CN110001182A - The preparation method of recoverable airship solar heat protection big bottom structure integrated with carrying - Google Patents
The preparation method of recoverable airship solar heat protection big bottom structure integrated with carrying Download PDFInfo
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- CN110001182A CN110001182A CN201910272652.3A CN201910272652A CN110001182A CN 110001182 A CN110001182 A CN 110001182A CN 201910272652 A CN201910272652 A CN 201910272652A CN 110001182 A CN110001182 A CN 110001182A
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- exterior skin
- heat shield
- core material
- inside panel
- carrying
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- 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
- B32B37/1018—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 using only vacuum
-
- 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
- B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
- B32B37/1284—Application of adhesive
-
- 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
- B32B37/14—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers
- B32B37/142—Laminating of sheets, panels or inserts, e.g. stiffeners, by wrapping in at least one outer layer, or inserting into a preformed pocket
-
- 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
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
-
- 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
- B32B2038/0076—Curing, vulcanising, cross-linking
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Health & Medical Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
- Fluid Mechanics (AREA)
- Laminated Bodies (AREA)
- Footwear And Its Accessory, Manufacturing Method And Apparatuses (AREA)
Abstract
The invention discloses a kind of preparation methods of recoverable airship solar heat protection big bottom structure integrated with carrying, and this method comprises the following steps: step 1: preparing core material, inner panel and outer panels；Step 2: the heat shield of outsole is prepared, and is punched in heat shield；Step 3: being glued the inner surface of outer panels and heat shield and solidify, and open up built-in fitting hole on outer panel, adds screw hole in the inner surface machine of outer panel and heat shield；Step 4: the one side of core material and outer panels are glued, and built-in fitting is embedded in core material by the built-in fitting hole of outer panels；Step 5: by the splicing of the another side of core material and inner panel and solidification, built-in fitting hole is opened up on inner panel；Step 6: the gasket at rear embedded part and interior connector sleeve is set in rear buried via hole, and is glued and solidifies with inner panel by the buried via hole after inner panel opens up；Step 7: outer surface brush coating, solidification and polishing to the heat shield of outsole.The present invention realizes carrying and anti-heat function.
Description
Technical field
The invention belongs to the recoverable airship thermal protection system technical field of the escape velocity more particularly to a kind of returns
The preparation method of formula airship solar heat protection big bottom structure integrated with carrying.
Background technique
Recoverable airship is changed into the thermal energy of air with the second space flight velocity ablated configuration process, most of kinetic energy,
And these thermal energy form high Aerodynamic Heating environment in the form of boundary layer convection current and Radiation From Shock Wave in spacecraft surface, outside airship
Surface must have reliable, resistance to erosion thermal protection system, protect the equipment inside the life security and spacecraft of spacefarer.Surface
Heat insulation material structural stability and integrity demands are higher, while heat shield is connected with internal structure, it is desirable that have very high
Bearing capacity, so recoverable airship proposes requirements at the higher level to the lightweight of thermal protection system, thermal protective performance and bearing capacity.
External space shuttle mostly uses a large amount of, low-density thermal insulation tile to be spliced, and that there are structural stabilities is poor for this connecting method, pacifies
The problems such as full property is poor, assembly is complicated, the lead time is long.Domestic Shenzhou spacecraft return capsule, which is used, is directly glued to metal for heat shield
Structure type on inner casing.To solve, external heat insulation tile of shuttle spicing forming type bring is insufficient, domestic Manned reentry capsule is anti-
Hot material does not have the deficiency of bearing function, is badly in need of developing heat insulation material low-density, high dimensional accuracy, integrally formed integration
Outsole moulding technique in thermal protection struc ture.
Summary of the invention
Technical problem solved by the present invention is overcome the deficiencies of the prior art and provide a kind of recoverable airship solar heat protection with
The preparation method of the big bottom structure of carrying integration, it is insufficient and domestic to solve external heat insulation tile of shuttle spicing forming type bring
Manned reentry capsule heat insulation material does not have the deficiency of bearing function, realizes carrying and anti-heat function.
