CN110978558B - Preparation method of seal-head-free fiber reinforced resin matrix composite material combustion chamber shell for rocket projectile - Google Patents
Preparation method of seal-head-free fiber reinforced resin matrix composite material combustion chamber shell for rocket projectile Download PDFInfo
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- CN110978558B CN110978558B CN201911400537.6A CN201911400537A CN110978558B CN 110978558 B CN110978558 B CN 110978558B CN 201911400537 A CN201911400537 A CN 201911400537A CN 110978558 B CN110978558 B CN 110978558B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/32—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B11/00—Making preforms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B11/00—Making preforms
- B29B11/04—Making preforms by assembling preformed material
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B15/00—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00
- B29B15/08—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00 of reinforcements or fillers
- B29B15/10—Coating or impregnating independently of the moulding or shaping step
- B29B15/12—Coating or impregnating independently of the moulding or shaping step of reinforcements of indefinite length
- B29B15/122—Coating or impregnating independently of the moulding or shaping step of reinforcements of indefinite length with a matrix in liquid form, e.g. as melt, solution or latex
- B29B15/125—Coating or impregnating independently of the moulding or shaping step of reinforcements of indefinite length with a matrix in liquid form, e.g. as melt, solution or latex by dipping
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B15/00—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00
- B29B15/08—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00 of reinforcements or fillers
- B29B15/10—Coating or impregnating independently of the moulding or shaping step
- B29B15/12—Coating or impregnating independently of the moulding or shaping step of reinforcements of indefinite length
- B29B15/14—Coating or impregnating independently of the moulding or shaping step of reinforcements of indefinite length of filaments or wires
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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
- B29C33/38—Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
- B29C33/3842—Manufacturing moulds, e.g. shaping the mould surface by machining
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3097—Cosmonautical vehicles; Rockets
Abstract
The invention discloses a preparation method of a seal-head-free fiber reinforced resin matrix composite material combustion chamber shell for rocket projectiles, and relates to the field of preparation methods of polymer matrix composite materials. The invention aims to solve the technical problems of poor heat insulation, low bursting strength and heavy mass of the combustion chamber shell prepared by the existing method. The method comprises the following steps: firstly, milling the outside of the metal ring to obtain a metal wire hanging ring; secondly, assembling an assembly part; dipping the fiber yarn, and winding the fiber yarn on the surface of the assembly; fourthly, heating and solidifying, naturally cooling, and then demoulding the core-pulling mould. The lining layer has good performance, and can meet the air tightness and ablation resistance in the combustion process of the combustion chamber grain. The requirements on the pressure resistance and the rigidity of the shell are met through the winding and forming structure layer. The fiber yarn is regularly dropped between the yarn hanging platforms of the metal wire hanging ring, so that the connection strength of the composite material and the metal and the bursting pressure of the shell are improved. The invention is used for preparing the seal-head-free fiber reinforced resin matrix composite material combustion chamber shell of the rocket projectile.
Description
Technical Field
The invention relates to the field of preparation methods of polymer-based composite materials.
Background
The rocket projectile mainly comprises a warhead, a rocket engine, a stabilizing device and the like. A warhead is a component that exerts its operational effectiveness at the end of a trajectory. The rocket engine is a propulsion power device which enables the rocket to fly, and the rocket projectile mainly adopts a solid rocket engine at present. The solid rocket engine consists of a connecting bottom, a combustion chamber, solid propellant charge, a charge supporting device, a spray pipe, an igniter and the like. Rocket projectiles can be classified into army rocket projectiles, navy rocket projectiles and air force rocket projectiles according to the types of launching platforms.
The solid rocket engine mainly comprises a combustion chamber, a jet pipe, a charging supporting device and an ignition device. The combustion chamber is one of the important parts of the solid rocket engine and is composed of a combustion chamber shell (generally a cylinder), front and rear end enclosures and an inner liner to form a semi-closed container. The combustion chamber housing structure is generally cylindrical, with the front end connected to the connecting ring and the rear end connected to the nozzle, and the housing can be divided into two types, a metal structure and a filament winding structure, depending on the materials and processing methods used. At present, the combustion chamber shell prepared by the existing method has the technical problems of poor heat insulation, low bursting strength and heavy quality, and influences the performance of the rocket projectile.
Disclosure of Invention
The invention provides a preparation method of a head-free fiber reinforced resin matrix composite material combustion chamber shell for rocket projectiles, aiming at solving the technical problems of poor heat insulation, low bursting strength and heavy mass of the combustion chamber shell prepared by the existing method.
