CN114229044A - Method for preparing heat-proof suit of revolving body - Google Patents
Method for preparing heat-proof suit of revolving body Download PDFInfo
- Publication number
- CN114229044A CN114229044A CN202111368773.1A CN202111368773A CN114229044A CN 114229044 A CN114229044 A CN 114229044A CN 202111368773 A CN202111368773 A CN 202111368773A CN 114229044 A CN114229044 A CN 114229044A
- Authority
- CN
- China
- Prior art keywords
- heat
- side wall
- bearing structure
- proof structure
- proof
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 45
- 238000012545 processing Methods 0.000 claims abstract description 42
- 238000004519 manufacturing process Methods 0.000 claims abstract description 9
- 239000003292 glue Substances 0.000 claims description 50
- 238000001514 detection method Methods 0.000 claims description 24
- 230000008569 process Effects 0.000 claims description 23
- 238000003754 machining Methods 0.000 claims description 21
- 229910000831 Steel Inorganic materials 0.000 claims description 17
- 239000010959 steel Substances 0.000 claims description 17
- 229910052782 aluminium Inorganic materials 0.000 claims description 14
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 14
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 12
- 229910052799 carbon Inorganic materials 0.000 claims description 10
- 238000000227 grinding Methods 0.000 claims description 10
- 238000005470 impregnation Methods 0.000 claims description 10
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 9
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 9
- 239000004809 Teflon Substances 0.000 claims description 9
- 229920006362 Teflon® Polymers 0.000 claims description 9
- 238000001035 drying Methods 0.000 claims description 9
- 238000005259 measurement Methods 0.000 claims description 8
- 238000004140 cleaning Methods 0.000 claims description 7
- 229920005989 resin Polymers 0.000 claims description 7
- 239000011347 resin Substances 0.000 claims description 7
- 239000004744 fabric Substances 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 6
- 238000005498 polishing Methods 0.000 claims description 6
- 239000000835 fiber Substances 0.000 claims description 5
- 238000005520 cutting process Methods 0.000 claims description 4
- 238000000465 moulding Methods 0.000 claims description 4
- YCKRFDGAMUMZLT-UHFFFAOYSA-N Fluorine atom Chemical compound [F] YCKRFDGAMUMZLT-UHFFFAOYSA-N 0.000 claims description 3
- 239000000853 adhesive Substances 0.000 claims description 3
- 230000001070 adhesive effect Effects 0.000 claims description 3
- 230000001680 brushing effect Effects 0.000 claims description 3
- 229910052731 fluorine Inorganic materials 0.000 claims description 3
- 239000011737 fluorine Substances 0.000 claims description 3
- 238000003801 milling Methods 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 3
- 239000000126 substance Substances 0.000 claims description 3
- 239000011248 coating agent Substances 0.000 claims description 2
- 238000000576 coating method Methods 0.000 claims description 2
- 230000001681 protective effect Effects 0.000 claims 1
- 238000004026 adhesive bonding Methods 0.000 description 9
- 239000002775 capsule Substances 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 238000012937 correction Methods 0.000 description 4
- 230000007547 defect Effects 0.000 description 4
- 238000007598 dipping method Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 238000009659 non-destructive testing Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 229910003460 diamond Inorganic materials 0.000 description 2
- 239000010432 diamond Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 238000004804 winding Methods 0.000 description 2
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 description 1
- 238000010146 3D printing Methods 0.000 description 1
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- FFBHFFJDDLITSX-UHFFFAOYSA-N benzyl N-[2-hydroxy-4-(3-oxomorpholin-4-yl)phenyl]carbamate Chemical compound OC1=C(NC(=O)OCC2=CC=CC=C2)C=CC(=C1)N1CCOCC1=O FFBHFFJDDLITSX-UHFFFAOYSA-N 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 229920001568 phenolic resin Polymers 0.000 description 1
- 239000005011 phenolic resin Substances 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000003908 quality control method Methods 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
- 229920002379 silicone rubber Polymers 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B11/00—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding
- F16B11/006—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding by gluing
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Health & Medical Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Rolling Contact Bearings (AREA)
Abstract
The invention relates to a method for preparing a heat-proof suit of a revolving body, which comprises the following steps: a. manufacturing a prefabricated body of the heat-proof structure (1); b. processing a molded surface and a supporting tool (2) of the prefabricated body; c. the heat-proof structure (1) and the side wall bearing structure (3) are subjected to trial assembly; d. the heat-proof structure (1) is sleeved with the side wall bearing structure (3). The invention can realize the high-precision assembly of the heat-proof structure and the side wall bearing structure.
