CN116517725A - Rocket storage tank heat insulation interlayer common-bottom structure and processing method thereof - Google Patents
Rocket storage tank heat insulation interlayer common-bottom structure and processing method thereof Download PDFInfo
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- CN116517725A CN116517725A CN202310491288.6A CN202310491288A CN116517725A CN 116517725 A CN116517725 A CN 116517725A CN 202310491288 A CN202310491288 A CN 202310491288A CN 116517725 A CN116517725 A CN 116517725A
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- 238000009413 insulation Methods 0.000 title claims abstract description 53
- 239000011229 interlayer Substances 0.000 title claims abstract description 20
- 238000003672 processing method Methods 0.000 title claims abstract description 8
- 238000003860 storage Methods 0.000 title abstract description 23
- 239000012792 core layer Substances 0.000 claims abstract description 35
- 239000010410 layer Substances 0.000 claims description 73
- 238000003466 welding Methods 0.000 claims description 31
- 238000005507 spraying Methods 0.000 claims description 14
- 238000000034 method Methods 0.000 claims description 13
- 239000006260 foam Substances 0.000 claims description 10
- 229920005830 Polyurethane Foam Polymers 0.000 claims description 8
- 229920007790 polymethacrylimide foam Polymers 0.000 claims description 8
- 239000011496 polyurethane foam Substances 0.000 claims description 8
- 238000004519 manufacturing process Methods 0.000 claims description 4
- 230000006641 stabilisation Effects 0.000 claims 1
- 238000011105 stabilization Methods 0.000 claims 1
- 229910052751 metal Inorganic materials 0.000 abstract description 15
- 239000002184 metal Substances 0.000 abstract description 15
- 239000003380 propellant Substances 0.000 abstract description 12
- 125000006850 spacer group Chemical group 0.000 abstract description 4
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 8
- 238000007789 sealing Methods 0.000 description 8
- 239000003350 kerosene Substances 0.000 description 7
- 230000001681 protective effect Effects 0.000 description 7
- 229920006335 epoxy glue Polymers 0.000 description 6
- 229910052755 nonmetal Inorganic materials 0.000 description 5
- 238000001514 detection method Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000003754 machining Methods 0.000 description 4
- 239000000446 fuel Substances 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 238000000465 moulding Methods 0.000 description 3
- 238000002360 preparation method Methods 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 241000219112 Cucumis Species 0.000 description 1
- 235000015510 Cucumis melo subsp melo Nutrition 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- FJJCIZWZNKZHII-UHFFFAOYSA-N [4,6-bis(cyanoamino)-1,3,5-triazin-2-yl]cyanamide Chemical compound N#CNC1=NC(NC#N)=NC(NC#N)=N1 FJJCIZWZNKZHII-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009835 boiling Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 238000009422 external insulation Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000011049 filling Methods 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000003475 lamination Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 231100000956 nontoxicity Toxicity 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000003756 stirring Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/605—Reservoirs
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention provides a rocket storage tank heat-insulating interlayer co-bottom structure and a processing method thereof, and relates to the technical field of rocket storage tanks. The rocket storage tank heat insulation interlayer common-bottom structure comprises an upper panel, a heat insulation core layer, a lower panel and an outflow flange, wherein the upper surface of the heat insulation core layer is connected with the lower surface of the upper panel, the lower surface of the heat insulation core layer is connected with the upper surface of the lower panel, the top root of the upper panel is fixedly connected with the top root of the lower panel, so that a heat insulation spacer can be canceled, the interlayer common-bottom assembly difficulty is reduced, the upper panel, the heat insulation core layer and the lower panel are provided with outflow openings at the center of the bottom end, the outflow flange is positioned at the outflow openings and is respectively connected with the upper panel and the lower panel, the propellant of the front tank can be conveyed to an engine in the rear tank through a tunnel pipe connected with the outflow flange, a conveying system of the rocket is optimized, and the outflow flange is provided with a compensation pipe which can compensate deformation and internal force generated by metal shrinkage of the upper panel and the lower panel in a low-temperature environment.
Description
Technical Field
The invention relates to the technical field of rocket storage tanks, in particular to a rocket storage tank heat-insulating interlayer common-bottom structure and a processing method thereof.
