cabin end face or recessed
The axial end face or boss of sunken alignment, the circumferential plane of symmetry or other surface-type features that can be aligned with the cabin plane of symmetry or feature.
8. according to the method described in claim 5, it is characterized in that, second technological datum includes can be with the circumferential former
Match the type face location feature and/or positioning datum feature of fitting.
9. according to the method described in claim 5, it is characterized in that, the heat-insulation composite material component is soaked using fiber preform
Stain resin adhesive liquid is combined.
10. according to the method described in claim 5, it is characterized in that, the preparation method of the heat-insulation composite material component includes:
Fiber preform is molded in molding die, pressurization injection resin precursor glue, after compound dipping is abundant, by solidifying,
It is dry, obtain heat-insulation composite material component.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910837307.XA CN110524915A (en) | 2019-09-05 | 2019-09-05 | A kind of socket forming frock and socket forming method |
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| CN201910837307.XA CN110524915A (en) | 2019-09-05 | 2019-09-05 | A kind of socket forming frock and socket forming method |
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| CN110524915A true CN110524915A (en) | 2019-12-03 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112318898A (en) * | 2020-09-30 | 2021-02-05 | 航天特种材料及工艺技术研究所 | Thermal protection cabin section, RTM (resin transfer molding) method and female die thereof |
| CN112483521A (en) * | 2020-11-17 | 2021-03-12 | 航天特种材料及工艺技术研究所 | Tool and method for sleeving rigid thermal protection layer on unclosed equal-diameter revolving body cabin section |
| CN113021226A (en) * | 2021-03-03 | 2021-06-25 | 航天特种材料及工艺技术研究所 | Sleeving tool and sleeving method for upper closed type outer heat-proof layer of cabin section |
| CN115159954A (en) * | 2022-07-15 | 2022-10-11 | 航天特种材料及工艺技术研究所 | Aerogel thermal insulation layer and preparation method thereof |
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| CN113021226A (en) * | 2021-03-03 | 2021-06-25 | 航天特种材料及工艺技术研究所 | Sleeving tool and sleeving method for upper closed type outer heat-proof layer of cabin section |
| CN115159954A (en) * | 2022-07-15 | 2022-10-11 | 航天特种材料及工艺技术研究所 | Aerogel thermal insulation layer and preparation method thereof |
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