The object of the invention is achieved by the following technical programs: a kind of recoverable airship solar heat protection outsole integrated with carrying
The preparation method of structure, described method includes following steps: step 1: prepare core material in the bearing structure of integrated outsole,
Inside panel and exterior skin；Step 2: the heat shield of integrated outsole is prepared, and is punched in heat shield；Step 3: to solar heat protection
Inner surface brush coating, solidification and the polishing of layer, the inner surface of exterior skin and heat shield is glued and is solidified later, and on exterior skin
Built-in fitting hole is opened up, adds screw hole in the inner surface machine of exterior skin and heat shield；Step 4: by the one side of core material and exterior skin glue
It connects, and built-in fitting is embedded in core material by the built-in fitting hole of exterior skin, and is solidified；Step 5: by the another side of core material
Splicing and solidification with inside panel, and built-in fitting hole is opened up on inside panel according to embedded location of the built-in fitting in core material；Step
Rapid six: rear embedded part is installed in rear buried via hole, and be glued and solidify with inside panel by the buried via hole after inside panel processing；Step 7: right
Outer surface brush coating, solidification and the polishing of the heat shield of integrated outsole.
In the preparation method of above-mentioned recoverable airship solar heat protection big bottom structure integrated with carrying, step 1 is specifically included: choosing
Determine the reinforcement and matrix, the reinforcement of exterior skin and matrix, the core material with sandwich of inside panel；By the reinforcement of inside panel
Unidirectional pre-immersion material is prepared by solwution method or hot melt arrangement with matrix, by unidirectional pre-immersion material manually lay or automatic fiber placement or
Automated tape-laying prepares inside panel pre-shaping blank, and inside panel pre-shaping blank is passed through vacuum bag-autoclave mode curing molding
Obtain the inside panel of integrated outsole；The reinforcement of exterior skin and matrix is unidirectional by solwution method or hot melt arrangement preparation
Unidirectional pre-immersion material is manually laid or automatic fiber placement or automated tape-laying prepares exterior skin pre-shaping blank, by exterior skin by prepreg
Pre-shaping blank obtains the exterior skin of integrated outsole by vacuum bag-autoclave mode curing molding.
It is described anti-in step 2 in the preparation method of above-mentioned recoverable airship solar heat protection big bottom structure integrated with carrying
The material of thermosphere is lightweight thermal-protect ablation material, and density is 0.2~0.9g/cm3；The inner surface and the outer surface of the heat shield
Machine adding method is NC Milling, and installation way is Special support tooling or built-up jig clamping.
In the preparation method of above-mentioned recoverable airship solar heat protection big bottom structure integrated with carrying, in step 3, in solar heat protection
The inner surface brush thermostable phenolic resin of layer, brush coating amount are 100~500g/m2；Then the outer layer of thermostable phenolic resin is again again
Brushing high-temperature-resisting silicon rubber, bondline thickness are 0.05~2mm；The inner surface of exterior skin and heat shield is glued and solidifies specific packet
It includes following steps: step 1: preparing the round valve of 300~Φ of exterior skin top center diameter of phi 1500；Step 2: preparation
Several fan shape leafs on exterior skin periphery；Step 3: round valve is attached at the top of the heat shield inner surface of head-shield, so that exterior skin
Round valve the center of circle and head-shield heat shield at the top of the center of circle it is concentric；Step 4: by fan shape leaf along the both sides of generatrix direction along week
It is open at 1~5 to respectively cutting, 5~150mm of Opening length；Step 5: all fan shape leafs are spliced into an entirety, each fan
Reserved 0.5~3mm piece, vacuumizes cure under pressure by vacuum bag-baking oven when shape valve splices.
In the preparation method of above-mentioned recoverable airship solar heat protection big bottom structure integrated with carrying, in step 4, pre-buried
The outer surface of part short transverse, which wraps up foamed glue and is embedded in core material, is assembled to position, and it is solid to vacuumize pressurization by vacuum bag-autoclave
Change；Wherein, the one side of core material is J47C glue film or J310B glue film with adhesive with exterior skin splicing.