Description
Technical Field
The invention relates to a method for preparing a heat-proof suit of a revolving body.
Background
The side wall structure of the small celestial body re-entry capsule is formed by combining and gluing a side wall heat-proof structure, a small-end heat-proof structure part and a re-entry capsule side wall force-bearing structure, the height of the whole capsule is 222mm, the height of the force-bearing structure is 207 +/-0.5 mm, the total height of the small-end heat-proof structure and a glue layer is 15mm, the height of the small-end heat-proof structure is 14mm, the height of the glue layer is 1mm, the maximum outer diameter phi 643mm of the large end of the side wall heat-proof structure, the diameter phi 634mm of the joint of the side wall heat-proof structure and the outsole, the thickness of the heat-proof structure is 8.5mm, the wall thickness of the force-bearing structure is 1mm, and the appearance half cone angle of the whole capsule is 31 +/-1'. The process characteristics and difficulties thereof exist in the following aspects:
firstly, the glue joint gap between the side wall heat-proof structure and the bearing structure is difficult to control. Namely, the side wall heat-proof structure glue interface is integrally processed and formed, the outer surface of the bearing structure is formed by 3D printing, and due to the difference of forming modes, the profile degrees of the glue joint surfaces of the two products are different, and the change of the glue joint gap can be caused by the difference of the profile degrees. Meanwhile, the glue applying amount uniformity of a glue joint interface in the sleeving process is difficult to control, the coaxiality of the heat-proof structure and the metal bearing structure in the sleeving process is difficult to control, and the thickness of a glue layer is difficult to guarantee. This makes it difficult to control the clearance between the heat shield structure and the load-carrying structure. In addition, the prior art also has difficulty in realizing nondestructive testing of the combined gluing process. Particularly, the lateral wall heat-proof structure is the toper type structure, adopts silicon rubber to glue between heat-proof structure and the bearing structure, because heat-proof structure is the porous state of light, leads to the rigidity lower, and the strike detection sound elasticity time difference of defect region and normal region is less, and detectivity is lower to be difficult to reach the detection demand. And the bearing structure is compact aluminum alloy with the thickness of 1mm, and the initial wave and the bottom wave are difficult to distinguish by the conventional pulse reflection contact ultrasonic, so the common plate bonding detection method is not suitable for the structure. Finally, although the ultrasonic phased array detection method can utilize linear focusing of sound waves to distinguish bottom wave attenuation caused by defects so as to realize defect detection of a planar product, the side wall heat release structure is a variable-curvature conical structure, and a complex convex structure exists in the side wall heat release structure, so that the detection of the bonding quality of an interface is difficult.
In the prior art, ultrasonic phased array probe reconstruction and experimental research are needed, and a nondestructive testing method for the glue joint quality after sleeving is explored. In addition, the existing heat-proof suit preparation is difficult to realize high-precision combined machining. Specifically, because the side wall heat-proof structure has a large number of characteristic dimensions and higher precision requirements, especially the characteristic dimension of the bearing structure reaches the design requirement value, and a large number of characteristics in the machining process of the heat-proof structure sleeving combination machine are all shielded by the heat-proof structure blank, so that the precision control in the machining process is difficult.
Disclosure of Invention
The invention aims to provide a method for preparing a heat-proof sleeve of a revolving body.
In order to realize the aim, the invention provides a method for preparing a heat-proof sleeve of a revolving body, which comprises the following steps:
a. manufacturing a prefabricated body of the heat-proof structure;
b. processing a molded surface and a supporting tool of the prefabricated body;
c. the heat-proof structure and the side wall bearing structure are subjected to trial assembly;
d. and sleeving the heat-proof structure with the side wall bearing structure.