Background
The low-temperature fuel such as liquid oxygen kerosene, liquid oxygen liquid hydrogen and the like has the characteristics of high combustion heat, no toxicity and no pollution, and is an advanced propellant of modern space vehicles, such as ARIANE series rocket in Europe, DELTA series rocket in the United states and ALTAS series rocket, which are all adopted at the low temperature. The new generation carrier rockets of CZ-5, CZ-7 and the like in China also adopt liquid oxygen kerosene as propellant.
The biggest bottleneck in using liquid oxygen kerosene low-temperature fuel is the manufacturing technology of the low-temperature liquid oxygen kerosene common-bottom storage tank, the ground preparation time of the carrier rocket is long, and the space flight and the residence time are long, so that the problem of heat insulation of the low-temperature storage tank is particularly outstanding. In order to effectively lighten the quality of the storage tank and improve the carrying capacity, the secondary storage tank in a new generation carrier rocket of a certain model is designed to be of a heat insulation common-base structure, the storage tank is divided into two independent systems, and the boiling point of liquid oxygen in the front tank is minus 183 ℃. This requires strict external insulation of the tank, which would otherwise cause the cryogenic liquid to evaporate rapidly, causing the tank to explode with serious consequences. According to the records of the American aviation and aerospace agency, 56% of carrier rocket accidents are related to liquid oxygen storage tanks. The freezing point of the liquid kerosene in the rear box is-47 ℃, and strict heat insulation measures are required for the front box and the rear box of the common-bottom structure in order to ensure that the fluidity of the kerosene can meet the requirements of normal operation of an engine. Thus, large temperature differential sandwich co-bottoming is one of the key technologies for low temperature fuel tanks.
The applicant found that at least the following technical problems exist in the prior art: the front box and the rear box have larger temperature difference, and the low-temperature storage problem of different heat leakage mechanisms such as convection heat exchange, solid heat conduction and the like is generated. At present, the scheme commonly adopted at home and abroad is two-layer metal shells and a sandwich layer structure positioned in the middle, the first is a sandwich common-bottom structure of a nonmetallic honeycomb sandwich aluminum alloy shell represented by a CZ-3B three-level storage tank, the heat insulation effect is achieved by vacuumizing, the advantage is that the heat insulation effect of a vacuum layer is very good, the heat conductivity is lower, the disadvantage is that the sandwich common-bottom structure is complex, the requirement on a heat insulation layer is higher, vacuumizing is needed before test and use, the efficiency is low, the cost is high, and the preparation time is longer before the carrier is launched.
The second is that the thickness-variable Polymethacrylimide (PMI) foam sandwich aluminum alloy panel represented by CZ-6A secondary storage tank shares the bottom storage tank structure, and has the advantages of simpler structure compared with vacuum sharing, no need of vacuumizing before test and use, shortened preparation time before the launch of a carrier, and the defects that the upper panel and the lower panel adopt complex melon split welding technology, the panel size and the form and position tolerance are larger, the bonding difficulty of a foam layer and a metal shell is higher, the VARI technology is needed to be adopted for bonding, and the connecting structure of the two panels at the bottom is more complex, the processing cost is higher and the efficiency is lower.
The two structures are characterized in that the absolute heat insulation performance of the two parts of the storage box is emphasized, the non-metal isolation pad is used at the connecting part of the inner layer and the outer layer of metal, the metal is not in direct contact with each other, and the upper panel and the lower panel are connected by using screws. Because the upper and lower metal panels of the structure are welded together, the structural accuracy of the metal panels is not high, so that the hard sandwich is quite difficult to attach to the upper and lower panels, the requirements on equipment and operators are high, and the time and the labor are wasted.
In addition, the two structures do not have a central outflow port design, the problem that the front box fuel is conveyed through the inside of the rear box cannot be solved, and the conveying mode outside the box is required to be carried out, so that the complexity of a rocket structure is increased, the aerodynamic characteristics of the appearance of an rocket body are affected, and the reliability of the whole rocket is reduced.
In addition, there is a third scheme, which is represented by the chinese patent of publication No. CN115750142a and adopts a common-bottom configuration of a single metal panel layer and a non-metal heat insulating layer, and the configuration has the advantages of simple structure, simpler processing technique and low manufacturing difficulty, but also has the disadvantage that the lower surface of the non-metal heat insulating layer directly contacts with the propellant in the working process, and the non-metal layer contacts with the low-temperature propellant to have the risk of cracking or even falling.