In the preparation method of above-mentioned recoverable airship solar heat protection big bottom structure integrated with carrying, in step 5, inside panel
It is glued with core material and solidifies and specifically comprise the following steps: step 1: prepares 300~Φ of inside panel top center diameter of phi
1500 round valve；Step 2: several fan shape leafs on inside panel periphery are prepared；Step 3: round valve is attached to the core of head-shield
The top of material, it is desirable that the center of circle of inside panel circle valve and the top center of circle of core material are concentric；Step 4: by fan shape leaf along generatrix direction
Both sides circumferentially respectively cut at 1~5 be open, 5~150mm of Opening length；Step 5: by all points of valves be spliced into one it is whole
Body, reserved 0.5~3mm piece when each valve splices；Wherein, the splicing of inside panel and core material with adhesive be J47C glue film or
J310B glue film, and cure under pressure is vacuumized by vacuum bag-autoclave.
In the preparation method of above-mentioned recoverable airship solar heat protection big bottom structure integrated with carrying, in step 6, rear embedded part
It with adhesive is EA934NA or Redux420 glue or J133 glue with inside panel splicing.
In the preparation method of above-mentioned recoverable airship solar heat protection big bottom structure integrated with carrying, in step 7, heat shield
Outer surface brush coating be thermostable phenolic resin, brush coating amount be 100~500g/m2。
In the preparation method of above-mentioned recoverable airship solar heat protection big bottom structure integrated with carrying, the integration outsole it is blunt
Sphere inner sphere radius r1 is 500mm~3000mm, and blunt sphere ectosphere radius surface r2 is 500mm~4000mm, and total height h is 2m
Within, heat shield thickness δfIn 20~100mm range, sandwiched thickness δcIn 10~80mm range, the exterior skin of sandwich
Thickness δmIn 0.1~4mm range, the core thickness δ of sandwichxIn 2~79.6mm range.
In the preparation method of above-mentioned recoverable airship solar heat protection big bottom structure integrated with carrying, sandwich is X-cor folder
Layer structure, honeycomb sandwich construction, foamed sandwich structure or lattice structure.
Compared with prior art, the present invention has the following advantages:
(1) present invention solves the insufficient and domestic Manned reentry capsule of external heat insulation tile of shuttle spicing forming type bring and prevents
Hot material does not have the deficiency of bearing function, realizes carrying and anti-heat function；
(2) preparation method good manufacturability of the invention, it is adaptable, it is readily converted to production line mass production, is reduced
Cost.
Detailed description of the invention
By reading the following detailed description of the preferred embodiment, various other advantages and benefits are common for this field
Technical staff will become clear.The drawings are only for the purpose of illustrating a preferred embodiment, and is not considered as to the present invention
Limitation.And throughout the drawings, the same reference numbers will be used to refer to the same parts.In the accompanying drawings:
Fig. 1 is the schematic diagram of recoverable airship solar heat protection provided in an embodiment of the present invention big bottom structure integrated with carrying；
Fig. 1-1 is the interlayer knot in recoverable airship solar heat protection provided in an embodiment of the present invention big bottom structure integrated with carrying
The schematic diagram of structure；
Fig. 2 is the preparation method of recoverable airship solar heat protection provided in an embodiment of the present invention big bottom structure integrated with carrying
Flow chart；
Fig. 3 is the schematic diagram of the splitted structure of exterior skin provided in an embodiment of the present invention；
Fig. 4 is the schematic diagram of the splitted structure of inside panel provided in an embodiment of the present invention.
Specific embodiment
Exemplary embodiments of the present disclosure are described in more detail below with reference to accompanying drawings.Although showing the disclosure in attached drawing
Exemplary embodiment, it being understood, however, that may be realized in various forms the disclosure without should be by embodiments set forth here
It is limited.On the contrary, these embodiments are provided to facilitate a more thoroughly understanding of the present invention, and can be by the scope of the present disclosure
It is fully disclosed to those skilled in the art.It should be noted that in the absence of conflict, embodiment in the present invention and
Feature in embodiment can be combined with each other.The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
Recoverable airship outsole uses detachable thermal protection struc ture, and heat shield passes through bearing structure carbon covering honeycomb panel
It is connected with return capsule metal structure, airship outsole is blunt sphere hatch frame, the incremental Varying-thickness configuration (structure of ball bottom to corner
Type is as shown in Figure 1), it can be realized simultaneously carrying and anti-heat function.
