CN115898695A - Heat insulation layer structure of solid rocket engine combustion chamber and bonding method thereof - Google Patents
Heat insulation layer structure of solid rocket engine combustion chamber and bonding method thereof Download PDFInfo
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- CN115898695A CN115898695A CN202310220610.1A CN202310220610A CN115898695A CN 115898695 A CN115898695 A CN 115898695A CN 202310220610 A CN202310220610 A CN 202310220610A CN 115898695 A CN115898695 A CN 115898695A
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Abstract
The invention discloses a heat insulation layer structure of a combustion chamber of a solid rocket engine and an adhesion method thereof, belonging to the technical field of solid rocket engines. The heat insulating layer structure includes: the front seal head heat insulation layer and the rear seal head heat insulation layer are respectively bonded to the front seal head part and the rear seal head part of the combustion chamber shell; the transition section heat insulation layer is bonded in the combustion chamber shell, and one end of the transition section heat insulation layer is lapped with the front end enclosure heat insulation layer; the ablation section heat insulation layer is bonded in the combustion chamber shell, one end of the ablation section heat insulation layer is in lap joint with the transition section heat insulation layer, and the other end of the ablation section heat insulation layer is in lap joint with the rear end socket heat insulation layer; the composite heat insulation layer is bonded to the surface of the rear end socket heat insulation layer; and the front artificial debonding layer and the rear artificial debonding layer are respectively bonded to the surface of the front end enclosure heat insulation layer and the surface of the ablation section heat insulation layer. The thermal insulation layer structure is used for a solid rocket engine combustion chamber with the length-diameter ratio larger than 15.
Description
Technical Field
The invention relates to the technical field of solid rocket engines, in particular to a solid rocket engine combustion chamber heat insulation layer structure and an adhesion method thereof.
Background
The heat insulation layer is an important part of the combustion chamber of the solid rocket engine, has the functions of ablation resistance and heat prevention, protects the shell of the combustion chamber from being burnt through or the strength of the shell of the combustion chamber is reduced after being heated, and also has the function of buffering the bonding stress between the explosive columns and the shell in the wall-attached pouring structure of some explosive columns.
With the technical development of solid rocket engines, especially the demand of rocket projectiles is gradually increased year by year, the requirements of large-batch power devices are more and more emphasized on the control and reduction of production cost on the premise of ensuring the product quality, wherein for medium-long distance rocket projectiles, in order to reduce the manufacturing cost, the design structure of a combustion chamber is generally concentrated in the direction of large length-diameter ratio, and new requirements on the ablation performance, scouring resistance and large overload resistance of a local heat insulation layer are provided.
The publication No. CN104960200A entitled "a method for sticking rubber-based heat insulating layer" proposes a method for assisting adhesion by using a silicon rubber air bag, wherein the front opening and the rear opening of an engine are narrow, the diameter of the engine is long, and an operator cannot enter a combustion chamber to operate, but the length-diameter ratio of the combustion chamber in the method and the example application is less than 7, the thickness of the heat insulating layer is thicker, the operation difficulty is not great to a certain extent, the structural design of the heat insulating layer of the combustion chamber is simpler, the forming is easy, and the risk of deformation and pleating exists when the air bag is used for assisting the heat insulating layer with the thickness of less than 1 mm.
For a combustion chamber of a solid rocket engine with a front and back closing-up structure of a combustion chamber shell and a length-diameter ratio larger than 15, particularly for a combustion chamber with a diameter of less than 400, a heat insulation layer is of a through-pasting structure, the thickness of the heat insulation layer with a local larger range is smaller than 1mm, an operator cannot enter the indoor operation at all, and the heat insulation layer with the thickness of less than 1mm is easy to deform in the pasting process by adopting the assistance of an air bag to cause thickness deviation and even thin.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a heat insulation layer structure of a combustion chamber of a solid rocket engine and a bonding method thereof. The technical scheme is as follows:
in one aspect, there is provided a solid rocket engine combustion chamber insulation structure, the insulation structure comprising:
the front end enclosure heat insulation layer and the rear end enclosure heat insulation layer are respectively bonded to the front end enclosure part and the rear end enclosure part of the combustion chamber shell;
the transition section heat insulation layer is bonded in the combustion chamber shell, and one end of the transition section heat insulation layer is lapped with the front end socket heat insulation layer;
the ablation section heat insulation layer is bonded in the combustion chamber shell, one end of the ablation section heat insulation layer is in lap joint with the transition section heat insulation layer, and the other end of the ablation section heat insulation layer is in lap joint with the rear end socket heat insulation layer;
the composite heat insulation layer is bonded on the surface of the rear end socket heat insulation layer;
and the front artificial debonding layer and the rear artificial debonding layer are respectively bonded to the surface of the front end enclosure heat insulation layer and the surface of the ablation section heat insulation layer.
Further, the ablative segment thermal insulation layer comprises: the ablation performance of the bottom layer insulating layer is higher than that of the surface layer insulating layer;
the bottom layer insulating layer is of one or more layers and is adhered in the combustion chamber shell, and the surface layer insulating layer is adhered to the surface of the bottom layer insulating layer;
the post-artificial debonding layer is bonded to the surface of the surface insulating layer;
the composite heat insulation layer is a carbon fiber composite heat insulation layer structure and comprises a plurality of layers, and each layer is divided into 6 to 8 petals.
Further, the thickness of the heat insulation layer of the front end socket and the heat insulation layer of the rear end socket is 4 to 5mm;
the thickness of the heat insulation layer of the transition section is less than 1mm, the length of the heat insulation layer of the transition section is 2000-4500 mm, a circumferential circle of thickened areas are arranged every 700-800mm, a reinforcing platform is formed, the width of the reinforcing platform is 20-50mm, and the thickness of the reinforcing platform is 2-3mm;
the thickness of the heat insulating layer of the ablation section is more than 5mm, and the thickness of the insulating layer of the surface layer is 1 to 2mm;
the thickness of the composite heat insulation layer is not less than 6mm;
the thickness of the front artificial debonding layer and the thickness of the rear artificial debonding layer are 2-3 mm.