A preparation method of a head-free fiber reinforced resin matrix composite material combustion chamber shell for a rocket projectile specifically comprises the following steps:
firstly, milling the surface of the outer ring of the metal ring to form a wire hanging table which is uniformly distributed to obtain a metal wire hanging ring;
secondly, assembling the lining layer material and the metal wire hanging ring on the core mold to obtain an assembly part;
thirdly, putting the fiber yarn into the modified epoxy resin adhesive for gum dipping, and then winding the fiber yarn on the surface of the assembly part obtained in the second step to obtain a shell prefabricated part;
heating the shell prefabricated member to 90-100 ℃, preserving heat for 1-2 hours, then heating to 110-120 ℃, preserving heat for 1-2 hours, then heating to 150-160 ℃, preserving heat for 4-6 hours, then cooling and demolding to obtain the shell of the combustion chamber, and completing the preparation method of the shell of the non-end-enclosure fiber reinforced resin matrix composite combustion chamber for the rocket projectile.
Further, in the first step, the material of the metal ring is 30CrMnSiA or TC 4; the outer diameter of the metal ring is 68-200 mm, the wall thickness is 2-5 mm, and the width is 30-80 mm.
Further, a metal wire hanging ring is obtained in the first step in a cross milling mode, the total number of wire hanging tables on the surface of the metal wire hanging ring is 42-140, the number of single-ring wire hanging tables is 14-28, and the total number of single-ring wire hanging tables is 3-5; the root of the wire hanging table is prismatic, the side length is 1-2 mm, the included angle of adjacent sides is 45-90 degrees, the height of the wire hanging table is 0.5-1 mm, and the upward 'drawing' inclination is 1-3 degrees.
Further, the preparation method of the core mold in the second step comprises the following steps:
mixing a polyvinyl alcohol solution with the mass concentration of 80-95% and river sand according to the mass ratio of (10-20) to (90-80), then placing the mixture into a sand core mold forming mold, heating and curing at the curing temperature of 100-120 ℃ for 6-10 h, and demolding to obtain a core mold;
or winding the hemp rope on the outer surface of the core mold, controlling the winding tension of the hemp rope to be 40N and no gap between the hemp ropes, mixing gypsum and cement according to the mass ratio of (60-70) to (40-30) to obtain mixed slurry, scraping the mixed slurry onto the surface of the core mold for winding the hemp rope, controlling the thickness of the mixed slurry to be 10-15 mm, and drying to obtain the core mold.
Further, the assembly method in the second step comprises the following steps:
mixing rubber serving as a lining layer material, then grinding the rubber into a rubber sheet layer with the thickness of 0.5-1.0 mm, coating the rubber sheet layer on the surface of a core mold, wherein the number of the coating layers is 2-3, then respectively assembling two metal wire hanging rings at two ends of the core mold coated with the rubber sheet layer, and controlling the lap joint width of the metal wire hanging rings and the rubber sheet layer to be 5-10 mm;
or taking rubber as the material of the inner liner, mixing the rubber, then grinding the rubber into a rubber sheet layer with the thickness of 0.5-1.0 mm, carrying out die pressing on the metal wire hanging ring and the rubber sheet layer to obtain die pressing pieces, and then respectively assembling the two die pressing pieces to the two ends of the mandrel through the positioning sleeve; coating the surface of the core mold with 2-3 coating layers by using a rubber sheet layer, and lapping and laying the rubber sheet layer and the mold pressing pieces at two ends of the core mold, wherein the lapping width is controlled to be 5-10 mm; the mould pressing process comprises the following steps: heating to 90-100 ℃, preserving heat for 1-2 h, then heating to 110-120 ℃, preserving heat for 1-2 h, then heating to 150-160 ℃, preserving heat for 4-6 h;
or taking the high silica fiber cloth reinforced phenolic base prepreg as an inner lining material, carrying out die pressing on the high silica fiber cloth reinforced phenolic base prepreg and two metal wire hanging rings to obtain a cylindrical die pressing piece, wherein the two metal wire hanging rings are respectively positioned at two ends of the cylindrical die pressing piece, and then assembling the cylindrical die pressing piece on a mandrel through a positioning sleeve; the mould pressing process comprises the following steps: heating to 140-180 ℃, and preserving heat for 3-6 h.