Fig. 2 is the preparation of recoverable airship solar heat protection provided in an embodiment of the present invention big bottom structure integrated with carrying
The flow chart of method.As shown in Fig. 2, this method comprises the following steps:
First carries out the preparation of the core material, inside panel and exterior skin of the sandwich in the bearing structure of integrated outsole.
The inner surface and the outer surface machine of second progress heat shield adds and part is punched.
Third carries out inner surface brush coating, solidification and the polishing of heat shield, carries out the inner surface of exterior skin and heat shield later
It is glued and solidifies, with the built-in fitting hole for beating exterior skin, adds screw hole in the inner surface machine of exterior skin and heat shield.
4th carries out the splicing of the core material, built-in fitting and exterior skin of sandwich and solidification.
5th carries out the splicing of the core material and inside panel of sandwich, solidification；With the built-in fitting hole for beating inside panel.
6th carries out the rear buried via hole processing of the inside panel of sandwich.
Embedded part is glued with the gasket at interior connector sleeve after 7th progress.
8th carry out heat shield outer surface and outer profile machine adds, interlayer outer profile and large opening machine add, integrated outsole
The outer surface brush coating of heat shield, solidification, polishing.
The sandwich is X-cor sandwich, honeycomb sandwich construction, foamed sandwich structure, lattice structure.
The sandwich covering is fiber-reinforced resin matrix compound material.Kinds of fibers can be carbon fiber, glass fibers
Dimension, organic fiber, ceramic fibre and metallic fiber etc..Carbon fiber is T300 and the above high-strength carbon fibre or the M40 and above Gao Mo
Measure carbon fiber etc..Glass fibre is E glass fibre, S glass fibre, basalt fibre etc..Organic fiber is aramid fiber, superelevation
Molecular weight polyethylene fiber, polyimide fiber, pbo fiber, PBI fiber etc..Ceramic fibre alumina silicate fibre and modified fibre.
Metallic fiber is copper fiber, aluminum fiber etc..
The resin matrix is thermoplastic resin, including polypropylene, polycarbonate, polyamide and polysulfones etc..Thermosetting property tree
Rouge includes the resins such as epoxy resin, cyanate ester resin.The inside and outside covering composite forming method is first to manually lay or spread automatically
Silk or automated tape-laying laying, then pass through vacuum bag-solidification of hot-press tank molding.Manually lay*Bing unidirectional pre-immersion material preparation method used is
Hot melt or solwution method, thickness in monolayer 0.02mm~0.5mm range.
The heat insulation material is lightweight thermal-protect ablation material, and density is in 0.2~0.9g/cm3Range.
The heat insulation material inner and outer surfaces machine adding method be NC Milling, installation way be Special support tooling or
Built-up jig clamping.
The heat insulation material inner surface brush coating is thermostable phenolic resin, 100~500g/m of brush coating amount2Range.
The exterior skin is high-temperature-resisting silicon rubber, bondline thickness 0.05~2mm range with adhesive with heat shield splicing.Gu
Change mode is that vacuum bag-baking oven vacuumizes cure under pressure.
The sandwich structure core is to have hole aluminum honeycomb, foam, C-cor etc..
The splicing of the core material, embedded part and exterior skin is J47C glue film or J310B glue film and similar products with adhesive,
Foamed glue is J47D or J245D2 and similar products.Curing mode is that vacuum bag-autoclave vacuumizes cure under pressure.
Burying machine after described to add with combination machine adding method is NC Milling, and installation way is Special support tooling or combination
Fixture clamping.
The splicing of the core material and inside panel is J47C glue film or J310B glue film and similar products with adhesive.