According to one aspect of the present invention, in the step (a), the fabricating of the preform of the heat shielding structure includes molding, curing by dipping, and drying.
According to one aspect of the invention, the female die is formed, a fiber mesh tire is laid on the surface of the female die, the mesh tire layers are connected through needling, and flaw detection is carried out after the preform is formed;
preparing resin impregnation glue solution, placing the prefabricated body in an impregnation tool and sealing, gradually impregnating the resin glue solution from the bottom of the prefabricated body to the top of the prefabricated body through vacuumizing, and baking by using an oven until the glue solution forms gel;
cleaning the gel block at the periphery of the preform, and drying the preform.
According to an aspect of the present invention, in the step (b), the profile working of the preform includes:
placing the small end of the prefabricated part upwards on the table surface of a machine tool, and processing the end surface of the small end;
placing the small end of the prefabricated body downwards on the table top of a machine tool, and marking a table on the reference surface of the small end to align the center reference of the conical shaft;
processing the large end face of the prefabricated body, and uniformly processing 8 first positioning through holes with phi of 20mm at the periphery of the large end flanging according to an axis reference;
machining the inner molded surface of the prefabricated body according to the axis standard, wherein the machining size is 11mm, the half cone angle of the inner molded surface is 31 degrees (-1' -0), and the overall profile degree of the inner molded surface is 0.1 mm;
roughly milling when processing the inner profile of the prefabricated body, reserving 2mm of allowance, and then grinding to a processing size by using a grinding wheel, wherein the tool cutting amount of each tool is not more than 0.5 mm;
turning over the prefabricated body, aligning the axis according to the circle center of the first positioning through hole, and processing the outer molded surface;
and (4) processing the large end of the prefabricated body to be flanged, forming a heat-proof structure, and removing the clamp and the clearance.
And a positioning aluminum block is arranged at the opposite angle of the first positioning through hole on the 3 large flanging.
According to one aspect of the invention, in the step (b), the support tool is machined based on the pin holes at two positions of the large end of the side wall bearing structure, and a machining reference surface and quadrant marks are established on the upper surface and the lower surface of the flanging of the support tool.
According to one aspect of the invention, the bottom surface of the flanging of the supporting tool is processed, and the flatness is less than 0.1 mm;
turning over the supporting tool, aligning the axis according to the excircle of the small-end flanging, and processing two positioning pin holes of phi 5(0 +0.05) at a distance of 600 +/-0.02 mm;
processing a second positioning through hole with phi 4.5 at 8 positions at the position with the reference circle phi of 600mm, and matching the second positioning through hole with phi 5;
machining quadrant holes with phi 20 at 4 positions at a reference circle phi 850, and marking the quadrant holes on the surface of the tool;
machining a threaded through hole of M10 at 8 positions at a reference circle phi 764;
the upper surfaces of the small end and the large end of the processing supporting tool are 0.05mm in flatness, and the distance between the upper end surface and the lower end surface is 98 +/-0.1 mm.
According to one aspect of the invention, in the step (c), the sidewall load-bearing structure is cleaned by using alcohol or acetone;
connecting and fixing the side wall force-bearing structure with a support tool through a bottom large-end connecting hole by using an M4 screw, a nut and a positioning pin;
carrying out three-dimensional measurement on the profile degree of the surface of the side wall bearing structure to form a three-dimensional virtual model, and recording a profile value on the surface of the side wall bearing structure;
carrying out three-dimensional scanning measurement on the profile degree of the heat-proof structure to form a three-dimensional virtual model, and recording the profile degree value on the inner surface of the heat-proof structure;
virtually sleeving a three-dimensional scanning model of the side wall bearing structure and the heat-proof structure, adjusting the combination position of the side wall bearing structure and the heat-proof structure according to the contour degree value, and making contour degree adjustment marks on the surface of the side wall bearing structure;
according to the mark points and the contour value of the surface of the side wall bearing structure, a heat-proof material sheet with the thickness of 20 x 2mm is pasted at the mark position below-0.5 mm, then the whole grinding is carried out, and the contour value of the side wall bearing structure is corrected to (-0.5, 0) mm;
bonding 12K carbon wires in a marking area at the negative difference position of the side wall load-bearing structure, wherein the interval of the carbon wires is 10mm, measuring the height of the carbon wires after curing, polishing, and correcting the profile value meeting the marking area;
and (4) polishing the outer surface of the side wall bearing structure, and completely cleaning the upper end face and the lower end face by using alcohol or acetone.