Disclosure of Invention
The invention aims to provide a rocket storage tank heat-insulating interlayer co-base structure and a processing method thereof, which are used for solving the technical problems in the prior art. The preferred technical solutions of the technical solutions provided by the present invention can produce a plurality of technical effects described below.
In order to achieve the above purpose, the present invention provides the following technical solutions:
the utility model provides a rocket tank heat insulation intermediate layer is bottom structure altogether, includes top panel, adiabatic sandwich layer, lower panel and outflow flange, the upper surface of adiabatic sandwich layer with the lower surface of top panel is connected, the lower surface of adiabatic sandwich layer with the upper surface of lower panel is connected, the top root of top panel with the top root fixed connection of lower panel, the top panel the adiabatic sandwich layer with the outflow mouth has been seted up jointly in the bottom center to the lower panel, outflow flange is located outflow mouth department and respectively with the top panel with the lower panel is connected, be provided with the compensation pipe on the outflow flange.
Preferably, the outflow flange further comprises an upper plate flange, a lower plate flange, an outlet flange and a flange heat insulation layer, wherein the upper plate flange is connected with the top of the compensation pipe, the outlet flange is connected with the bottom of the compensation pipe, the lower plate flange is positioned on the outer side of the compensation pipe, the bottom of the lower plate flange is connected with the bottom of the outlet flange, the flange heat insulation layer is connected with the outer side of the compensation pipe, the upper plate flange is connected with the upper plate flange, the lower plate flange is connected with the lower plate flange, and the outlet flange is connected with an external pipeline flange.
Preferably, the outflow flange further comprises a low-temperature sealing ring, and the low-temperature sealing ring is respectively arranged between the upper plate flange and the upper panel and between the lower plate flange and the lower panel.
Preferably, the heat insulating core layer is made of polyurethane foam or PMI foam.
Preferably, a buffer layer is provided between the upper surface of the heat insulating core layer and the lower surface of the upper panel and between the lower surface of the heat insulating core layer and the upper surface of the lower panel.
Preferably, the flange heat insulation layer is made of polyurethane foam or PMI foam.
A processing method of a rocket tank heat-insulating interlayer common-bottom structure comprises the following specific steps:
s1, respectively processing and forming an upper panel, a lower panel and an outflow flange;
s2, spraying a buffer layer on the lower surface of the upper panel, and spraying a heat insulation core layer on the lower surface of the buffer layer after the buffer layer is solidified;
s3, removing foam allowance of the heat insulation core layer to a theoretical size;
s4, spraying a buffer layer on the upper surface of the lower panel or the lower surface of the heat insulation core layer;
s5, buckling the lower panel with the upper panel, attaching the upper surface of the lower panel with the lower surface of the heat insulation core layer, and fixedly connecting the top root of the upper panel with the top root of the lower panel;
s6, connecting the outflow flange with the upper panel and the lower panel respectively to form a common-bottom structure.
Preferably, the method further comprises a step S7, wherein the airtight hydraulic test is carried out on the co-base structure workpiece formed in the step S6, then a low-temperature test is carried out, and temperature data of different positions are recorded after the temperature is stable.
Preferably, in step S1, the specific steps of the outflow flange processing and molding are:
i, welding the upper plate flange and the compensating pipe through circular seams;
II, welding the compensating pipe with the annular seam of the outlet flange, and detecting a flaw after the welding is finished;
thirdly, carrying out girth welding on the outlet flange and the lower plate flange, and detecting a flaw after the welding is finished;
and IV, performing airtight hydraulic test and low-temperature test.
Preferably, before step S6, a flange heat insulation layer is sprayed on the outflow flange, and the foam allowance of the flange heat insulation layer is removed to a theoretical size.