In another aspect, there is provided a bonding method of a thermal insulation layer structure of a combustion chamber of a solid rocket motor, the bonding method comprising:
s1: pretreating the combustion chamber shell;
s2: preparing a front end enclosure heat insulation layer, a rear end enclosure heat insulation layer, a transition section heat insulation layer, an ablation section heat insulation layer, a composite heat insulation layer, a front artificial debonding layer and a rear artificial debonding layer;
s3: respectively bonding the prepared front seal head heat insulation layer and the prepared rear seal head heat insulation layer to a front seal head part and a rear seal head part of a combustion chamber shell;
s4: bonding the heat insulating layer of the transition section to the inner wall of the shell of the combustion chamber, wherein one end of the heat insulating layer of the transition section is lapped with the heat insulating layer of the front end enclosure;
s5: then the ablation section heat insulation layer and the composite heat insulation layer are bonded, one end of the ablation section heat insulation layer is in lap joint with the transition section heat insulation layer, the other end of the ablation section heat insulation layer is in lap joint with the rear end socket heat insulation layer, and the composite heat insulation layer is positioned on the surface of the rear end socket heat insulation layer;
s6: finally, respectively bonding the front manual debonding layer and the rear manual debonding layer to the surface of the front end socket heat insulation layer and the surface of the ablation section heat insulation layer to form a heat insulation layer structure of the combustion chamber of the solid rocket engine;
s7: vulcanizing the solid rocket engine combustion chamber heat insulating layer structure.
Further, the S1 includes:
carrying out sand blowing treatment on the inner surface of the combustion chamber shell by adopting 16-24 meshes of brown corundum or quartz sand under the air pressure of 0.4-0.6 MPa, then removing floating dust on the inner surface of the combustion chamber shell, cleaning and airing, and brushing and coating an adhesive primer on an adhesive surface for later use.
Further, the S2 includes:
after the rubber insulating layer is filled into a mold, the mold is pressed on a flat vulcanizing machine at 80 to 85 ℃ for 80 to 150kg/cm 2 Keeping the temperature for 2 to 3 hours, and polishing after pressing to obtain the heat insulation layer of the front end socket and the heat insulation layer of the rear end socket;
splicing a plurality of rubber heat insulation layers according to the molded surfaces of the transition sections to form the heat insulation layers of the transition sections and a plurality of reinforcing platforms;
according to the profile of the ablation section, adopting a mould to press and form, wherein the pressing temperature is 80-85 ℃, and the pressure is 80-150kg/cm 2 Keeping the temperature for 2 to 3h to obtain a bottom insulating layer and a surface insulating layer which form the ablation section heat insulating layer, wherein the ablation performance of the bottom insulating layer is higher than that of the surface insulating layer;
designing a molded surface according to the composite heat insulating layer at the rear end socket part, and pressing the composite heat insulating layer by adopting a male and female die, wherein the pressing temperature is 50-60 ℃, and the pressure is 100-300 kg/cm 2 The heat preservation time is 1-3 h, the composite heat insulation layer is multilayer, and each layer is divided into 6 to 8 petals;
after the rubber insulating layer is filled into a mold, pressurizing 100-150kg/cm on a flat vulcanizing machine at the temperature of 150-160 DEG C 2 Preserving heat for 1-2 h, and polishing the bonding surface after pressing to obtain the front manual debonding layer and the rear manual debonding layer;
the rubber insulating layer is a nitrile rubber insulating layer or an ethylene propylene diene monomer insulating layer.
Further, the S4 includes: brushing an adhesive on the bonding surface of the heat insulating layer of the transition section, winding the bonding surface on the surface of an auxiliary bonding tool, isolating the bonding surface by using polytetrafluoroethylene varnished cloth, putting the auxiliary bonding tool into a combustion chamber shell, taking the end surface of the heat insulating layer of a front end socket as a positioning reference, simultaneously rotating the combustion chamber shell and unfolding the auxiliary bonding tool to bond the heat insulating layer of the transition section at a corresponding position on the inner wall of the combustion chamber shell, finally taking out the auxiliary bonding tool, and compacting;
the auxiliary bonding tool is a cylindrical barrel-shaped tool or a tapered cylindrical barrel-shaped tool.
Further, when the underlying insulating layer is a one-layer structure, the S5 includes:
the bottom layer insulating layer is adhered in the combustion chamber shell, and the front and the rear of the bottom layer insulating layer are respectively lapped with the transition section insulating layer and the rear end socket insulating layer;
cleaning the surface of the first layer of composite heat insulation layer, adhering the first layer of composite heat insulation layer to the surface of the heat insulation layer of the rear end socket, performing butt joint treatment between every two sections of the first layer of composite heat insulation layer, and then performing hot pressing;
cleaning the surface of the second layer of composite heat insulation layer, then sticking the second layer of composite heat insulation layer to the surface of the first layer of composite heat insulation layer, and sticking the composite heat insulation layer to the required thickness by analogy, wherein a heat insulation layer adhesive tape with the thickness of 1-2 mm is arranged at the butt joint gap of each section of composite heat insulation layer (5);
bonding the surface insulating layer on the surface of the bottom insulating layer, and hot-pressing;
when the underlying insulating layer is a multilayer structure, the S5 includes:
adhering a first layer of the bottom insulating layer in a combustion chamber shell, and respectively overlapping the front and the back of the first layer of the bottom insulating layer with a transition section insulating layer and a back end enclosure insulating layer;
cleaning and wiping the surface of the first layer of composite heat insulation layer, adhering the first layer of composite heat insulation layer to the surface of the heat insulation layer of the rear end enclosure, performing butt joint treatment on each section of the first layer of composite heat insulation layer, and then performing hot pressing;
adhering a second bottom insulating layer to the surface of the first bottom insulating layer;
cleaning and wiping the surface of the second layer of composite heat insulation layer, then sticking the second layer of composite heat insulation layer on the surface of the first layer of composite heat insulation layer, carrying out butt joint treatment between every two sections of composite heat insulation layers, placing a heat insulation layer adhesive tape with the thickness of 1-2 mm between every two sections of second layer of composite heat insulation layers to ensure the integrity of the whole profile structure and no gap, and then carrying out hot pressing;
repeating the step S5 until the thicknesses of the bottom layer insulating layer and the composite heat insulating layer meet the requirements;
bonding the surface insulating layer on the surface of the bottom insulating layer on the uppermost layer, and hot-pressing;
wherein the hot pressing condition is that the temperature is 80 to 90 ℃, the pressure is 0.7 to 0.9MPa, and the heat preservation is carried out for 1 to 3 hours.
