CN115958818A - Embedded metal beam honeycomb sandwich structure, forming method and fairing - Google Patents
Embedded metal beam honeycomb sandwich structure, forming method and fairing Download PDFInfo
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- CN115958818A CN115958818A CN202211580577.5A CN202211580577A CN115958818A CN 115958818 A CN115958818 A CN 115958818A CN 202211580577 A CN202211580577 A CN 202211580577A CN 115958818 A CN115958818 A CN 115958818A
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Abstract
The invention provides a pre-buried metal beam honeycomb sandwich structure, a forming method and a fairing, which comprise the following steps: the honeycomb structure comprises a metal beam, a lower skin, an upper skin and a honeycomb; the metal beam and the honeycomb are installed between the upper skin and the lower skin, and the metal beam is arranged on the periphery of the honeycomb. The application realizes the integral co-curing of the materials with large differential expansion coefficients, avoids the repeated use and production of large-scale forming dies, greatly improves the production takt and reduces the manufacturing cost of the dies.
Description
Technical Field
The invention relates to the field of composite material sandwich structure forming methods, in particular to a pre-buried metal beam honeycomb sandwich structure, a forming method and a fairing.
Background
During the storage, transportation and launching processes of the carrier rocket, the fairing is required to be adopted to protect other effective loads such as satellites and the like in the carrier rocket, so that the carrier rocket is prevented from being influenced by harmful factors such as severe environment, pneumatic heating and resonance, higher requirements are provided for the wave transmission performance of the fairing along with the change of communication frequency band and frequency, and the requirements for the overall strength, rigidity and weight reduction of components are higher. Therefore, rocket fairings generally adopt a large enveloping size, an interlayer structure with a communication window and a pre-embedded large-size metal beam so as to meet the overall requirements.
Through a search of patent documents and non-patent documents, patent documents relating to sandwich structures are, for example: chinese patent publication No. CN108045002a, publication No. 2018, 5 and 18, and entitled "a honeycomb sandwich structure and a method for manufacturing the same" discloses a honeycomb sandwich structure and a method for manufacturing the same. The honeycomb sandwich structure described in this patent requires that a layer of adhesive and a layer of prepreg are laid on the upper and lower surfaces of a honeycomb core material, respectively, and then the prepreg is pretreated, and the prepreg in other sequences and angles is laid after the pretreatment is completed. In the honeycomb sandwich structure and the preparation method thereof, parts such as large-scale metal beams do not exist in advance, the forming method is divided into two periods of pretreatment and post-curing, and the forming period is long, so that the control of the production cost is not facilitated.
Another example is: chinese patent publication No. CN108372693A, publication No. 2018, 8, 7 and named "an oversized single-curved reflecting surface composite honeycomb sandwich structure and a forming method thereof" discloses an oversized single-curved reflecting surface composite honeycomb sandwich structure and a preparation method thereof. This patent compound honeycomb sandwich structure of single curved reflection face of oversize constitute by three-layer duralumin plate, two-layer aluminum honeycomb core and the section bar skeleton that is used for connecting and supports, this patent the material is the aluminum alloy, when solidification shaping, the thermal expansion deformation of each partial material is the same, and aluminum alloy material wave-transparent communication function is poor simultaneously. The honeycomb sandwich structure forming method described in this patent is not suitable for forming sandwich structures containing materials with large differential expansion coefficients (such as metal and paper honeycombs) at the same time.
Based on the above, a forming method of a pre-embedded large metal beam honeycomb sandwich structure is expected, and the method can meet the requirement of integral co-curing of materials with large differential expansion coefficients.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a pre-buried metal beam honeycomb sandwich structure, a forming method and a fairing.
According to the invention, the embedded metal beam honeycomb sandwich structure for the rocket fairing comprises the following components: the honeycomb structure comprises a metal beam, a lower skin, an upper skin and a honeycomb;
the metal beam and the honeycomb are installed between the upper skin and the lower skin, and the metal beam is arranged on the periphery of the honeycomb.
Preferably, the metal beam includes: frame girders and truss girders;
the lower skin and the upper skin are both arranged into arc-shaped surface structures, and arc lines extend in a straight line in the direction perpendicular to the surface of the arc lines;
the U-shaped frame beam is arranged at the arc ends at the two ends of the lower skin and the upper skin and is matched with the arc ends of the lower skin and the upper skin in shape;
the stringers, which are linear, are installed at linear sides of both sides of the lower and upper skins.