The beneficial effects of the invention are as follows: the top root of the upper panel is fixedly connected with the top root of the lower panel, so that a heat insulation spacer can be omitted, and the assembly difficulty of the sandwich type common bottom is reduced;
the center is provided with the outflow port and is connected with the outflow flange, the outflow flange can be connected with an external tunnel pipe, and the propellant in the front box can be conveyed to the engine through the tunnel pipe in the rear box, so that the rocket conveying system is optimized;
the outflow flange is provided with a compensation pipe, and the compensation pipe can compensate deformation and internal force generated by metal shrinkage of the upper panel and the lower panel in a low-temperature environment.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a block diagram of the present invention;
FIG. 2 is an enlarged structural view of the portion A in FIG. 1;
FIG. 3 is an enlarged structural view at B in FIG. 1;
FIG. 4 is a block diagram of an outflow flange of the present invention;
1, an upper panel;
2. a thermally insulating core layer;
3. a lower panel;
4. an outflow flange; 41. a compensation tube; 42. an upper plate flange; 43. a lower plate flange; 44. an outlet flange; 45. a flange heat insulating layer; 46. and (5) a low-temperature sealing ring.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail below. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. All other embodiments, based on the examples herein, which are within the scope of the invention as defined by the claims, will be within the scope of the invention as defined by the claims.
In the description of the present invention, it should be understood that the terms "center", "side", "length", "width", "height", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "side", etc. indicate orientations or positional relationships based on the orientation or positional relationships shown in fig. 1 are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
In the description of the present invention, it should also be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the above terms in the present invention can be understood as appropriate by those of ordinary skill in the art.
Referring to fig. 1 to 4, the invention provides a rocket tank heat insulation interlayer co-base structure, which comprises an upper panel 1, a heat insulation core layer 2, a lower panel 3 and an outflow flange 4;
the upper surface of the heat insulation core layer 2 is connected with the lower surface of the upper panel 1, the lower surface of the heat insulation core layer 2 is connected with the upper surface of the lower panel 3, the upper panel 1 and the lower panel 3 are similar in shape, a fork-shaped ring structure matched with each other is formed at the root of the top end, the root of the top end of the upper panel 1 and the root of the top end of the lower panel 3 are fixedly connected, the fixed connection can be further preferably welded, and the heat insulation spacer can be omitted, so that the sandwich type common-bottom assembly difficulty is reduced;
the upper panel 1 and the lower panel 3 are preferably formed by metal through a high-precision integral machining, so that the metal panel is formed, the heat insulation core layer 2 is made of polyurethane foam or PMI foam, and the arrangement can reduce the bonding difficulty of the metal layer and the hard sandwich and simplify the assembly process;
the upper panel 1, the heat insulation core layer 2 and the lower panel 3 are connected together to form a double-sided board sandwich common-bottom structure, so that the non-metal heat insulation layer can be prevented from directly contacting the propellant, the heat insulation layer is prevented from falling off and the generation of excessive materials is also prevented, and the filling, short-time storage and outflow of liquid oxygen and kerosene of the upper tank and the lower tank of the rocket propellant storage tank are realized through the double-sided board sandwich common-bottom structure;
the upper panel 1, the heat insulation core layer 2 and the lower panel 3 are provided with a flow outlet at the center of the bottom end, and the outflow flange 4 is positioned at the flow outlet and is respectively connected with the upper panel 1 and the lower panel 3;
through arranging an outflow port in the center and connecting an outflow flange 4, the outflow flange 4 can be connected with an external tunnel pipe, so that a front box and an engine can be communicated through the outflow flange 4, the tunnel pipe can pass through a rear box, propellant in the front box can be conveyed to the engine in the rear box through the tunnel pipe, and a rocket conveying system is optimized;
the outflow flange 4 is provided with a compensating tube 41, and the compensating tube 41 is preferably a corrugated compensating tube, and the compensating tube 41 can compensate deformation and internal force generated by metal shrinkage of the upper panel 1 and the lower panel 3 in a low-temperature environment by being provided with the compensating tube 41.