Further, the sulfurization in S7 includes:
assembling the air bag and the tool in place, heating the room temperature to 90-100 ℃ within 2-3 h, preserving heat for 1-2h, heating the room temperature to 120-130 ℃ within 1-h, preserving heat for 2-3h, heating the room temperature to 160-170 ℃ within 2-3h, preserving heat for 3-5 h, and naturally cooling the room temperature after the heat preservation is finished; the whole vulcanization pressure is 0.8-0.9 MPa.
Further, the bonding method is used for bonding the heat insulating layer of the combustion chamber of the solid rocket motor, and the length-diameter ratio of the heat insulating layer is larger than 15.
The technical scheme provided by the embodiment of the invention has the following beneficial effects: the solid rocket engine combustion chamber heat insulation layer structure and the bonding method are used for a solid rocket engine combustion chamber with the length-diameter ratio larger than 15, the auxiliary manual bonding tool or the mechanical automatic bonding tool is used for realizing the integral bonding molding of the heat insulation layer at the transition section with the thickness of less than 1mm, compared with the segmentation and split bonding, the solid rocket engine combustion chamber heat insulation layer structure has the characteristics of high reliability and good consistency, and the production efficiency is improved by at least 5 times; in addition, when the composite heat insulating layer is bonded, a process of integrated vulcanization molding of a mold is adopted, so that the interface bonding effect and the quality reliability are high compared with multiple times of vulcanization molding, and the molding period is shortened from the original 6 days to 3 days.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic view of the structure of the insulating layer of the combustion chamber of a solid rocket engine according to a second embodiment of the present invention;
FIG. 2 is an enlarged view of a portion of FIG. 1 at A;
FIG. 3 is an enlarged view of a portion of FIG. 1 at B;
FIG. 4 is a schematic view of the structure of the insulating layer of the combustion chamber of the solid rocket engine according to a third embodiment of the present invention;
FIG. 5 is an enlarged view of a portion of FIG. 4 at C;
FIG. 6 is an enlarged view of a portion of FIG. 4 at D;
reference numerals: 1-heat insulating layer of front end enclosure; 2-heat insulating layer of the rear end socket; 3-a transition section heat insulating layer; 4-ablation of the segment insulation layer; 5-composite heat insulating layer; 6-manually removing the adhesive layer; 7-manual debonding of the adhesive layer.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail with reference to the accompanying drawings.
Example one
A solid rocket engine combustion chamber heat insulation layer structure comprises a front end socket heat insulation layer 1, a rear end socket heat insulation layer 2, a transition section heat insulation layer 3, an ablation section heat insulation layer 4, a composite heat insulation layer 5, a front artificial debonding layer 6 and a rear artificial debonding layer 7.
The heat insulation layer 1 of the front end socket and the heat insulation layer 2 of the rear end socket are respectively bonded to the front end socket part and the rear end socket part of the combustion chamber shell, and the thickness of the heat insulation layer 1 of the front end socket and the thickness of the heat insulation layer 2 of the rear end socket are 4-5 mm; the transition section heat insulation layer 3 is bonded in a combustion chamber shell, one end of the transition section heat insulation layer 3 is overlapped with the front end socket heat insulation layer 1, the ablation amount of the transition section heat insulation layer 3 is smaller, the thickness of the transition section heat insulation layer 3 is smaller than 1mm, the length of the transition section heat insulation layer is 2000-4500 mm, a circumferential circle of thickened areas are arranged every 700-800mm to form a reinforced platform, the width of the reinforced platform is 20-50 mm, the thickness of the reinforced platform is 2-3 mm, the purpose of the thickened areas is a process overlapping section, meanwhile, a chemical pouring column stress releasing area is also provided, the transition section heat insulation layer is taken out and spliced according to the size requirement, the length of the overlapping part is controlled to be 20-30 mm, and is compacted by a roller to ensure firm bonding; wherein, a cylindrical barrel-shaped tool or a tapered cylindrical barrel-shaped tool (auxiliary bonding tool for transition section) is required to be prepared for the heat-insulating layer 3 of the transition section during bonding according to the profile of the transition section, and the weight is reduced for convenient operation, or a movable, movable and automatically-rotating long-arm mechanical shaft (automatic mechanical laying device for transition section) is processed for auxiliary bonding of the heat-insulating layer of the transition section; in addition, if the heat insulating layer 3 at the transition section is of a structure with gradually changed thickness, the molded surface of the auxiliary bonding tool also needs to be processed into a matched molded surface; the transition section auxiliary bonding tool can be made of high-hardness paper tubes, stainless steel tubes, plastic tubes and the like.