According to one aspect of the invention, two layers of Teflon plugs are pasted on the large openings at 4 positions in the lateral direction of the periphery of the side wall force bearing structure, and Teflon cloth is pasted inside the small holes at 14 positions below the side wall force bearing structure and at the bottom edge for protection;
after the profile tolerance of the heat-proof structure and the side wall bearing structure is adjusted, the positioning pin penetrates through the first positioning through hole at the 3 flanged positions of the large end of the heat-proof structure, the bottom surface of the positioning pin is bonded and fixed with the surface of the supporting tool, the distance between the position of the first positioning through hole at the upper flanged position of the large end of the heat-proof structure and the plane of the supporting tool is measured, and the height limiting block is processed accordingly.
According to one aspect of the invention, the side wall force bearing structure corresponds to a support tool quadrant, and the large end is connected and fixed with the support tool through 2 positioning pins and 8 screws;
the opening at the side 4 of the surface of the side wall bearing structure, the hole at the lower part 14 and the upper and lower end surfaces of the side wall bearing structure are protected by Teflon.
The heat-proof structure is sleeved on the side wall bearing structure in a trial manner, so that the positioning pin penetrates through a hole with a positioning aluminum block at the large-end flanging of the heat-proof structure;
uniformly taking 8 points to measure gaps between the heat-proof structure and the side wall bearing structure, and adjusting the gaps to be 0.2 mm;
and measuring the distance between the typical position of the upper flanging of the large end of the heat-proof structure and the plane of the supporting tool, and processing a height limiting block with the same height as the distance.
According to one aspect of the invention, in said step (d), wiping the surface of the heat protecting structure with alcohol to remove the dirt;
brushing PR1200 base glue on the glue joint surface of the side wall bearing structure and the heat-proof structure, and airing for 0.5h at normal temperature;
winding first steel wires of 0.2mm on the surface of the side wall force bearing structure at intervals of 50mm, and winding second steel wires of 0.1mm on the inner surface of the heat-proof structure at intervals of 50mm along the circumferential direction;
as a component A (RTV 560): the weight ratio of the component B (DBT) is 100: 0.5, preparing RTV560 glue solution, wherein the component B is calculated according to 0.022g per drop, added dropwise, and fully and uniformly stirred;
the adhesive surface of the side wall bearing structure and the heat-proof structure is not less than 250g/m2Coating RTV560 glue and taking out the steel wire;
placing a supporting tool provided with a side wall bearing structure on the surface of a base of a sleeving pressurization tool, and placing a height limiting block on the surface of a flanging of the supporting tool;
enabling a first positioning through hole at the 3-position flanging of the large end of the heat-proof structure to penetrate through the 3-position positioning pin on the surface of the supporting tool;
a layer of steel plate is arranged between a pressure head of the sleeved pressurizing tool and the heat-proof structure, a pressure sensor is arranged at the center of the steel plate and the pressure head, and two layers of fluorine cloth are padded between the pressure sensor and the pressure head;
and (3) pressurizing the small end flanging by 10kg, if the heat-proof structure does not fall in the pressurizing process, placing a pressure equalizing aluminum plate on the surface of the large end flanging until the heat-proof structure is contacted with the height limiting block, so that the glue solution slowly flows out from one side of the large end, and then curing at room temperature for 24 hours.
And (5) carrying out physical and chemical detection on the sleeved structure, carrying out ultrasonic flaw detection on the glued joint surface, and issuing a detection report.