As an alternative embodiment, the outflow flange 4 further comprises an upper plate flange 42, a lower plate flange 43, an outlet flange 44 and a flange heat insulation layer 45, wherein the upper plate flange 42 is connected to the top of the compensation tube 41, the connection is preferably a welding connection, and further preferably automatic TIG welding is adopted, and flaw detection operation is required after the welding is completed;
the outlet flange 44 is connected to the bottom of the compensation tube 41, where the connection is preferably a welded connection, and further preferably an automatic TIG welding is used, and after the welding is completed, a flaw detection operation is performed;
the lower plate flange 43 is located outside the compensation tube 41 and its bottom is connected to the bottom of the outlet flange 44, where the connection is preferably a welded connection, and may further preferably be an automatic TIG welding, and after the welding is completed, the flaw detection operation is performed;
the compensation pipe 41, the upper plate flange 42, the lower plate flange 43 and the outlet flange 44 can be connected together, so that the connection strength and the stability are good;
the flange heat insulating layer 45 is connected to the outside of the compensation tube 41, and in this embodiment, the flange heat insulating layer 45 is preferably made of polyurethane foam or PMI foam, and thus, the flange heat insulating layer 45 is preferably sprayed to the outside of the compensation tube 41;
the upper plate flange 42 is in flange connection with the upper panel 1, the flange connection has good connection strength, so that the upper plate flange 42 and the upper panel 1 are firmly connected, the disassembly and the assembly are convenient, and the assembly process is simplified;
the lower plate flange 43 is in flange connection with the lower panel 3, the flange connection has good connection strength, so that the upper plate flange 42 and the upper panel 1 are firmly connected, the disassembly and the assembly are convenient, and the assembly process is simplified;
as described above, the compensation tube 41, the upper plate flange 42, the lower plate flange 43, the upper panel 1, and the lower panel 3 can be connected together, whereby the compensation tube 41 can compensate for deformation and internal force generated by metal shrinkage of the upper panel 1 and the lower panel 3 in a low-temperature environment;
the outlet flange 44 is connected with an external pipeline flange, the external pipeline is a tunnel pipe, the front box and the engine can be communicated, the flange connection has good connection strength, the disassembly and the assembly are convenient, the outlet flange 44 is favorable for smooth connection with the external pipeline, the tunnel pipe can penetrate through the rear box, the propellant of the front box can be conveyed to the engine through the tunnel pipe, and the conveying system of the rocket is optimized.
As an alternative embodiment, the outflow flange 4 further includes a low-temperature sealing ring 46, and the low-temperature sealing ring 46 is respectively disposed between the upper plate flange 42 and the upper panel 1 and between the lower plate flange 43 and the lower panel 3, so that the low-temperature sealing ring 46 can have a good sealing effect, thereby effectively maintaining air tightness.
As an alternative embodiment, a buffer layer is provided between the upper surface of the heat insulating core layer 2 and the lower surface of the upper panel 1 and between the lower surface of the heat insulating core layer 2 and the upper surface of the lower panel 3, the buffer layer is preferably made of epoxy glue, and in actual processing, the upper surface of the heat insulating core layer 2 is preferably sprayed with epoxy glue by spraying, and the lower surface of the heat insulating core layer 2 or the upper surface of the lower panel 3 is sprayed with epoxy glue by spraying epoxy glue as the buffer layer, so that the bonding firmness can be effectively increased.
The invention also provides a processing method of the rocket storage tank heat-insulating interlayer co-bottom structure, which comprises the following specific steps:
s1, respectively processing and forming an upper panel 1, a lower panel 3 and an outflow flange 4;
the upper panel 1 and the lower panel 3 are preferably made of metal materials, and are formed by high-precision integral machining, the machining precision is preferably within +/-0.2 mm, and the main machining process of the outflow flange 4 is that all parts are integrally machined firstly and then welded and connected, so that the connection is firm;
s2, spraying a buffer layer on the lower surface of the upper panel 1, and spraying a heat insulation core layer 2 on the lower surface of the buffer layer after the buffer layer is solidified;
it should be noted that, before spraying the buffer layer and the heat insulation core layer 2, the surface of the relevant area, which is not sprayed on the upper panel 1, is preferably coated with a protective film, including the upper surface of the upper panel 1 and other parts to be assembled, after the protective film is coated, a buffer layer mainly containing epoxy glue is sprayed on the lower surface part of the upper panel 1 which is not coated with the protective film, then the buffer layer is cured, after the buffer layer is cured, polyurethane foam or PMI foam is sprayed to form the heat insulation core layer 2, and the upper panel 1 and the heat insulation core layer 2 form a temporary workpiece;