The ablation section heat-insulating layer 4 is adhered in the combustion chamber shell, one end of the ablation section heat-insulating layer 4 is in lap joint with the transition section heat-insulating layer 3, the other end of the ablation section heat-insulating layer 4 is in lap joint with the rear end heat-insulating layer 2, the ablation section heat-insulating layer 4 is generally distributed at a distance of 500-1500 mm from the rear end of the combustion chamber shell, the exposure time of the heat-insulating layer at the position is longest in the working process of an engine, the ablation is serious, the requirement on the ablation performance of the heat-insulating layer material at the position is higher, the linear ablation rate and the mass ablation rate are generally not more than 0.05mm/s and 0.04g/s (oxygen-acetylene test), the rubber heat-insulating layer capable of meeting the performance generally has higher hardness, the elongation is smaller, and the material cost is also high; therefore, in order to comprehensively consider the requirements of the reliability and the cost of the product, the heat insulation layer of the ablation section is divided into two heat insulation layers with different performances and the same base body, wherein the two heat insulation layers are respectively a bottom insulation layer close to the shell of the combustion chamber and a surface insulation layer attached to the explosive column, the bottom insulation layer is made of materials with high hardness and high ablation performance, for example, an ablation type ethylene propylene diene monomer heat insulation layer and an ablation type nitrile butadiene rubber heat insulation layer with the linear ablation rate of 0.02-0.05mm/s and the mass ablation rate of 0.03-0.05g/s, the safety and the reliability of the product in the combustion process of the explosive column are ensured, the surface insulation layer is made of soft heat insulation layers with high elongation and low hardness, and can be consistent with the heat insulation layer of the transition section, for example, the ordinary type ethylene propylene diene monomer heat insulation layer and the ordinary nitrile butadiene rubber heat insulation layer with the linear ablation rate of 0.1-0.15mms/s and the mass ablation rate of 0.08-0.12 g/s; the total thickness of the heat insulating layer 4 in the ablation section is more than 5mm, the thickness of the surface insulating layer is 1 to 2mm, the bottom heat insulating layer is one or more, the thickness is thicker, the process of preforming the manual paster of the latter by a mold is generally adopted to prepare according to the design size, the lap joint structure between the heat insulating layer 3 in the transition section and the heat insulating layer at the bottom layer needs to be considered, and the heat insulating layer at the bottom layer can be formed by one-step pressing by the mold in order to improve the production efficiency.
The composite heat insulation layer 5 is bonded on the surface of the heat insulation layer 2 of the rear end enclosure, the exposure time of the part is longest, ablation erosion resistance and overload are the most serious, a carbon fiber composite heat insulation layer structure is generally adopted, wherein the thickness of a carbon fiber material is not less than 6mm, in the application, a carbon fiber-butyronitrile phenolic aldehyde soft sheet (carbon wool board for short) is taken as a research object, a molded surface is designed according to the composite heat insulation layer of the rear end enclosure part, the dried carbon wool board is pressed and molded by adopting a male and female die, a certain thickness and equal division of 6 to 8 sections are obtained, the molded surface is convenient to be matched with and bonded with the molded surface of the heat insulation layer 2 of the rear end enclosure, and multiple layers are generally required to be bonded; the thicknesses of the front artificial debonding layer 6 and the rear artificial debonding layer 7 are 2-3 mm, the front artificial debonding layer 6 is adhered to the surface of the front end socket heat insulation layer 1, and the rear artificial debonding layer 7 is adhered to the surface of the surface layer heat insulation layer.
The solid rocket engine combustion chamber heat insulation layer structure is used for a solid rocket engine combustion chamber with the length-diameter ratio larger than 15, the ablation section heat insulation layer adopts a bottom layer insulation layer and a surface layer insulation layer which are combined by two soft materials and hard materials, the bonding effect with a grain can be better obtained, the ablation resistance and scouring resistance requirements of materials are met, and the design thickness of the heat insulation layer can be effectively reduced through decomposing the heat insulation layer structure into structures with the same base body and different properties, so that the material cost is reduced, and the cost can be reduced by more than 12%; in addition, the composite heat insulation layer is of a carbon fiber composite heat insulation layer structure, and a split multilayer structure is adopted, so that the bonding quality is reliable and high.
Example two
Referring to fig. 1 to 3, the diameter of a solid rocket engine combustion chamber shell is 365mm, the length is 6000mm, and the length-diameter ratio is about 17.8, and the bonding method of the solid rocket engine combustion chamber heat insulation layer structure comprises the following steps:
a step (101): carrying out sand blowing treatment on the inner surface of the combustion chamber shell by adopting 16-mesh brown corundum under the air pressure of 0.4MPa, then removing dust, cleaning the bonding surface by using ethyl acetate, and brushing the bonding primer on the bonding surface after drying.
A step (102): pressing a front end socket heat insulation layer 1 and a rear end socket heat insulation layer 2 by using a die, filling the common nitrile rubber heat insulation layer into the die, and pressurizing 100kg/cm on a flat vulcanizing machine at 80 DEG C 2 And preserving heat for 2h, polishing the bonding surfaces of the preformed front end socket heat-insulating layer 1 and the preformed rear end socket heat-insulating layer 2 by using a file after the pressing is finished, and then wiping the bonding surfaces by using ethyl acetate for standby to obtain the front end socket heat-insulating layer 1 and the rear end socket heat-insulating layer 2 with the thicknesses of 5 mm.
Step (103): preparing a common nitrile rubber heat insulation layer with the thickness of 0.8mm, and completing splicing of the heat insulation layer 3 of the transition section according to the drawing size and the lap joint requirement, wherein the thickness of the heat insulation layer 3 of the transition section is 0.8mm, the length of the heat insulation layer is 4500mm, a reinforcing platform is arranged at the interval of 800mm, the length of the heat insulation layer is 30mm, and the thickness of the heat insulation layer is 2mm; and preparing an auxiliary bonding tool, wherein the molded surface of the transition section is cylindrical, and a paper tube with the diameter of 100mm is adopted, and the length of the paper tube is about 5500mm.
A step (104): according to the requirement of ablation section thickness of 6mm, the heat-insulating material can be decomposed into a bottom heat-insulating layer of 4mm and a surface heat-insulating layer of 2mm, wherein the bottom heat-insulating layer of 4mm is made of an ablation nitrile rubber heat-insulating layer, and is formed by one-step pressing by adopting a die, the pressing temperature is 80 ℃, and the pressure is 80kg/cm 2 The surface layer heat insulation layer material with the heat preservation time of 2h and 2mm is a common nitrile rubber heat insulation layer.
A step (105): the carbon wool board in the composite heat insulating layer 5 has a thickness of 6mm and can be divided into 2 layers and 3mm, the prepared carbon wool boards are respectively laid in a mould cavity and are pressed and formed on a flat vulcanizing machine, the pressing process is carried out at a temperature of 50 ℃ and under a pressure of 100kg/cm 2 And keeping the temperature for 1h to finish the pressing of the two heat insulating layers of the carbon wool boards.