Preferably, a method for forming the embedded metal beam honeycomb sandwich structure comprises the following steps:
s1, completing gradual change layering of the lower skin according to a set sequence and angle, and integrally paving an adhesive;
s2, respectively installing the truss girder and the frame girder to the peripheral boundary position of the lower skin, wherein one side surface of the truss girder and one side surface of the frame girder are in contact with the surface of the lower skin, and the gap of the intersection position of the truss girder and the frame girder is 1.5-3mm;
s3, laying the honeycomb in a range enclosed by the truss girder and the frame girder, and laying an adhesive on the honeycomb;
s4, after finishing the gradual-change layering of the upper skin according to a set sequence and a set angle, preparing a vacuum bag, and performing one-time curing molding through an autoclave and a curing oven;
and S5, obtaining the pre-buried metal beam honeycomb sandwich structure after hot demolding.
Preferably, the lower skin and the upper skin are made of glass fiber reinforced resin matrix composite materials, and the thickness of the lower skin and the upper skin is 1-3mm.
Preferably, the length of the truss girder is more than 3m, the width of the truss girder is 20-50mm, the arc circumference of the frame girder is more than 5m, and the width of the frame girder is 20-50mm.
Preferably, the honeycomb is aramid paper honeycomb, the thickness of the honeycomb paper is 0.05-0.08mm, the thickness of the honeycomb is 20-40mm, and the density is 48-76kg/m 3 。
Preferably, in step S4, the curing molding includes an initial heating and pressing stage, a stepped and segmented heating and pressing stage, and a heat-preserving and pressure-maintaining stage.
Preferably, in the initial temperature rise and pressure rise stage, the temperature rise temperature is 30-50 ℃, in the initial temperature rise stage, the pressure in the autoclave is increased, and the auxiliary pressure in the vacuum bag is removed;
in the step-type sectional heating and pressing stage, the temperature is firstly increased to 110-120 ℃, the pressure is 0.1MPa, and then the pressure is increased to 0.5MPa in a sectional manner in the process of increasing the temperature to 120-150 ℃;
and in the heat preservation and pressure maintaining stage, keeping the temperature for 1h, then continuously heating to 170-180 ℃, keeping the pressure at 0.5MPa in the process, keeping the temperature for 4-6h, then cooling to 120 ℃, and carrying out thermal demolding.
Compared with the prior art, the invention has the following beneficial effects:
1. the method realizes the integral co-curing of the materials with large differential expansion coefficients, avoids the repeated use and production of large-scale forming dies, greatly improves the production takt and reduces the manufacturing cost of the dies;
2. according to the scheme, the deformation risk of the product caused by multiple times of curing of a large-size and multi-part product is reduced by adopting a multi-stage heating, grading, pressing and heat preservation scheme;
3. the sandwich structure not only meets the requirements of the integral strength and rigidity of the rocket fairing, but also realizes the functions of omnidirectional and full wave transmission.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic view of an overall structure of a pre-embedded metal beam honeycomb sandwich structure;
FIG. 2 is a schematic view of the relative positions of the stringers, honeycomb and skin;
FIG. 3 is a schematic view of the skin covering the stringer surface location;
FIG. 4 is a schematic diagram showing the relative positions of the frame beam, the honeycomb and the skin
FIG. 5 is a schematic view of the skin monolith and interpenetrated plies;
shown in the figure:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
Example 1
As shown in fig. 1 to 5, the present embodiment includes: the frame beam comprises a frame beam 1, a truss beam 2, a lower skin 3, an upper skin 4 and a honeycomb 5; and a frame beam 1, a truss beam 2 and a honeycomb 5 are arranged between the upper skin 4 and the lower skin 3, and the frame beam 1 and the truss beam 2 are arranged at the peripheral side position of the honeycomb 5. Lower covering 3 and last covering 4 all set up to the arc face structure that the arc line extends towards the direction straight line of perpendicular to arc line place face, and the frame roof beam 1 of U type is installed under the arc end of covering 3 and 4 both ends of last covering and with the shape looks adaptation of covering 3 and 4 arc ends of last covering down, and the straight line side of covering 3 and 4 both sides of last covering is installed under to linear type longeron 2.