s3, removing foam allowance of the heat insulation core layer 2 to a theoretical size;
the temporary workpiece formed in the step S2 can be placed on a vertical lathe turntable, and the foam allowance is removed to the theoretical size, so that the lower surface of the heat insulation core layer 2 is smoother, and the subsequent lamination connection with the lower panel 3 is facilitated;
s4, spraying a buffer layer on the upper surface of the lower panel 3 or the lower surface of the heat insulation core layer 2;
the specific spraying position of the buffer layer can be flexibly selected according to the actual use requirement, and it is noted that if the buffer layer is sprayed on the upper surface of the lower panel 3, before the buffer layer is sprayed, a protective film is preferably coated on the surface of a relevant area, which is not sprayed on the lower panel 3, after the protective film is coated, a buffer layer mainly containing epoxy glue is sprayed on the upper surface part of the lower panel 3 without the protective film, then the buffer layer is cured, the thickness is preferably controlled to be 0.2mm+, and after the buffer layer is cured, the protective film on the lower panel 3 is removed;
s5, buckling the lower panel 3 with the upper panel 1, matching the corresponding positions of the outflow openings, bonding the upper surface of the lower panel 3 with the lower surface of the heat insulation core layer 2, knocking by using tools such as a rubber hammer when checking whether bonding is performed between the lower panel 3 and the lower surface of the heat insulation core layer, bonding the lower panel and the upper surface tightly, fixedly connecting the top root of the upper panel 1 with the top root of the lower panel 3, pressing the lower panel 3 by using a tool, bonding the circular seam, welding by using friction stir welding equipment, and welding by using fusion welding equipment;
s6, the outflow flange 4 is respectively connected with the upper panel 1 and the lower panel 3, the low-temperature sealing ring 46 is correctly placed to determine the position of the outflow flange, the moment is well made, and finally the common-bottom structure is formed.
The rocket storage tank heat-insulating interlayer co-bottom structure processed by the method can convey the propellant of the front tank to the engine through the tunnel pipe in the rear tank, and optimize the rocket conveying system;
the bonding difficulty of the metal layer and the hard sandwich can be reduced, and the assembly process is simplified;
the upper panel and the lower panel of the common-bottom structure are connected in a welding mode, so that an insulating spacer is omitted, and the assembly difficulty is reduced;
by adopting the double-sided board sandwich structure, the nonmetallic heat insulation layer can be prevented from directly contacting the propellant, and the heat insulation layer is prevented from falling off and generating surplus.
As an alternative implementation mode, the method further comprises a step S7, an airtight hydraulic test is carried out on the common-bottom structure formed in the step S6, then a low-temperature test is carried out, temperature data of different positions are recorded after the temperature is stable, the airtight hydraulic test is preferably 0.5MPa, the low-temperature test is preferably a low-temperature test at-192 ℃, and the common-bottom structure detected through the test can meet actual use requirements.
In an alternative embodiment, in step S1, the specific steps of the outflow flange processing and molding are as follows:
i, carrying out girth welding on the upper plate flange 42 and the compensation tube 41;
II, carrying out girth welding on the compensation tube 41 and the outlet flange 44, and detecting a flaw after the welding is finished;
III, carrying out girth welding on the outlet flange 44 and the lower plate flange 43, and detecting a flaw after the welding is finished;
IV, performing an airtight hydraulic test and a low-temperature test;
the welding in the steps is preferably automatic TIG welding, and the same welding equipment and fixture can be used to simplify the process, the airtight hydraulic test is preferably 0.5MPa, the low-temperature test is preferably-192 ℃ low-temperature test, and the outflow flange after the test detection can meet the actual use requirement.
As an alternative embodiment, before step S6, the flange heat insulating layer 45 is sprayed on the outflow flange 4, and since the flange heat insulating layer 45 is made of polyurethane foam or PMI foam, after the spraying is finished and the molding is performed, the foam allowance of the flange heat insulating layer 45 needs to be removed to the theoretical size, and the process can be modified by using a lathe, so that the surface of the flange heat insulating layer 45 is smoother, and a gap of 1-2mm is preferably left when the foam is polished, thereby facilitating the assembly.
The foregoing is merely illustrative embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily think about variations or substitutions within the technical scope of the present invention, and the invention should be covered. Therefore, the protection scope of the invention is subject to the protection scope of the claims.