Step (106): preparing a front artificial debonding layer 6 and a rear artificial debonding layer 7, filling a common nitrile rubber heat insulating layer into a mold, and pressurizing 100kg/cm on a flat vulcanizing machine at 160 DEG C 2 And preserving the heat for 1h to obtain a front artificial debonding layer 6 and a rear artificial debonding layer 7 with the thickness of 2 mm.
A step (107): and brushing an adhesive on the bonding surfaces of the combustion chamber shell and the front end enclosure heat-insulating layer 1 and the rear end enclosure heat-insulating layer 2, then respectively bonding the front end enclosure heat-insulating layer 1 and the rear end enclosure heat-insulating layer 2 on the front end enclosure part and the rear end enclosure part of the combustion chamber shell, and compacting.
Step (108): the adhesive is brushed on the bonding surface of the transition section heat insulation layer 3, then the transition section heat insulation layer is wound on a cylindrical barrel-shaped tool and is isolated by polytetrafluoroethylene varnished cloth, then the cylindrical barrel-shaped tool is placed in the combustion chamber shell, the end face of the front end socket heat insulation layer is used as a positioning reference, the combustion chamber shell is rotated and the cylindrical barrel-shaped tool is unfolded simultaneously, so that the transition section heat insulation layer 3 is bonded at the corresponding position of the inner wall of the combustion chamber shell, and finally the cylindrical barrel-shaped tool is taken out, compacted, firmly bonded and not fallen off.
Step (109): and brushing an adhesive on the bonding surface of the bottom insulating layer of the erosion section, bonding the bottom insulating layer of the erosion section at a corresponding position in the combustion chamber shell, respectively overlapping the front and the back with the transition section insulating layer 3 and the back end socket insulating layer 2, and compacting in place by using a roller.
A step (110): and (3) adhering the first layer of the composite heat-insulating layer 5, wiping the surface of the prepared carbon wool board heat-insulating layer with ethyl acetate, drying, brushing an adhesive on the adhering surface (including the side surface) of the carbon wool board and the surface of the rear end enclosure heat-insulating layer adhered with the adhering surface, adhering the carbon wool board to the corresponding position on the surface of the rear end enclosure heat-insulating layer 2, performing butt joint treatment between every two sections, and compacting by hands to ensure that the adhering is firm.
Step (111): after the work is finished, the surface of the heat insulation layer is checked to have no foreign matters, the sticking is firm, the air bag and the tool are assembled in place, and the heat is preserved for 1 hour in an oven at the temperature of 80 ℃ and under the pressure of 0.7 MPa.
Step (112): and (3) adhering a second layer of the composite heat-insulating layer 5, wiping the surface of the prepared second layer of the heat-insulating layer of the carbon wool board with ethyl acetate, airing, brushing an adhesive on the adhering surface (including the side surface) of the second layer of the carbon wool board and the surface of the first layer of the carbon wool board adhered with the adhering surface, adhering the second layer of the carbon wool board to the corresponding position on the surface of the first layer of the carbon wool board, performing butt joint treatment between the petals, compacting by hands to firmly adhere the carbon wool board, placing a heat-insulating layer adhesive tape with the thickness of 1-2 mm at the butt joint gap of each petal of the carbon wool boards, and performing hot pressing by the method in the step (111).
Step (113): and (5) brushing an adhesive on the surface of the prepared surface heat-insulating layer, the surface of the bottom heat-insulating layer adhered to the surface of the prepared surface heat-insulating layer and the surface of the carbon wool board, then finishing the adhesion of the surface heat-insulating layer, and carrying out hot pressing by the method in the step (111).
Step (114): and respectively bonding the front artificial debonding layer 6 and the rear artificial debonding layer 7 to the surface of the front end socket heat insulation layer 1 and the surface of the surface layer heat insulation layer to form the heat insulation layer structure of the combustion chamber of the solid rocket engine.
Step (115): vulcanizing, checking that no foreign matter exists on the surface of the heat insulating layer after the work is finished, firmly sticking, assembling the air bag and the tool in place, heating the room temperature to 90 ℃ after 2 hours, preserving the heat for 1 hour, heating the room temperature to 120 ℃ after 1 hour, preserving the heat for 2 hours, heating the room temperature to 160 ℃ after 2 hours, preserving the heat for 3 hours, and naturally cooling the room temperature after the heat preservation is finished; the whole vulcanization pressure was 0.8MPa.
Step (116): and after the curing is finished, dismantling the tool, and carrying out size, thickness and interface inspection. The heat insulation layer has complete profile, no bulge, qualified size, qualified thickness and qualified ultrasonic flaw detection of the bonding interface.
EXAMPLE III
Referring to fig. 4 to 6, the diameter of a shell of a combustion chamber of a solid rocket engine is 295mm, the length is 5500mm, and the length-diameter ratio is about 18.6, and the bonding method of the heat insulation layer structure of the combustion chamber of the solid rocket engine comprises the following steps:
a step (201): and (3) carrying out sand blowing treatment on the inner surface of the combustion chamber shell by adopting 24-mesh quartz sand under the air pressure of 0.6MPa, then carrying out dust removal, cleaning the bonding surface by using acetone, and brushing the bonding primer on the bonding surface after drying.
Step (202): pressing a front end socket heat insulation layer 1 and a rear end socket heat insulation layer 2 by using a die, filling the common ethylene propylene diene monomer rubber heat insulation layer into the die, and pressurizing 150kg/cm on a flat vulcanizing machine at 85 DEG C 2 And preserving heat for 3 hours, polishing the bonding surfaces of the preformed front end socket heat insulation layer 1 and the preformed rear end socket heat insulation layer 2 by using a file after pressing is finished, and then wiping the bonding surfaces by using ethyl acetate for standby to obtain the front end socket heat insulation layer 1 and the rear end socket heat insulation layer 2 with the thickness of 4 mm.