The length of the truss girder 2 is more than 3m, the width is 20-50mm, the arc circumference of the frame girder 1 is more than 5m, and the width is 20-50mm. The lower skin 3 and the upper skin 4 are made of glass fiber reinforced resin matrix composite materials, and the thickness is 1-3mm. The honeycomb 5 is aramid fiber paper honeycomb, the thickness of the honeycomb paper is 0.05-0.08mm, the thickness of the honeycomb 5 is 20-40mm, and the density is 48-76kg/m 3 。
The embodiment also provides a forming method of the embedded metal beam honeycomb sandwich structure, which comprises the following steps:
s1, finishing gradual change layering of a lower skin 3 according to a set sequence and an angle, and integrally laying an adhesive;
s2, respectively installing the truss girder 2 and the frame girder 1 to the peripheral boundary position of the lower skin 3, wherein one side surfaces of the truss girder 2 and the frame girder 1 are in contact with the surface of the lower skin 3, and the gap of the intersection position of the truss girder 2 and the frame girder 1 is 1.5-3mm;
s3, laying a honeycomb 5 in a range enclosed by the truss beam 2 and the frame beam 1, and laying an adhesive on the honeycomb 5;
s4, after finishing the gradual change layering of the upper skin 4 according to a set sequence and a set angle, preparing a vacuum bag, and performing one-time curing molding through an autoclave and a curing oven;
the solidification molding comprises an initial heating and pressing stage, a stepped sectional heating and pressing stage and a heat preservation and pressure maintaining stage. In the initial temperature rise and pressure rise stage, the temperature rise temperature is 30-50 ℃, the pressure in the autoclave is increased in the initial temperature rise stage, and the auxiliary pressure in the vacuum bag is removed; in the step-type sectional heating and pressing stage, the temperature is firstly increased to 110-120 ℃, the pressure is 0.1MPa, and then the pressure is increased to 0.5MPa in a sectional manner in the process of increasing the temperature to 120-150 ℃; in the heat preservation and pressure maintaining stage, the temperature is kept for 1h, then the temperature is continuously raised to 170-180 ℃, the pressure is kept at 0.5MPa in the process, the temperature is kept for 4-6h, then the temperature is reduced and cooled to 120 ℃, and the thermal demolding is carried out.
And S5, obtaining the pre-buried metal beam honeycomb sandwich structure after hot demolding.
Example 2
Example 2 is a preferred example of example 1.
As shown in fig. 1 to 5, the honeycomb sandwich structure is an integrally formed member including: the frame beam 1, the trussed beam 2, the honeycomb 5, the upper skin 4 and the lower skin 3 are pre-embedded, the frame beam 1, the trussed beam 2, the honeycomb 5, the upper skin 4 and the lower skin 3 are cured simultaneously, the trussed beam 2 is linear, the frame beam 1 is U-shaped, the honeycomb 5 is a variable-cross-section variable-thickness honeycomb, and the upper skin 4 and the lower skin 3 are made of glass fiber reinforced resin matrix composite materials.
The length of the truss beam 2 is more than 3m, the width is 20-50mm, the arc-direction perimeter of the frame beam 1 is more than 5m, and the width is 20-50mm; the honeycomb 5 is aramid fiber paper honeycomb, the thickness of the honeycomb paper is 0.05-0.08mm, the thickness of the honeycomb 5 is 20-40mm, and the density is 48-76kg/m 3 (ii) a The upper skin 4 and the lower skin 3 are made of fiber reinforced resin matrix composite materials, have the thickness of 1-3mm, and are layered according to symmetrical (or quasi-symmetrical) dip angles.
The frame beam 1 and the trussed beams 2 are distributed around the honeycomb 5, the honeycomb 5 is of a variable-section and variable-thickness structure, and the upper skin 4 and the lower skin 3 completely cover the upper surface and the lower surface of the frame beam 1, the trussed beams 2 and the honeycomb 5 respectively.
The forming method of the embedded metal beam honeycomb sandwich structure comprises the following steps:
the method comprises the following steps: the lower skin 3 finishes gradual change layering according to a set sequence and an angle, and an adhesive is integrally paved;
step two: respectively installing the frame beam 1 and the truss beam 2 to the boundary positions of four positions of the lower skin 3 completed in the step one, contacting the lower surfaces of the frame beam 1 and the truss beam 2 with the surface of the lower skin 3, and controlling the gap of the intersection position of the frame beam 1 and the truss beam 2 to be 1.5-3mm;
step three: laying honeycombs 5 in sequence in the range of the concave shape surrounded by the frame beam 1 and the truss beam 2, and laying an adhesive on the upper surfaces of the honeycombs 5;
step four: and on the basis of the third step, finishing gradual change paving of the upper skin 4 according to a specific sequence and an angle, preparing a vacuum bag, and performing one-step forming on equipment such as an autoclave, a curing oven and the like, wherein the one-step forming comprises an initial heating and pressing stage, a stepped sectional heating and pressing stage and a heat and pressure preservation stage.