Claims (10)
1. The utility model provides a rocket tank heat insulation intermediate layer is bottom structure altogether, its characterized in that includes top panel, adiabatic sandwich layer, lower panel and outflow flange, the upper surface of adiabatic sandwich layer with the lower surface of top panel is connected, the lower surface of adiabatic sandwich layer with the upper surface of lower panel is connected, the top root of top panel with the top root fixed connection of lower panel, the top panel adiabatic sandwich layer with the outflow mouth has been seted up jointly in the bottom center to the lower panel, outflow flange is located outflow mouth department and respectively with the top panel with the lower panel is connected, be provided with the compensation pipe on the outflow flange.
2. A rocket tank insulating interlayer co-floor structure according to claim 1, wherein the outflow flange further comprises an upper plate flange, a lower plate flange, an outlet flange and a flange insulating layer, wherein the upper plate flange is connected with the top of the compensation tube, the outlet flange is connected with the bottom of the compensation tube, the lower plate flange is positioned on the outer side of the compensation tube and the bottom thereof is connected with the bottom of the outlet flange, the flange insulating layer is connected on the outer side of the compensation tube, the upper plate flange is connected with the upper plate flange, the lower plate flange is connected with the lower plate flange, and the outlet flange is connected with an external pipeline flange.
3. A rocket tank insulating interlayer co-floor structure as recited in claim 2, wherein said outflow flange further comprises a low temperature seal ring, said low temperature seal ring being disposed between said upper plate flange and said upper panel and between said lower plate flange and said lower panel, respectively.
4. A rocket tank insulating interlayer co-floor structure according to claim 1, wherein said insulating core is made of polyurethane foam or PMI foam.
5. A rocket tank insulating interlayer co-floor structure according to claim 1, wherein a buffer layer is provided between the upper surface of the insulating core and the lower surface of the upper panel and between the lower surface of the insulating core and the upper surface of the lower panel.
6. A rocket tank insulating interlayer co-floor structure according to claim 2, wherein said flange insulating layer is made of polyurethane foam or PMI foam.
7. The processing method of the rocket tank heat-insulating interlayer common-bottom structure is characterized by comprising the following specific steps of:
s1, respectively processing and forming an upper panel, a lower panel and an outflow flange;
s2, spraying a buffer layer on the lower surface of the upper panel, and spraying a heat insulation core layer on the lower surface of the buffer layer after the buffer layer is solidified;
s3, removing foam allowance of the heat insulation core layer to a theoretical size;
s4, spraying a buffer layer on the upper surface of the lower panel or the lower surface of the heat insulation core layer;
s5, buckling the lower panel with the upper panel, attaching the upper surface of the lower panel with the lower surface of the heat insulation core layer, and fixedly connecting the top root of the upper panel with the top root of the lower panel;
s6, connecting the outflow flange with the upper panel and the lower panel respectively to form a common-bottom structure.
8. The method for processing a rocket tank insulating interlayer co-base structure according to claim 7, further comprising the step S7 of performing an airtight hydraulic test on the co-base structure workpiece formed in the step S6, then performing a low temperature test, and recording temperature data of different positions after temperature stabilization.
9. A method for manufacturing a rocket tank insulating interlayer co-bottom structure according to claim 7, wherein in step S1, the concrete steps of the outflow flange forming are as follows:
i, welding the upper plate flange and the compensating pipe through circular seams;
II, welding the compensating pipe with the annular seam of the outlet flange, and detecting a flaw after the welding is finished;
thirdly, carrying out girth welding on the outlet flange and the lower plate flange, and detecting a flaw after the welding is finished;
and IV, performing airtight hydraulic test and low-temperature test.
10. A method of manufacturing a rocket tank insulating interlayer co-floor structure as recited in claim 7, wherein prior to step S6, a flange insulating layer is sprayed onto said outflow flange, and the foam balance of said flange insulating layer is removed to a theoretical size.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310491288.6A CN116517725A (en) | 2023-05-04 | 2023-05-04 | Rocket storage tank heat insulation interlayer common-bottom structure and processing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310491288.6A CN116517725A (en) | 2023-05-04 | 2023-05-04 | Rocket storage tank heat insulation interlayer common-bottom structure and processing method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116517725A true CN116517725A (en) | 2023-08-01 |
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ID=87400677
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310491288.6A Pending CN116517725A (en) | 2023-05-04 | 2023-05-04 | Rocket storage tank heat insulation interlayer common-bottom structure and processing method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116517725A (en) |
-
2023
- 2023-05-04 CN CN202310491288.6A patent/CN116517725A/en active Pending
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