It is EA934NA or Redux420 glue or J133 glue that splicing is buried after described with adhesive.
The attachment spacers is metal or nonmetallic materials, and adhesive is Redux420 glue or J133 glue.
Heat insulation material outer surface brush coating is thermostable phenolic resin, 100~500g/m of brush coating amount2Range.
Process island of the preparation method design convenient for forming operation and to guarantee dimensional accuracy, using increased in size, increases
Configurations are added to carry out the increase design of product blank size.
The outsole supporting tool refers to pneumatic outer mold surface (convex surface) the dead size design according to technique redesign, outer dimension
Greater than the integrated support tooling of redesign product size, tooling requires to be resistant to 200 DEG C or more high temperature；Product type face region it is airtight
Property require vacuum pressure maintaining 10 minutes in change value of pressure be less than 0.01MPa.
Specifically, this method comprises the following steps: (1) selecting the reinforcement of covering according to the target capabilities of product and size
And resin matrix.
(2) core material of sandwich is selected according to the target capabilities of integrated outsole.
(3) reinforcement in step (1) unidirectional pre-immersion material is prepared by solwution method or hot melt arrangement with matrix to use
Automatic fiber placement or automated tape-laying are used in manually lay*Bing, or by infiltration.
(4) it is manually laid with the prepreg in step (3) or automatic fiber placement or automated tape-laying prepares carbon fibre composite
Covering pre-shaping blank.
(5) the covering pre-shaping blank in step (4) is passed through into vacuum bag-autoclave mode curing molding.
(6) NC Milling heat insulation material inner and outer surfaces, installation way are that Special support tooling or built-up jig fill
Folder.
(7) the heat insulation material inner surface brush thermostable phenolic resin after step (6) processing, 100~500g/m of brush coating amount2
Range.
(8) the heat insulation material inner surface brushing high-temperature-resisting silicon rubber in step (7), bondline thickness 0.05~2mm range.
(9) it determines that inside and outside covering divides valve division, is attached to after then dividing exterior skin prepared by step (5) to valve according to scheme
On heat insulation material inner surface high-temperature-resisting silicon rubber layer in step (8), cure under pressure is vacuumized by vacuum bag-baking oven.
(10) it polishes and step (9) China and foreign countries' skin-surface and clears up, brushing primer and glue film.
(11) core material is spliced into target size, be attached on the exterior skin in step (10).
(12) foamed glue or similar products are wrapped up around built-in fitting and are embedded in core material and are assembled to position, pass through vacuum bag-heat
Pressure tank vacuumizes cure under pressure.
(13) core surfaces that will be attached to after the Inner Mongol subcutaneous surface rubberizing film of step (5) preparation in step (12).
(14) buried via hole after NC Milling, installation way are Special support tooling or built-up jig clamping.
(15) it is glued the rear embedded part of corresponding type and quantity in rear buried via hole in step (14) and solidifies.
(16) numerical control Combined machining part height, hole location and appearance profile, installation way are Special support tooling or group
Co-clip has clamping.
(17) in step (16) heat insulation material outer surface brushing thermostable phenolic resin, 100~500g/m of brush coating amount2Model
It encloses, obtains integrated outsole.
In step (9), exterior skin includes that central circular divides valve 1 and several periphery sectors to divide valve 2；Several peripheries fan
The circumferential setting that shape divides valve 2 to divide valve 1 along central circular, two neighboring periphery sector divide between valve 2 and are connected by piece 31.Fan
Shape divides the opening 4 being provided on valve 2 circumferentially.
Exterior skin is the round valve for being divided into a 300~Φ of diameter of phi 1500 at the top of exterior skin, is connected with the circle
Periphery is divided into 2~36 fan shape leafs, and every valve is circumferentially cut along the both sides of generatrix direction and is open at 1~5, and Opening length 5~
150mm.All points of valves are spliced into an entirety, reserved 0.5~3mm piece when each valve splices.Divide valve mode as shown in Figure 3.