The invention has the beneficial effects that:
the seal-head-free fiber reinforced resin matrix (FRP) combustion chamber shell for rocket projectiles consists of a wire hanging ring, an inner liner layer and a structural layer, wherein the inner liner layer has good heat insulation, ablation resistance, scouring resistance and other properties, and can meet the air tightness and ablation resistance of a combustion chamber explosive column in the combustion process. And the combustion chamber structure layer formed by the winding process can meet the requirements on pressure resistance and rigidity of the shell. In addition, a certain number of thread hanging tables are milled on the surface of the metal thread hanging ring, fiber yarns fall between the thread hanging tables according to rules in the winding forming process, the shearing strength between the metal thread hanging ring and the structural layer is increased by the connection mode of the thread hanging ring and the structural layer, and further the strength of the weak position of the shell, namely the strength between the thread hanging ring and the structural layer is improved, so that the explosion pressure of the shell is further improved.
The explosion pressure of the shell can reach 9-30 MPa, which shows that the shell has pressure resistance and stronger rigidity performance.
The invention is used for preparing the seal-head-free fiber reinforced resin matrix composite material combustion chamber shell of the rocket projectile.
Drawings
Fig. 1 is a schematic structural diagram of a head-free fiber reinforced resin matrix composite combustion chamber shell for a rocket projectile prepared according to a first embodiment, wherein 1 represents a metal suspension wire ring, 2 represents an inner liner layer, and 3 represents a structural layer;
FIG. 2 is a cross-sectional view of a wire loop according to one embodiment;
FIG. 3 is a front view of a wire loop according to one embodiment;
fig. 4 is a schematic view of a wire hanging platform on the surface of a metal wire hanging ring according to a first embodiment.
Detailed Description
The technical solution of the present invention is not limited to the specific embodiments listed below, and includes any combination of the specific embodiments.
The first embodiment is as follows: the embodiment of the invention relates to a preparation method of a seal-head-free fiber reinforced resin matrix composite material combustion chamber shell for rocket projectiles, which specifically comprises the following steps:
firstly, milling the surface of the outer ring of the metal ring to form a wire hanging table which is uniformly distributed to obtain a metal wire hanging ring;
secondly, assembling the lining layer material and the metal wire hanging ring on the core mold to obtain an assembly part;
thirdly, putting the fiber yarn into the modified epoxy resin adhesive for gum dipping, and then winding the fiber yarn on the surface of the assembly part obtained in the second step to obtain a shell prefabricated part;
heating the shell prefabricated member to 90-100 ℃, preserving heat for 1-2 hours, then heating to 110-120 ℃, preserving heat for 1-2 hours, then heating to 150-160 ℃, preserving heat for 4-6 hours, then cooling and demolding to obtain the shell of the combustion chamber, and completing the preparation method of the shell of the non-end-enclosure fiber reinforced resin matrix composite combustion chamber for the rocket projectile.
The seal head-free fiber reinforced resin matrix composite material combustion chamber shell for the rocket projectile prepared by the embodiment is composed of a metal wire hanging ring, an inner liner layer and a structural layer; the inner liner layer is formed by vulcanizing the inner liner layer material, and after gum dipping is carried out in the modified epoxy resin glue, the fiber yarns wound on the surface of the assembly part form a structural layer by curing.
In fig. 4, the number of the loops distributed on the wire hanging table on the surface of the metal wire hanging loop is 5.
The second embodiment is as follows: the first difference between the present embodiment and the specific embodiment is: in the first step, the material of the metal ring is 30CrMnSiA or TC 4; the outer diameter of the metal ring is 68-200 mm, the wall thickness is 2-5 mm, and the width is 30-80 mm. The rest is the same as the first embodiment.
The third concrete implementation mode: the present embodiment differs from the first or second embodiment in that: in the first step, a metal wire hanging ring is obtained by adopting a cross milling mode, the total number of wire hanging tables on the surface of the metal wire hanging ring is 42-140, and the number of single-ring wire hanging tables is 14-28, and the total number of single-ring wire hanging tables is 3-5; the root of the wire hanging table is prismatic, the side length is 1-2 mm, the included angle of adjacent sides is 45-90 degrees, the height of the wire hanging table is 0.5-1 mm, and the upward 'drawing' inclination is 1-3 degrees. The other is the same as in the first or second embodiment.
The number of the loops distributed on the wire hanging table on the surface of the metal wire hanging ring is 3-5 loops.
The fourth concrete implementation mode: the difference between this embodiment mode and one of the first to third embodiment modes is: the preparation method of the core mold in the second step comprises the following steps:
mixing a polyvinyl alcohol solution with the mass concentration of 80-95% and river sand according to the mass ratio of (10-20) to (90-80), then placing the mixture into a sand core mold forming mold, heating and curing at the curing temperature of 100-120 ℃ for 6-10 h, and demolding to obtain a core mold;
or winding the hemp rope on the outer surface of the core mold, controlling the winding tension of the hemp rope to be 40N and no gap between the hemp ropes, mixing gypsum and cement according to the mass ratio of (60-70) to (40-30) to obtain mixed slurry, scraping the mixed slurry onto the surface of the core mold for winding the hemp rope, controlling the thickness of the mixed slurry to be 10-15 mm, and drying to obtain the core mold. The others are the same as in one of the first to third embodiments.