Step (203): preparing a common ethylene propylene diene monomer rubber heat insulation layer with the thickness of 0.6mm, completing splicing of a transition section heat insulation layer 3 according to the drawing size and the lap joint requirement, wherein the thickness of the transition section heat insulation layer 3 is 0.6mm, the length of the transition section heat insulation layer is 3000mm, a reinforcing platform is arranged at the interval of 700mm, the length of the reinforcing platform is 30mm, the thickness of the reinforcing platform is 2mm, and meanwhile, a heat insulation layer adhesive tape with the width of 0.8mm and the width of 30mm is stuck at the reinforcing platform; and (3) preparing an auxiliary bonding tool, wherein the molded surface of the transition section is in a tapered cylinder shape, and a paper tube with the diameter of 80mm and the length of about 4500mm is adopted, wherein 3500mm is in a cylinder shape, and 1000mm is in a tapered shape, so that the molded surface is parallel to a shell bus after the heat-insulating layer 3 of the transition section is wrapped.
A step (204): according to the requirement of ablation section thickness of 10mm, the heat-insulating material can be decomposed into 8mm bottom heat-insulating layer and 2mm surface heat-insulating layer, wherein the 8mm bottom heat-insulating layer is made of ablation ethylene propylene diene monomer rubber heat-insulating layer, and is formed by one-step pressing with a die at 85 ℃ and 150kg/cm under pressure 2 The surface layer heat insulation layer material with the heat preservation time of 3h and 2mm is an ethylene propylene diene monomer heat insulation layer; wherein the ablation type heat insulation layer of 8mm is 3+2, and bonding is carried out for three times.
Step (205): the thickness of the carbon wool board in the composite heat insulation layer 5 is 9mm, the carbon wool board can be divided into 3 layers of 3mm, the prepared carbon wool boards are respectively paved in a mould cavity and are pressed and formed on a flat vulcanizing machine, the pressing process is carried out at the temperature of 50 ℃, and the pressure is 300kg/cm 2 And keeping the temperature for 3 hours to finish the pressing of the three layers of the heat insulating layers of the carbon wool boards.
Step (206): preparing a front artificial debonding layer 6 and a rear artificial debonding layer 7, filling a common ethylene propylene diene monomer rubber heat insulating layer into a mold, and pressurizing at 150kg/cm on a flat vulcanizing machine at 150 DEG C 2 And preserving the heat for 2 hours to obtain a front artificial debonding layer 6 and a rear artificial debonding layer 7 with the thickness of 3mm.
Step (207): and brushing an adhesive on the bonding surfaces of the combustion chamber shell and the front end enclosure heat-insulating layer 1 and the rear end enclosure heat-insulating layer 2, then respectively bonding the front end enclosure heat-insulating layer 1 and the rear end enclosure heat-insulating layer 2 on the front end enclosure part and the rear end enclosure part of the combustion chamber shell, and compacting.
A step (208): brushing an adhesive on the bonding surface of the heat insulating layer 3 at the transition section, winding the bonding surface on a tapered cylindrical barrel-shaped tool, isolating the bonding surface by polytetrafluoroethylene varnished cloth, putting the tapered cylindrical barrel-shaped tool into a combustion chamber shell, taking the end surface of the front end enclosure heat insulating layer 1 as a positioning reference, simultaneously rotating the combustion chamber shell and unfolding the tapered cylindrical barrel-shaped tool to enable the heat insulating layer 3 at the transition section to be bonded at a corresponding position on the inner wall of the combustion chamber shell, finally taking the tapered cylindrical barrel-shaped tool out, compacting, bonding and preventing the bonding from falling off.
Step (209): and brushing an adhesive on the bonding surface of the first bottom insulating layer of the erosion section, adhering the first bottom insulating layer of the erosion section to a corresponding position in the combustion chamber shell, respectively overlapping the front and the back with the transition section heat insulating layer 3 and the back end socket heat insulating layer 2, and compacting in place by using a roller.
A step (210): the first layer of the composite heat insulation layer 5 is bonded, the prepared surface of the carbon wool board heat insulation layer is wiped clean by ethyl acetate, after the carbon wool board heat insulation layer is dried, an adhesive is coated on the bonding surface (including the side surface) of the carbon wool board and the surface of the rear end enclosure heat insulation layer 2 which is bonded with the bonding surface, then the carbon wool board is bonded on the corresponding position of the surface of the rear end enclosure heat insulation layer 2, the carbon wool board is subjected to butt joint treatment between each section of the carbon wool board, the carbon wool board is firmly bonded by hand compaction, wherein a heat insulation layer adhesive tape with the thickness of 1 mm-2 mm is placed at the butt joint gap of each section of the carbon wool board, the material is consistent with the heat insulation layer 3 at the transition section, and the integrity and the absence of a whole profile structure are ensured.
A step (211): after the work is finished, the surface of the heat insulation layer is checked to have no foreign matters, the sticking is firm, the air bag and the tool are assembled in place, and the heat is preserved for 3 hours in an oven at the temperature of 90 ℃ and under the pressure of 0.9MPa.
Repeating the step (209) to the step (211).
Step (212): and (3) coating an adhesive on the surface of the prepared surface heat-insulating layer, the surface of the bottom heat-insulating layer adhered to the surface of the prepared surface heat-insulating layer and the surface of the carbon wool board, then finishing the adhesion of the surface heat-insulating layer, and carrying out hot pressing by the method in the step (211).
Step (213): and respectively bonding the front artificial debonding layer 6 and the rear artificial debonding layer 7 to the surface of the front end socket heat insulation layer 1 and the surface of the surface layer heat insulation layer to form the heat insulation layer structure of the combustion chamber of the solid rocket engine.
Step (214): vulcanizing, checking that no foreign matter exists on the surface of the heat insulating layer after the work is finished, firmly sticking, assembling the air bag and the tool in place, heating the room temperature to 100 ℃ after 3h, preserving the heat for 2h, heating to 130 ℃ after 2h, preserving the heat for 3h, heating to 170 ℃ after 3h, preserving the heat for 5h, and naturally cooling to the room temperature after the heat preservation is finished; the total vulcanization pressure was 0.9MPa.