Step five: and (4) after hot demolding, obtaining the pre-embedded large metal beam honeycomb sandwich structure.
In the initial temperature rise and pressure rise stage, the temperature rise temperature is 30-50 ℃, the pressure in the autoclave can be increased in the initial temperature rise stage, and in the process, the auxiliary pressure in the vacuum bag is removed;
in the stages of stepped sectional heating and pressing and heat preservation and pressure maintaining, the temperature is firstly raised to 110-120 ℃ and the pressure is 0.1MPa, then the temperature is raised to 120-150 ℃ and the pressure is increased to 0.5MPa in a sectional manner, the temperature is kept for 1h and then is continuously raised to 170-180 ℃, the pressure is kept at 0.5MPa in the process, the temperature is kept for 4-6h, then the temperature is reduced and the temperature is cooled to 120 ℃, and the thermal demolding is carried out.
In the above-described embodiments, the specific sequence and angle means that, when the prepreg is laid, the lay-up angle and the gradation position setting sequence can be adjusted according to the specific situation and actual need of the embodiment.
In particular, in this embodiment, the overall layering of the lower skin 3 is firstly completed, then the thickening layering of the lower skin 3 is completed according to a specific sequence, an angle and a gradual change position, then the frame beam 1 and the truss beam 2 are installed, the honeycomb 5 with the variable thickness and the variable cross section is laid in the concave area surrounded by the frame beam 1 and the truss beam 2, and then the layering of the upper skin 4 is completed. And finally, carrying out integral curing molding by means of equipment such as an autoclave, a curing oven and the like and vacuum bag auxiliary molding technology. Therefore, the preparation method realizes real integral curing molding.
Example 3
The embodiment comprises the following steps: the outer enveloping dimension of the honeycomb sandwich structure is phi 4200mm multiplied by 5038mm,2 pieces of trussed beams 2 are distributed on the left side and the right side of the sandwich structure along the length direction 5038mm, and 2 pieces of U-shaped frame beams 1 are distributed on the upper end and the lower end of the sandwich structure along the arc direction with the diameter phi 4200 mm; the honeycombs 5 with the thickness of 24.02mm-28.02mm are distributed in a concave area surrounded by 4 metal beams (2 trussed beams 2 and 2 frame beams 1).
The method comprises the following steps: the lower skin 3 finishes the gradual change of the prepreg paving according to a certain sequence and angle, then integrally lays the adhesive, and the sequence and the angle of the integral paving of the prepreg are as follows: [ +45 °/0 °/90 °/0 °/45 ° ], in the middle of the integral laying layer, the variable-thickness gradual-change laying of the lower skin 3 is completed through penetration, and the adhesive laying angle is 0 °;
step two: respectively installing the frame beam 1 and the truss beam 2 to the boundary positions of four positions of the lower skin 3 completed in the step one, contacting the lower surfaces of the frame beam 1 and the truss beam 2 with the surface of the lower skin 3, and controlling the gap of the intersection position of the frame beam 1 and the truss beam 2 to be 2.5mm;
step three: laying honeycombs 5 in sequence in the range of the concave shape surrounded by the frame beam 1 and the truss beam 2, and laying an adhesive on the upper surfaces of the honeycombs 5;
step four: on the basis of the completion of the third step, finishing the gradual-change layering of the upper skin 4 according to a set sequence and an angle, preparing a vacuum bag, and performing one-step forming on equipment such as an autoclave, a curing oven and the like, wherein the sequence and the angle of the overall layering of the upper skin 4 are as follows: [ +45 °/0 °/90 °/0 °/45 °/0 °/+45 ° ], and penetrating and completing the thickness-variable gradient paving of the lower skin in the middle of the integral paving;
step five: and (4) after hot demolding, obtaining the pre-embedded large metal beam honeycomb sandwich structure.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description has described specific embodiments of the present invention. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (9)
1. The utility model provides a pre-buried metal beam honeycomb sandwich structure which characterized in that includes: the honeycomb structural body comprises a metal beam, a lower skin (3), an upper skin (4) and a honeycomb (5);
go up covering (4) with install between covering (3) down the metal roof beam with honeycomb (5), the metal roof beam sets up honeycomb (5) week side position.