The fifth concrete implementation mode: the difference between this embodiment and one of the first to fourth embodiments is: the assembly method comprises the following steps:
mixing rubber serving as a lining layer material, then grinding the rubber into a rubber sheet layer with the thickness of 0.5-1.0 mm, coating the rubber sheet layer on the surface of a core mold, wherein the number of the coating layers is 2-3, then respectively assembling two metal wire hanging rings at two ends of the core mold coated with the rubber sheet layer, and controlling the lap joint width of the metal wire hanging rings and the rubber sheet layer to be 5-10 mm;
or taking rubber as the material of the inner liner, mixing the rubber, then grinding the rubber into a rubber sheet layer with the thickness of 0.5-1.0 mm, carrying out die pressing on the metal wire hanging ring and the rubber sheet layer to obtain die pressing pieces, and then respectively assembling the two die pressing pieces to the two ends of the mandrel through the positioning sleeve; coating the surface of the core mold with 2-3 coating layers by using a rubber sheet layer, and lapping and laying the rubber sheet layer and the mold pressing pieces at two ends of the core mold, wherein the lapping width is controlled to be 5-10 mm; the mould pressing process comprises the following steps: heating to 90-100 ℃, preserving heat for 1-2 h, then heating to 110-120 ℃, preserving heat for 1-2 h, then heating to 150-160 ℃, preserving heat for 4-6 h;
or taking the high silica fiber cloth reinforced phenolic base prepreg as an inner lining material, carrying out die pressing on the high silica fiber cloth reinforced phenolic base prepreg and two metal wire hanging rings to obtain a cylindrical die pressing piece, wherein the two metal wire hanging rings are respectively positioned at two ends of the cylindrical die pressing piece, and then assembling the cylindrical die pressing piece on a mandrel through a positioning sleeve; the mould pressing process comprises the following steps: heating to 140-180 ℃, and preserving heat for 3-6 h. The other is the same as one of the first to fourth embodiments.
In the embodiment, the manufacturer of the high silica fiber cloth reinforced phenolic prepreg material is Beijing glass fiber reinforced plastic research institute Co. The material standard is GJB 3402-98.
The sixth specific implementation mode: the difference between this embodiment and one of the first to fifth embodiments is: the rubber is 46-3 ethylene propylene diene monomer rubber or 9621 rubber. The other is the same as one of the first to fifth embodiments.
In this embodiment, the material manufacturers of the 46-3 epdm rubber and the 9621 rubber are as follows: the material standard of 46-3 ethylene propylene diene monomer rubber is Q/Gn15-1995, and the material standard of 9621 rubber is GJB 1202-1991.
The seventh embodiment: the difference between this embodiment and one of the first to sixth embodiments is: and the fiber yarn in the third step is made of glass fiber, quartz fiber, carbon fiber or aramid fiber. The other is the same as one of the first to sixth embodiments.
The specific implementation mode is eight: the present embodiment differs from one of the first to seventh embodiments in that: the modified epoxy resin in the third step is a mixture of TDE-85 epoxy resin, 0617 epoxy resin and aromatic amine type epoxy curing agent according to the mass ratio of (60-70) to (40-30) to (50-60). The other is the same as one of the first to seventh embodiments.
The present embodiment 0617 is an epoxy resin purchased from southwestern star synthetic materials ltd.
The specific implementation method nine: the present embodiment differs from the first to eighth embodiments in that: and step three, winding in a longitudinal and circumferential alternate winding mode, and controlling the winding angle to be 10-90 degrees. The rest is the same as the first to eighth embodiments.
The detailed implementation mode is ten: the present embodiment differs from one of the first to ninth embodiments in that: and in the fourth step, the core-pulling die is demolded after natural cooling. The other is the same as one of the first to ninth embodiments.