Step (215): and after the curing is finished, dismantling the tool, and carrying out size, thickness and interface inspection. The heat insulation layer has complete profile, no bulge, qualified size, qualified thickness and qualified ultrasonic flaw detection of the bonding interface. In the process, the adhesive is dried for not less than 15min after being coated, so that the solvent is ensured to be volatilized completely. The air bag is made of butyl rubber, and the profile of the air bag is matched with the inner profile of the heat insulation layer.
It is worth explaining that the bonding method of the solid rocket engine combustion chamber heat insulation layer structure is used for the solid rocket engine combustion chamber with the length-diameter ratio larger than 15, the auxiliary manual bonding tool or the mechanical automatic bonding tool is used for realizing the integral bonding molding of the heat insulation layer of the transition section with the thickness of less than 1mm, compared with the segmentation and split bonding, the bonding method has the characteristics of high reliability and good consistency, and the production efficiency is improved by at least 5 times, secondly, the heat insulation layer of the ablation section adopts a bottom layer insulation layer and a surface layer insulation layer which are combined by two types of soft and hard, the bonding effect with the grain can be better obtained, the ablation resistance and scouring resistance requirements of the material are simultaneously met, the design thickness of the heat insulation layer can be effectively reduced through decomposing into structures with different performances of the same matrix, the cost of the material is reduced, and the cost can be reduced by more than 12%; in addition, when the composite heat insulating layer is bonded, a process of integrated vulcanization molding of a mold is adopted, so that the interface bonding effect and the quality reliability are high compared with multiple times of vulcanization molding, and the molding period is shortened from the original 6 days to 3 days.
The above-mentioned serial numbers of the embodiments of the present invention are merely for description and do not represent the merits of the embodiments.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and should not be taken as limiting the scope of the present invention, which is intended to cover any modifications, equivalents, improvements, etc. within the spirit and scope of the present invention.
Claims (10)
1. A solid rocket engine combustion chamber insulation barrier, said insulation barrier comprising:
the front seal head heat insulation layer (1) and the rear seal head heat insulation layer (2) are respectively bonded to the front seal head part and the rear seal head part of the combustion chamber shell;
the transition section heat insulation layer (3) is adhered in the combustion chamber shell, and one end of the transition section heat insulation layer (3) is lapped with the front end enclosure heat insulation layer (1);
the ablation section heat insulation layer (4) is adhered in the combustion chamber shell, one end of the ablation section heat insulation layer (4) is in lap joint with the transition section heat insulation layer (3), and the other end of the ablation section heat insulation layer (4) is in lap joint with the rear end enclosure heat insulation layer (2);
the composite heat insulation layer (5) is adhered to the surface of the rear end socket heat insulation layer (2);
the front artificial debonding layer (6) and the rear artificial debonding layer (7) are respectively bonded to the surface of the front end enclosure heat insulation layer (1) and the surface of the ablation section heat insulation layer (4).
2. The solid rocket engine combustion chamber insulation structure of claim 1,
the ablation section thermal insulation layer (4) comprises: the ablation performance of the bottom layer insulating layer is higher than that of the surface layer insulating layer;
the bottom layer insulating layer is of one or more layers and is adhered in the combustion chamber shell, and the surface layer insulating layer is adhered to the surface of the bottom layer insulating layer;
the post manual debonding layer (7) is bonded to the surface of the surface layer insulating layer;
the composite heat insulation layer (5) is of a carbon fiber composite heat insulation layer structure and comprises multiple layers, and each layer is divided into 6 to 8 petals.
3. The solid rocket engine combustion chamber insulation structure of claim 2,
the thicknesses of the front end socket heat insulation layer (1) and the rear end socket heat insulation layer (2) are 4 to 5mm;
the thickness of the heat insulation layer (3) of the transition section is less than 1mm, the length of the heat insulation layer (3) of the transition section is 2000-4500 mm, a circumferential circle of thickened areas are arranged every 700-800mm to form a reinforced platform, the width of the reinforced platform is 20-50mm, and the thickness of the reinforced platform is 2-3mm;
the thickness of the ablation section heat insulation layer (4) is more than 5mm, and the thickness of the surface layer heat insulation layer is 1 to 2mm;
the thickness of the composite heat insulation layer (5) is not less than 6mm;
the thicknesses of the front artificial debonding layer (6) and the rear artificial debonding layer (7) are 2-3mm.
4. A method of bonding a solid rocket motor combustion chamber insulation as claimed in any one of claims 1-3, wherein said bonding method comprises:
s1: pretreating the combustion chamber shell;
s2: preparing a front end enclosure heat insulation layer (1), a rear end enclosure heat insulation layer (2), a transition section heat insulation layer (3), an ablation section heat insulation layer (4), a composite heat insulation layer (5), a front artificial debonding layer (6) and a rear artificial debonding layer (7);
s3: respectively bonding the prepared front seal head heat insulation layer (1) and the prepared rear seal head heat insulation layer (2) to a front seal head part and a rear seal head part of a combustion chamber shell;
s4: bonding the transition section heat insulation layer (3) to the inner wall of the combustion chamber shell, wherein one end of the transition section heat insulation layer (3) is overlapped with the front end socket heat insulation layer (1);
s5: then adhering the ablation section heat insulation layer (4) and the composite heat insulation layer (5), wherein one end of the ablation section heat insulation layer (4) is overlapped with the transition section heat insulation layer (3), the other end of the ablation section heat insulation layer (4) is overlapped with the rear end socket heat insulation layer (2), and the composite heat insulation layer (5) is positioned on the surface of the rear end socket heat insulation layer (2);
s6: finally, respectively bonding the front manual debonding layer (6) and the rear manual debonding layer (7) to the surface of the front end socket heat insulation layer (1) and the surface of the ablation section heat insulation layer (4) to form a solid rocket engine combustion chamber heat insulation layer structure;
s7: vulcanizing the solid rocket engine combustion chamber heat insulating layer structure.
5. The method of bonding a solid rocket engine combustion chamber insulation layer structure as recited in claim 4, wherein said S1 comprises:
carrying out sand blowing treatment on the inner surface of the combustion chamber shell by adopting 16-24 meshes of brown corundum or quartz sand under the air pressure of 0.4-0.6 MPa, then removing floating dust on the inner surface of the combustion chamber shell, cleaning and airing, and brushing an adhesive primer on the adhesive surface for later use.