Inside panel includes that central circular divides valve 11 and several periphery sectors to divide valve 21；Several periphery sectors divide valve 21 edge
Central circular divides the circumferential setting of valve 11, and two neighboring periphery sector divides between valve 21 and is connected by piece 31.Sector divides valve
Opening 41 circumferentially is provided on 21.
Inside panel is the round valve for being divided into a 300~Φ of diameter of phi 1500 at the top of inside panel, is connected with the circle
Periphery is divided into 2~36 fan shape leafs, and every valve is circumferentially cut along the both sides of generatrix direction and is open at 1~5, and Opening length 5~
150mm.All points of valves are spliced into an entirety, reserved 0.5~3mm piece when each valve splices.Divide valve mode as shown in Figure 4.
1 embodiment is more detailed below illustrates preparation process:
The opening maximum outside diameter R2035.1mm of integrated outsole, inside and outside spherical surface diameter be respectively R4715mm,
R4570mm is designed, eccentric 88mm by the centre of sphere bias of inside and outside spherical surface, forms what ball base thickness degree 57mm was incremented by corner
Varying-thickness configuration.Honeycomb interlayer thickness 30mm, skin material are M40J/4211 resin composite materials, skin thickness 0.64mm, bee
Steps are as follows for the integrated outsole preparation method of nest core specification 0.03 × 3:
(1) reinforcement of the high modulus carbon fiber M40J as covering is selected, 4211 resin of high-temp epoxy is resin matrix.
(2) selecting has hole aluminium honeycomb core as core material.
(3) reinforcement in step (1) is prepared into unidirectional pre-immersion material, thickness in monolayer by solwution method arrangement with matrix
0.08mm。
(4) it is manually laid with the prepreg in step (3) and prepares carbon fibre composite covering pre-shaping blank, covering point
7 valve of valve.
(5) the covering pre-shaping blank in step (4) is passed through into vacuum bag-autoclave mode curing molding.
(6) NC Milling heat insulation material surfaces externally and internally, installation way are Special support tooling.
(7) 192 phenolic resin of heat insulation material inner surface brush after step (6) processing, brush coating amount (250 ± 10) g/m2。
(8) heat insulation material inner surface the brushing RTV560, bondline thickness 0.15mm in step (7).
(9) it determines that inside and outside covering divides valve division, carbon fiber exterior skin prepared by step (5) is then divided into 7 according to scheme
Valve, top are the circle of Φ 1200, and periphery is that 6 valves are fan-shaped, the heat insulation material inner surface high-temperature-resisting silicon rubber layer being attached in step (8)
On, cure under pressure is vacuumized by vacuum bag-baking oven.
(10) it polishes and step (9) China and foreign countries' skin-surface and clears up, brush J47B primer simultaneously pastes one layer of J47C glue film.
(11) by honeycomb core point 11 valves splicing, wherein top is the circle of Φ 1200, periphery is that 10 valves are fan-shaped, between each section
It is connected, is attached on the exterior skin in step (10) with J47D.
(12) foamed glue J47D is wrapped up around built-in fitting and is embedded in honeycomb core assembly in place, passes through vacuum bag-autoclave
Vacuumize cure under pressure.
(13) divide by the carbon fiber Inner Mongol subcutaneous surface brush J47B primer of step (5) preparation and after pasting one layer of J47C glue film
Valve, top are the circle of Φ 1300, and periphery is that 6 valves are fan-shaped, after be attached to honeycomb wicking surface in step (12), glue film face and honeycomb core
Contact.
(14) buried via hole after NC Milling, installation way are Special support tooling.
(15) it is glued the rear embedded part of corresponding type and quantity in rear buried via hole in step (14) and solidifies.
(16) numerical control Combined machining part height, hole location and appearance profile, installation way are Special support tooling.
(17) 192 phenolic resin, glue amount (250 ± 10) g/m are brushed in step (16) heat insulation material outer surface2, obtain one
Body outsole.