The following examples were used to demonstrate the beneficial effects of the present invention:
the first embodiment is as follows:
the preparation method of the seal-head-free fiber reinforced resin matrix composite material combustion chamber shell for the rocket projectile comprises the following steps:
firstly, milling the surface of the outer ring of the metal ring to form a wire hanging table which is uniformly distributed to obtain a metal wire hanging ring; the material of the metal ring is 30 CrMnSiA; the outer diameter of the metal ring is 68mm, the wall thickness is 2mm, and the width is 60 mm; obtaining metal wire hanging rings by adopting a cross milling mode, wherein the total number of wire hanging tables on the surfaces of the metal wire hanging rings is 140, and the number of single-ring wire hanging tables is 28, and the total number of single-ring wire hanging tables is 5; the root part of the wire hanging table is prismatic, the side length is 2mm, the included angle of adjacent sides is 90 degrees, the height of the wire hanging table is 1mm, and the upward 'drawing' inclination is 3 degrees;
secondly, assembling the lining layer material and the metal wire hanging ring on the core mold to obtain an assembly part;
thirdly, putting the fiber yarn into the modified epoxy resin adhesive for gum dipping, and then winding the fiber yarn on the surface of the assembly part obtained in the second step to obtain a shell prefabricated part;
heating the shell prefabricated part to 90 ℃ and preserving heat for 2h, then heating to 120 ℃ and preserving heat for 2h, then heating to 150 ℃ and preserving heat for 6h, then cooling and demoulding by a core-pulling mould to obtain a combustion chamber shell, and finishing the preparation method of the end-enclosure-free fiber reinforced resin matrix composite combustion chamber shell for the rocket projectile;
the preparation method of the core mold in the second step comprises the following steps:
the method comprises the steps of winding a hemp rope on the outer surface of a core mold, controlling the winding tension of the hemp rope to be 40N and no gap between the hemp ropes, mixing gypsum and cement according to the mass ratio of 70: 30 to obtain mixed slurry, scraping the mixed slurry onto the surface of the core mold for winding the hemp rope, controlling the thickness of the mixed slurry to be 15mm, and drying to obtain the core mold.
The assembly method comprises the following steps:
mixing rubber serving as a lining layer material, then grinding the rubber into a rubber sheet layer with the thickness of 1.0mm, coating the rubber sheet layer on the surface of a core mold, wherein the number of the coating layers is 2, then respectively assembling two metal wire hanging rings at two ends of the core mold coated with the rubber sheet layer, and controlling the overlapping width of the metal wire hanging rings and the rubber sheet layer to be 10 mm; the rubber is 46-3 ethylene propylene diene monomer.
Step three, the fiber yarn is made of glass fiber; the modified epoxy resin is a mixture of TDE-85 epoxy resin, 0617 epoxy resin and aromatic epoxy curing agent in the mass ratio of 70 to 30 to 50.
And thirdly, winding in a longitudinal and circumferential alternate winding mode, wherein the longitudinal winding angle is controlled to be 10 degrees, and the circumferential winding angle is controlled to be 90 degrees.
The combustion chamber shell prepared by the embodiment has the performances of heat insulation, ablation resistance and scouring resistance; the explosion pressure of the shell can reach 30 MPa.
Example two:
the preparation method of the seal-head-free fiber reinforced resin matrix composite material combustion chamber shell for the rocket projectile comprises the following steps:
firstly, milling the surface of the outer ring of the metal ring to form a wire hanging table which is uniformly distributed to obtain a metal wire hanging ring; the material of the metal ring is 30 CrMnSiA; the outer diameter of the metal ring is 90mm, the wall thickness is 5mm, and the width is 60 mm; obtaining metal wire hanging rings by adopting a cross milling mode, wherein the total number of wire hanging tables on the surfaces of the metal wire hanging rings is 140, and the number of single-ring wire hanging tables is 28, and the total number of single-ring wire hanging tables is 5; the root part of the wire hanging table is prismatic, the side length is 2mm, the included angle of adjacent sides is 90 degrees, the height of the wire hanging table is 1mm, and the upward 'drawing' inclination is 3 degrees;
secondly, assembling the lining layer material and the metal wire hanging ring on the core mold to obtain an assembly part;
thirdly, putting the fiber yarn into the modified epoxy resin adhesive for gum dipping, and then winding the fiber yarn on the surface of the assembly part obtained in the second step to obtain a shell prefabricated part;
heating the shell prefabricated part to 90 ℃ and preserving heat for 2h, then heating to 120 ℃ and preserving heat for 2h, then heating to 150 ℃ and preserving heat for 6h, then cooling and demoulding by a core-pulling mould to obtain a combustion chamber shell, and finishing the preparation method of the end-enclosure-free fiber reinforced resin matrix composite combustion chamber shell for the rocket projectile;
the preparation method of the core mold in the second step comprises the following steps:
the method comprises the steps of winding a hemp rope on the outer surface of a core mold, controlling the winding tension of the hemp rope to be 40N and no gap between the hemp ropes, mixing gypsum and cement according to the mass ratio of 65: 35 to obtain mixed slurry, scraping the mixed slurry onto the surface of the core mold for winding the hemp rope, controlling the thickness of the mixed slurry to be 14mm, and drying to obtain a core mold.