2. The pre-buried metal beam honeycomb sandwich structure of claim 1, wherein the metal beam comprises: the frame beam (1) and the truss beam (2);
the lower skin (3) and the upper skin (4) are both arranged into arc-shaped surface structures, arc lines of which extend in a straight line in a direction perpendicular to the surface where the arc lines are located;
the U-shaped frame beam (1) is arranged at the arc ends at the two ends of the lower skin (3) and the upper skin (4) and is matched with the arc ends of the lower skin (3) and the upper skin (4) in shape;
the trusses (2) of a straight line type are installed on the straight line side of both sides of the lower skin (3) and the upper skin (4).
3. The forming method of the embedded metal beam honeycomb sandwich structure of claim 2 is characterized by comprising the following steps:
s1, finishing gradual change paving of the lower skin (3) according to a set sequence and angle, and integrally paving an adhesive;
s2, respectively installing the truss girder (2) and the frame girder (1) to the peripheral side boundary position of the lower skin (3), wherein one side surfaces of the truss girder (2) and the frame girder (1) are in surface contact with the lower skin (3), and the gap of the intersection position of the truss girder (2) and the frame girder (1) is 1.5-3mm;
s3, laying the honeycomb (5) in a range enclosed by the truss beam (2) and the frame beam (1), and laying an adhesive on the honeycomb (5);
s4, after finishing the gradual change layering of the upper skin (4) according to a set sequence and a set angle, preparing a vacuum bag, and performing one-time curing molding through an autoclave and a curing oven;
and S5, obtaining the pre-buried metal beam honeycomb sandwich structure after hot demolding.
4. The molding method according to claim 3, wherein: the lower skin (3) and the upper skin (4) are made of glass fiber reinforced resin matrix composite materials, and the thickness of the composite materials is 1-3mm.
5. The molding method according to claim 3, wherein: the length of the truss beam (2) is larger than 3m, the width of the truss beam is 20-50mm, the arc-direction perimeter of the frame beam (1) is larger than 5m, and the width of the frame beam is 20-50mm.
6. The molding method according to claim 3, wherein: the honeycomb (5) is aramid fiber paper honeycomb, the thickness of the honeycomb paper is 0.05-0.08mm, the thickness of the honeycomb (5) is 20-40mm, and the density is 48-76kg/m 3 。
7. The molding method according to claim 3, wherein: in step S4, the curing and forming includes an initial heating and pressing stage, a stepped sectional heating and pressing stage, and a heat-preserving and pressure-maintaining stage.
8. The molding method according to claim 7, wherein: in the initial temperature rise and pressure rise stage, the temperature rise temperature is 30-50 ℃, the pressure in the autoclave is increased in the initial temperature rise stage, and the auxiliary pressure in the vacuum bag is removed;
in the stage of stepwise heating and pressurizing, firstly heating to 110-120 ℃, pressurizing to 0.1MPa, and then heating to 120-150 ℃, and pressurizing to 0.5MPa in stages and sections;
in the heat preservation and pressure maintaining stage, the temperature is kept for 1h, then the temperature is continuously raised to 170-180 ℃, the pressure is kept at 0.5MPa in the process, the temperature is kept for 4-6h, then the temperature is reduced and cooled to 120 ℃, and the thermal demolding is carried out.
9. A fairing, characterized by: the embedded metal beam honeycomb sandwich structure of claim 1 or 2 is adopted.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211580577.5A CN115958818A (en) | 2022-12-09 | 2022-12-09 | Embedded metal beam honeycomb sandwich structure, forming method and fairing |
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| CN202211580577.5A CN115958818A (en) | 2022-12-09 | 2022-12-09 | Embedded metal beam honeycomb sandwich structure, forming method and fairing |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117067637A (en) * | 2023-09-13 | 2023-11-17 | 哈尔滨远驰航空装备有限公司 | Resin-based composite honeycomb reinforcing structure and forming method thereof |
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2022
- 2022-12-09 CN CN202211580577.5A patent/CN115958818A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117067637A (en) * | 2023-09-13 | 2023-11-17 | 哈尔滨远驰航空装备有限公司 | Resin-based composite honeycomb reinforcing structure and forming method thereof |
| CN117067637B (en) * | 2023-09-13 | 2023-12-19 | 哈尔滨远驰航空装备有限公司 | Resin-based composite honeycomb reinforcing structure and forming method thereof |
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