Fig. 1-1 is the interlayer knot in recoverable airship solar heat protection provided in an embodiment of the present invention big bottom structure integrated with carrying
The schematic diagram of structure.As Figure 1-1, compared with prior art, the big bottom structure of integration of the invention be outer layer heat insulation material with
Internal layer sandwich has thermal protective performance and load-carrying properties concurrently, while having the function of detachably to reuse, and preparation of the invention
Method Product Precision is high, and dimensional accuracy is better than 2mm.Can be achieved size range it is wide, blunt sphere inner sphere radius r1 SR500mm~
SR3000mm range, blunt sphere ectosphere radius surface r2 are within SR500mm~SR4000mm range, total height h is 2m, heat shield
Thickness δfIn 20~100mm range, sandwiched thickness δcIn 10~80mm range, sandwich plate thickness δm0.1~
4mm range, sandwich structure core thickness δxIn 2~79.6mm range.
The present invention solves the insufficient and domestic Manned reentry capsule solar heat protection of external heat insulation tile of shuttle spicing forming type bring
Material does not have the deficiency of bearing function, realizes carrying and anti-heat function；Preparation method good manufacturability of the invention, adaptability
By force, it is readily converted to production line mass production, reduces cost.
Embodiment described above is the present invention more preferably specific embodiment, and those skilled in the art is in this hair
The usual variations and alternatives carried out in bright technical proposal scope should be all included within the scope of the present invention.
Claims (10)
1. a kind of preparation method of recoverable airship solar heat protection big bottom structure integrated with carrying, which is characterized in that the method packet
Include following steps:
Step 1: core material, inside panel and the exterior skin in the bearing structure of integrated outsole are prepared；
Step 2: the heat shield of integrated outsole is prepared, and is punched in heat shield；
Step 3: the inner surface of exterior skin and heat shield is glued simultaneously by inner surface brush coating, solidification and polishing to heat shield later
Solidification, and built-in fitting hole is opened up on exterior skin, add screw hole in the inner surface machine of exterior skin and heat shield；
Step 4: the one side of core material and exterior skin are glued, and built-in fitting is embedded in core material by the built-in fitting hole of exterior skin,
And solidified；
Step 5: opening up built-in fitting hole on inner panel, will the another side of inside panel and core material is glued and be solidified, and according to pre-
Embedded location of the embedded part in core material opens up built-in fitting hole on inside panel；
Step 6: rear embedded part is installed in rear buried via hole, and be glued and solidify with inside panel by the buried via hole after inside panel processing；
Step 7: outer surface brush coating, solidification and polishing to the heat shield of integrated outsole.
2. the preparation method of recoverable airship solar heat protection according to claim 1 big bottom structure integrated with carrying, feature
Be: step 1 specifically includes:
The reinforcement and matrix, the reinforcement of exterior skin and matrix of selected inside panel, the core material with sandwich；
The reinforcement of inside panel and matrix are prepared into unidirectional pre-immersion material by solwution method or hot melt arrangement, by unidirectional pre-immersion material
It manually lays or automatic fiber placement or automated tape-laying prepares inside panel pre-shaping blank, inside panel pre-shaping blank is passed through into vacuum
Bag-autoclave mode curing molding obtains the inside panel of integrated outsole；
The reinforcement of exterior skin and matrix are prepared into unidirectional pre-immersion material by solwution method or hot melt arrangement, by unidirectional pre-immersion material
It manually lays or automatic fiber placement or automated tape-laying prepares exterior skin pre-shaping blank, exterior skin pre-shaping blank is passed through into vacuum
Bag-autoclave mode curing molding obtains the exterior skin of integrated outsole.
3. the preparation method of recoverable airship solar heat protection according to claim 1 big bottom structure integrated with carrying, feature
Be: in step 2, the material of the heat shield is lightweight thermal-protect ablation material, and density is 0.2~0.9g/cm3；It is described anti-
The machine adding method of the inner surface and the outer surface of thermosphere is NC Milling, and installation way is Special support tooling or built-up jig
Clamping.