The assembly method comprises the following steps:
mixing rubber serving as a lining layer material, then grinding the rubber into a rubber sheet layer with the thickness of 0.9mm, coating the rubber sheet layer on the surface of a core mold, wherein the number of the coating layers is 2, then respectively assembling two metal wire hanging rings at two ends of the core mold coated with the rubber sheet layer, and controlling the lapping width of the metal wire hanging rings and the rubber sheet layer to be 9 mm; the rubber is 9621 rubber.
Step three, the fiber yarn is made of carbon fiber; the modified epoxy resin is a mixture of TDE-85 epoxy resin, 0617 epoxy resin and aromatic amine type epoxy curing agent in a mass ratio of 70: 30: 50.
And thirdly, winding in a longitudinal and circumferential alternate winding mode, controlling the longitudinal winding angle to be 25 degrees and controlling the circumferential winding angle to be 90 degrees.
The combustion chamber shell prepared by the embodiment has the performances of heat insulation, ablation resistance and scouring resistance; the explosion pressure of the shell can reach 26 MPa.
Example three:
the preparation method of the seal-head-free fiber reinforced resin matrix composite material combustion chamber shell for the rocket projectile comprises the following steps:
firstly, milling the surface of the outer ring of the metal ring to form a wire hanging table which is uniformly distributed to obtain a metal wire hanging ring; the material of the metal ring is 30 CrMnSiA; the outer diameter of the metal ring is 120mm, the wall thickness is 5mm, and the width is 70 mm; obtaining metal wire hanging rings by adopting a cross milling mode, wherein the total number of wire hanging tables on the surfaces of the metal wire hanging rings is 112, and the number of single-ring wire hanging tables is 28, and the total number of the single-ring wire hanging tables is 4; the root part of the wire hanging table is prismatic, the side length is 2mm, the included angle of adjacent sides is 90 degrees, the height of the wire hanging table is 1mm, and the upward 'drawing' inclination is 2 degrees;
secondly, assembling the lining layer material and the metal wire hanging ring on the core mold to obtain an assembly part;
thirdly, putting the fiber yarn into the modified epoxy resin adhesive for gum dipping, and then winding the fiber yarn on the surface of the assembly part obtained in the second step to obtain a shell prefabricated part;
heating the shell prefabricated part to 90 ℃ and preserving heat for 2h, then heating to 120 ℃ and preserving heat for 2h, then heating to 150 ℃ and preserving heat for 6h, then cooling and demoulding by a core-pulling mould to obtain a combustion chamber shell, and finishing the preparation method of the end-enclosure-free fiber reinforced resin matrix composite combustion chamber shell for the rocket projectile;
the preparation method of the core mold in the second step comprises the following steps:
mixing 90% polyvinyl alcohol solution and river sand according to the mass ratio of 10: 90, then placing the mixture into a sand core mold forming mold, heating and curing at 100 ℃ for 10 hours, and demolding to obtain the core mold.
The assembly method comprises the following steps:
mixing rubber serving as a lining layer material, then grinding the rubber into a rubber sheet layer with the thickness of 1.0mm, carrying out die pressing on the metal wire hanging ring and the rubber sheet layer to obtain die-pressed pieces, and then respectively assembling the two die-pressed pieces to two ends of a mandrel through a positioning sleeve; coating the surface of the core mold with 2 layers of rubber sheets, lapping and laying the rubber sheets and the mold pressing pieces at two ends of the core mold, and controlling the lapping width to be 8 mm; the mould pressing process comprises the following steps: heating to 90 ℃, preserving heat for 1h, then heating to 110 ℃, preserving heat for 1h, and then heating to 150 ℃ and preserving heat for 4 h; the rubber is 46-3 ethylene propylene diene monomer.
Step three, the fiber yarn is made of carbon fiber; the modified epoxy resin is a mixture of TDE-85 epoxy resin, 0617 epoxy resin and aromatic amine type epoxy curing agent in a mass ratio of 70: 30: 50.
And thirdly, winding in a longitudinal and circumferential alternate winding mode, controlling the longitudinal winding angle to be 30 degrees and controlling the circumferential winding angle to be 90 degrees.
The combustion chamber shell prepared by the embodiment has the performances of heat insulation, ablation resistance and scouring resistance; the explosion pressure of the shell can reach 21 MPa.