6. The method of bonding a solid rocket engine combustion chamber insulation layer structure as recited in claim 4, wherein said S2 comprises:
after the rubber insulating layer is filled into a mold, the mold is pressed on a flat vulcanizing machine at 80 to 85 ℃ for 80 to 150kg/cm 2 Keeping the temperature for 2 to 3 hours, and performing polishing treatment after pressing to obtain the front end socket heat insulation layer (1) and the rear end socket heat insulation layer (2);
splicing a plurality of rubber heat insulation layers according to the molded surface of the transition section to form the heat insulation layer (3) of the transition section and a plurality of reinforcing platforms;
pressing and forming by adopting a mould according to the molded surface of the ablation section, wherein the pressing temperature is 80-85 ℃, and the pressure is 80-150kg/cm 2 Keeping the temperature for 2 to 3h to obtain a bottom insulating layer and a surface insulating layer which form the ablation section insulating layer (4), wherein the ablation performance of the bottom insulating layer is higher than that of the surface insulating layer;
designing a molded surface according to the composite heat insulation layer at the rear end socket part, and pressing the composite heat insulation layer (5) by adopting a male and female die, wherein the pressing temperature is 50-60 ℃, and the pressure is 100-300 kg/cm 2 The heat preservation time is 1-3 h, the composite heat insulation layer (5) is a plurality of layers, and each layer is divided into 6 to 8 petals;
filling the rubber insulating layer into a mold, and pressurizing 100-150kg/cm on a flat vulcanizing machine at the temperature of 150-160 DEG C 2 Keeping the temperature for 1-2 h, and polishing the bonding surface after pressing to obtain the front manual debonding layer (6) and the rear manual debonding layer (7);
the rubber insulating layer is a nitrile rubber insulating layer or an ethylene propylene diene monomer insulating layer.
7. The method of claim 6, wherein the step of bonding the insulation layer structure of the combustion chamber of the solid-rocket engine,
the S4 comprises the following steps: brushing an adhesive on the bonding surface of the heat insulating layer (3) of the transition section, winding the bonding surface on the surface of an auxiliary bonding tool, isolating the bonding surface by using polytetrafluoroethylene varnished cloth, putting the auxiliary bonding tool into a combustion chamber shell, taking the end surface of the heat insulating layer (1) of the front end socket as a positioning reference, simultaneously rotating the combustion chamber shell and unfolding the auxiliary bonding tool to enable the heat insulating layer (3) of the transition section to be bonded at a corresponding position on the inner wall of the combustion chamber shell, and finally taking out the auxiliary bonding tool for compaction;
the auxiliary bonding tool is a cylindrical barrel-shaped tool or a tapered cylindrical barrel-shaped tool.
8. The method for bonding a thermal insulation layer structure of a combustion chamber of a solid rocket motor according to claim 6 wherein when said underlying insulation layer is a one-layer structure, said S5 comprises:
the bottom layer insulating layer is adhered in the combustion chamber shell, and the front and the rear of the bottom layer insulating layer are respectively lapped with the transition section insulating layer (3) and the rear end enclosure insulating layer (2);
cleaning the surface of the first composite heat insulation layer (5), adhering the cleaned surface to the surface of the rear end socket heat insulation layer (2), performing butt joint treatment between every two sections, and then performing hot pressing;
cleaning the surface of the second layer of composite heat insulation layer (5), then sticking the second layer of composite heat insulation layer (5) to the surface of the first layer of composite heat insulation layer (5), and repeating the steps to stick the composite heat insulation layer (5) to the required thickness, wherein a heat insulation layer adhesive tape with the thickness of 1-2 mm is placed at the butt joint gap of each section of composite heat insulation layer (5);
bonding the surface insulating layer on the surface of the bottom insulating layer, and hot-pressing;
when the underlying insulating layer is a multilayer structure, the S5 includes:
adhering a first layer of the bottom insulating layer in a combustion chamber shell, and respectively overlapping the front and the back of the first layer of the bottom insulating layer with a transition section heat insulating layer (3) and a back end enclosure heat insulating layer (2);
cleaning the surface of the first layer of composite heat insulation layer (5), adhering the first layer of composite heat insulation layer to the surface of the rear end enclosure heat insulation layer (2), performing butt joint treatment between every two sections of the first layer of composite heat insulation layer, and then performing hot pressing;
adhering a second bottom insulating layer to the surface of the first bottom insulating layer;
cleaning the surface of the second layer of composite heat insulation layer (5), sticking the cleaned surface on the surface of the first layer of composite heat insulation layer (5), performing butt joint treatment between every two sections, placing a heat insulation layer adhesive tape with the thickness of 1-2 mm between every two sections of the second layer of composite heat insulation layer (5) to ensure the integrity of the whole profile structure and no gap, and then performing hot pressing;
repeating the step S5 until the thicknesses of the bottom layer insulating layer and the composite heat insulating layer (5) meet the requirements;
bonding the surface insulating layer on the surface of the bottom insulating layer on the uppermost layer, and hot-pressing;
wherein the hot pressing condition is that the temperature is 80 to 90 ℃, the pressure is 0.7 to 0.9MPa, and the heat preservation is carried out for 1 to 3 hours.
9. The method of claim 4, wherein the S7 curing comprises:
assembling the air bag and the tool in place, heating the air bag to 90-100 ℃ within 2-3 h at room temperature, preserving heat for 1-2h, heating to 120-130 ℃ within 1-2h, preserving heat for 2-3h, heating to 160-170 ℃ within 2-3h, preserving heat for 3-5 h, and naturally cooling to room temperature after heat preservation is finished; the whole vulcanization pressure is 0.8-0.9 MPa.
10. The method for bonding the structure of the heat insulating layer of the combustion chamber of the solid rocket engine according to any one of claims 4 to 9, wherein the bonding method is used for bonding the heat insulating layer of the combustion chamber of the solid rocket engine with the length-diameter ratio of more than 15.
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