4. the preparation method of recoverable airship solar heat protection according to claim 1 big bottom structure integrated with carrying, feature
Be: in step 3, in the inner surface brush thermostable phenolic resin of heat shield, brush coating amount is 100~500g/ ㎡；Then again
Brushing high-temperature-resisting silicon rubber, bondline thickness are 0.05~2mm to the outer layer of thermostable phenolic resin again；
The inner surface of exterior skin and heat shield is glued and is solidified and is specifically comprised the following steps:
Step 1: the round valve of 300~Φ of exterior skin top center diameter of phi 1500 is prepared；
Step 2: several fan shape leafs on exterior skin periphery are prepared；
Step 3: round valve is attached at the top of the heat shield inner surface of head-shield, so that the center of circle of the round valve of exterior skin and head-shield
The center of circle is concentric at the top of heat shield；
Step 4: fan shape leaf circumferentially respectively being cut along the both sides of generatrix direction and is open at 1~5,5~150mm of Opening length；
Step 5: all fan shape leafs are spliced into an entirety, reserved 0.5~3mm piece, passes through when each fan shape leaf splices
Vacuum bag-baking oven vacuumizes cure under pressure.
5. the preparation method of recoverable airship solar heat protection according to claim 1 big bottom structure integrated with carrying, feature
It is: in step 4, wraps up foamed glue in the outer surface of built-in fitting short transverse and be embedded in core material and be assembled to position, pass through vacuum
Bag-autoclave vacuumizes cure under pressure；Wherein,
The one side of core material is J47C glue film or J310B glue film with adhesive with exterior skin splicing.
6. the preparation method of recoverable airship solar heat protection according to claim 1 big bottom structure integrated with carrying, feature
Be: in step 5, inside panel is glued and is solidified with core material and specifically comprised the following steps:
Step 1: the round valve of 300~Φ of inside panel top center diameter of phi 1500 is prepared；
Step 2: several fan shape leafs on inside panel periphery are prepared；
Step 3: round valve is attached to the top of the core material of head-shield, it is desirable that the center of circle of inside panel circle valve and the top circle of core material
The heart is concentric；
Step 4: fan shape leaf circumferentially respectively being cut along the both sides of generatrix direction and is open at 1~5,5~150mm of Opening length；
Step 5: being spliced into an entirety for all points of valves, reserved 0.5~3mm piece when each valve splices；
Wherein, the splicing of inside panel and core material is J47C glue film or J310B glue film with adhesive, and passes through vacuum bag-hot pressing
Tank vacuumizes cure under pressure.
7. the preparation method of recoverable airship solar heat protection according to claim 1 big bottom structure integrated with carrying, feature
Be: in step 6, rear embedded part is EA934NA or Redux420 glue or J133 glue with adhesive with inside panel splicing.
8. the preparation method of recoverable airship solar heat protection according to claim 1 big bottom structure integrated with carrying, feature
Be: in step 7, the outer surface brush coating of heat shield is thermostable phenolic resin, and brush coating amount is 100~500g/ ㎡.
9. the preparation method of recoverable airship solar heat protection according to claim 1 big bottom structure integrated with carrying, feature
Be: the blunt sphere inner sphere radius r1 of the integration outsole is 500mm~3000mm, and blunt sphere ectosphere radius surface r2 is
500mm~4000mm, total height h are heat shield thickness δ within 2mfIn 20~100mm range, sandwiched thickness δc10~
80mm range, the exterior skin thickness δ of sandwichmIn 0.1~4mm range, the core thickness δ of sandwichxIn 2~79.6mm
Range.
10. the preparation method of recoverable airship solar heat protection according to claim 2 big bottom structure integrated with carrying, feature
Be: sandwich is X-cor sandwich, honeycomb sandwich construction, foamed sandwich structure or lattice structure.
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| CN110001181A (en) * | 2019-04-04 | 2019-07-12 | 北京卫星制造厂有限公司 | The preparation method of recoverable airship solar heat protection hood structure integrated with carrying |
| CN111805938A (en) * | 2020-06-28 | 2020-10-23 | 北京电子工程总体研究所 | Heat-proof bearing integrated structure for aircraft and forming method thereof |
| CN112895611A (en) * | 2021-02-19 | 2021-06-04 | 航天科工空间工程发展有限公司 | Satellite structure cabin board |
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