Example four:
the preparation method of the seal-head-free fiber reinforced resin matrix composite material combustion chamber shell for the rocket projectile comprises the following steps:
firstly, milling the surface of the outer ring of the metal ring to form a wire hanging table which is uniformly distributed to obtain a metal wire hanging ring; the metal ring is made of TC 4; the outer diameter of the metal ring is 190mm, the wall thickness is 5mm, and the width is 70 mm; obtaining metal wire hanging rings by adopting a cross milling mode, wherein the total number of wire hanging platforms on the surfaces of the metal wire hanging rings is 70, and the number of single-ring wire hanging platforms is 14, and the total number of the single-ring wire hanging platforms is 5; the root part of the wire hanging table is prismatic, the side length is 2mm, the included angle of adjacent sides is 90 degrees, the height of the wire hanging table is 0.8mm, and the upward 'drawing' inclination is 2 degrees;
secondly, assembling the lining layer material and the metal wire hanging ring on the core mold to obtain an assembly part;
thirdly, putting the fiber yarn into the modified epoxy resin adhesive for gum dipping, and then winding the fiber yarn on the surface of the assembly part obtained in the second step to obtain a shell prefabricated part;
heating the shell prefabricated part to 90 ℃ and preserving heat for 2h, then heating to 120 ℃ and preserving heat for 2h, then heating to 150 ℃ and preserving heat for 6h, then cooling and demoulding by a core-pulling mould to obtain a combustion chamber shell, and finishing the preparation method of the end-enclosure-free fiber reinforced resin matrix composite combustion chamber shell for the rocket projectile;
the preparation method of the core mold in the second step comprises the following steps:
the method comprises the steps of winding a hemp rope on the outer surface of a core mold, controlling the winding tension of the hemp rope to be 40N and no gap between the hemp ropes, mixing gypsum and cement according to the mass ratio of 60: 40 to obtain mixed slurry, scraping the mixed slurry onto the surface of the core mold for winding the hemp rope, controlling the thickness of the mixed slurry to be 10mm, and drying to obtain the core mold.
The assembly method comprises the following steps:
the method comprises the following steps of (1) using high silica fiber cloth reinforced phenolic base prepreg as an inner lining material, carrying out die pressing on the high silica fiber cloth reinforced phenolic base prepreg and two metal wire hanging rings to obtain a cylindrical die pressing piece, wherein the two metal wire hanging rings are respectively positioned at two ends of the cylindrical die pressing piece, and then assembling the cylindrical die pressing piece onto a mandrel through a positioning sleeve; the mould pressing process comprises the following steps: raising the temperature to 140 ℃, and preserving the temperature for 6 h.
Step three, the fiber yarn is made of carbon fiber; the modified epoxy resin is a mixture of TDE-85 epoxy resin, 0617 epoxy resin and aromatic amine type epoxy curing agent in a mass ratio of 70: 30: 50.
And thirdly, winding in a longitudinal and circumferential alternate winding mode, controlling the longitudinal winding angle to be 45 degrees and controlling the circumferential winding angle to be 90 degrees.
The combustion chamber shell prepared by the embodiment has the performances of heat insulation, ablation resistance and scouring resistance; the explosion pressure of the shell can reach 12 MPa.
Claims (9)
1. A preparation method of a head-free fiber reinforced resin matrix composite material combustion chamber shell for a rocket projectile is characterized by comprising the following steps:
firstly, milling the surface of the outer ring of the metal ring to form a wire hanging table which is uniformly distributed to obtain a metal wire hanging ring; the root part of the wire hanging table is prismatic, the side length is 1-2 mm, the included angle of adjacent sides is 45-90 degrees, the height of the wire hanging table is 0.5-1 mm, and the upward 'drawing' inclination is 1-3 degrees;
secondly, assembling the lining layer material and the metal wire hanging ring on the core mold to obtain an assembly part;
thirdly, putting the fiber yarn into the modified epoxy resin adhesive for gum dipping, and then winding the fiber yarn on the surface of the assembly part obtained in the second step to obtain a shell prefabricated part;
heating the shell prefabricated part to 90-100 ℃, preserving heat for 1-2 hours, then heating to 110-120 ℃, preserving heat for 1-2 hours, then heating to 150-160 ℃, preserving heat for 4-6 hours, then cooling and demolding to obtain a combustion chamber shell, and completing the preparation of the seal-head-free fiber reinforced resin matrix composite combustion chamber shell for the rocket projectile;
the assembly method comprises the following steps:
mixing rubber serving as a lining layer material, then grinding the rubber into a rubber sheet layer with the thickness of 0.5-1.0 mm, coating the rubber sheet layer on the surface of a core mold, wherein the number of the coating layers is 2-3, then respectively assembling two metal wire hanging rings at two ends of the core mold coated with the rubber sheet layer, and controlling the lap joint width of the metal wire hanging rings and the rubber sheet layer to be 5-10 mm;
or taking rubber as the material of the inner liner, mixing the rubber, then grinding the rubber into a rubber sheet layer with the thickness of 0.5-1.0 mm, carrying out die pressing on the metal wire hanging ring and the rubber sheet layer to obtain die pressing pieces, and then respectively assembling the two die pressing pieces to the two ends of the core die through the positioning sleeves; coating the surface of the core mold with 2-3 coating layers by using a rubber sheet layer, and lapping and laying the rubber sheet layer and the mold pressing pieces at two ends of the core mold, wherein the lapping width is controlled to be 5-10 mm; the mould pressing process comprises the following steps: heating to 90-100 ℃, preserving heat for 1-2 h, then heating to 110-120 ℃, preserving heat for 1-2 h, then heating to 150-160 ℃, preserving heat for 4-6 h;
or taking the high silica fiber cloth reinforced phenolic base prepreg as an inner lining material, carrying out die pressing on the high silica fiber cloth reinforced phenolic base prepreg and two metal wire hanging rings to obtain a cylindrical die pressing piece, wherein the two metal wire hanging rings are respectively positioned at two ends of the cylindrical die pressing piece, and then assembling the cylindrical die pressing piece on a core die through a positioning sleeve; the mould pressing process comprises the following steps: heating to 140-180 ℃, and preserving heat for 3-6 h.
2. The method for preparing the seal-head-free fiber reinforced resin matrix composite combustor casing for the rocket projectile according to claim 1, wherein in the step one, the metal ring is made of 30CrMnSiA or TC 4; the outer diameter of the metal ring is 68-200 mm, the wall thickness is 2-5 mm, and the width is 30-80 mm.
3. The preparation method of the seal-head-free fiber reinforced resin matrix composite combustor casing for the rocket projectile according to claim 1, wherein the metal wire hanging rings are obtained in a cross milling mode in the first step, the total number of wire hanging tables on the surfaces of the metal wire hanging rings is 42-140, and the number of single-ring wire hanging tables is 14-28 and is 3-5.
4. The method for preparing the cap-free fiber reinforced resin matrix composite combustor casing for the rocket projectile according to claim 1, wherein the method for preparing the core mold in the second step comprises the following steps:
mixing a polyvinyl alcohol solution with the mass concentration of 80-95% and river sand according to the mass ratio of (10-20) to (90-80), then placing the mixture into a sand core mold forming mold, heating and curing the mixture at the curing temperature of 100-120 ℃ for 6-10 h, and demolding to obtain a core mold;
or winding the hemp rope on the outer surface of the core mold, controlling the winding tension of the hemp rope to be 40N and no gap between the hemp ropes, mixing gypsum and cement according to the mass ratio of (60-70) to (40-30) to obtain mixed slurry, scraping the mixed slurry onto the surface of the core mold for winding the hemp rope, controlling the thickness of the mixed slurry to be 10-15 mm, and drying to obtain the core mold.
5. The method for preparing the seal-head-free fiber reinforced resin matrix composite material combustion chamber shell for the rocket projectile according to claim 1, wherein the rubber is 46-3 ethylene propylene diene monomer rubber or 9621 rubber.
6. The method for preparing the seal-head-free fiber reinforced resin matrix composite combustor casing for the rocket projectile according to claim 1, wherein the fiber yarn in the third step is made of glass fiber, quartz fiber, carbon fiber or aramid fiber.
7. The preparation method of the seal-head-free fiber reinforced resin matrix composite combustor casing for the rocket projectile according to claim 1, wherein the modified epoxy resin in the third step is a mixture of TDE-85 epoxy resin, 0617 epoxy resin and an aromatic amine type epoxy curing agent in a mass ratio of (60-70) to (40-30) to (50-60).
8. The method for preparing the seal-head-free fiber reinforced resin matrix composite combustor casing for the rocket projectile according to claim 1, wherein the third step is to wind in a longitudinal and circumferential alternate winding manner, and the winding angle is controlled to be 10-90 °.
9. The preparation method of the seal-head-free fiber reinforced resin matrix composite combustion chamber shell for the rocket projectile according to claim 1, wherein the step four is to demold the shell by a core-pulling die after natural cooling.
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| CN113250858A (en) * | 2021-04-21 | 2021-08-13 | 西安英利科电气科技有限公司 | Winding structure and method for large-opening solid rocket combustion chamber |
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