According to the scheme of the invention, in the process of manufacturing the suit of the heat-proof structure on the side wall of the return capsule, the inner molded surface of the heat-proof structure is firstly processed to reach the theoretical size, then the side wall bearing structure is connected with the supporting tool, the reference of the bearing structure is transferred to the surface of the supporting tool, and the contour of the glued surface is adjusted according to the contour of the side wall bearing structure. Then, the heat-proof structure and the side wall bearing structure are assembled in a trial mode, the glue joint gap is guaranteed, and then the position of the heat-proof structure is fixed with the supporting tool through the positioning pin. And then, the heat-proof structure and the side wall bearing structure are sleeved and glued, and the sleeved pressurizing tool and the large-end uniform plate are used for pressurizing and adjusting to meet the trial assembly state. And then, processing the heat-proof structure, removing the flanging, reserving 3mm allowance in the shape, then performing combined gluing on the small-end heat-proof structure component, and performing final size processing forming on the heat-proof structure and the small-end heat-proof structure component after the gluing is completed. Therefore, the sleeving process comprises the processes of machining the inner profile of the blank, trial sleeving the heat-proof structure, installing and machining the small-end heat-proof frame and the like, and the process implementation is mainly controlled according to the gluing gap and the profile tolerance, so that high-precision assembly is realized.
Drawings
FIG. 1 schematically illustrates a flow chart for forming a heat shield structure according to an embodiment of the present invention;
FIG. 2 is a view schematically showing the structure of a heat-shielding structural preform according to an embodiment of the present invention;
FIG. 3 schematically shows an X-ray inspection of a preform according to one embodiment of the invention;
FIGS. 4 and 5 are schematic views showing two views of a preform dip cured according to an embodiment of the present invention;
FIGS. 6 and 7 are schematic views showing two views of a preform drying process according to an embodiment of the present invention;
FIGS. 8 and 9 are two-stage flow charts schematically illustrating the sleeving and processing of a heat-proof structure and a side wall force-bearing structure according to an embodiment of the invention;
FIG. 10 is a schematic view showing a small end face machined in the method for manufacturing a heat shield for a rotating body according to an embodiment of the present invention;
fig. 11 is a schematic view showing the reference finding and the processing of the inner profile and the large end face in the method for manufacturing the heat-proof jacket of a revolving body according to the embodiment of the present invention;
FIG. 12 is a schematic view showing flanging at the outer surface and the large end surface in the method for manufacturing a heat-proof jacket of a revolving body according to an embodiment of the present invention;
FIGS. 13 and 14 are schematic views showing two views of a preform in accordance with an embodiment of the present invention;
FIGS. 15 and 16 are block diagrams schematically illustrating two views of positioning an aluminum block according to an embodiment of the present invention;
FIG. 17 is a schematic illustration of a position of a bonded positioned aluminum block in accordance with an embodiment of the present invention;
FIG. 18 is a schematic view of a support tool according to an embodiment of the invention with the large end facing upwards;
FIG. 19 is a schematic representation of a support tool dowel hole and quadrant hole machining of one embodiment of the present invention;
FIG. 20 is a schematic view of one embodiment of the present invention with the small end of the support tool facing up;
fig. 21 is a schematic diagram showing an external structure of a side wall bearing structure after being connected with a support tool according to an embodiment of the invention;
fig. 22 is a three-dimensional measurement diagram for the profile of a side wall load-bearing structure in an embodiment of the invention;
FIG. 23 schematically illustrates a three-dimensional measurement of the profile of a thermal protection structure in accordance with one embodiment of the present invention;
FIG. 24 schematically illustrates a virtual assembly drawing of a three-dimensional model of a thermal protection structure and a sidewall load-bearing structure in accordance with an embodiment of the present invention;
fig. 25 is a schematic diagram showing a side wall force-bearing structure contour degree measuring diagram according to an embodiment of the invention;
FIG. 26 is a schematic view of a side wall load-bearing structure contour correction and combined machining polishing according to an embodiment of the present invention;
FIG. 27 is a schematic representation of a profile adjustment of one embodiment of the present invention;
FIG. 28 is a cross-sectional view taken along line E-E of FIG. 27;
fig. 29 is a schematic view showing the surface hole treatment of a sidewall force-bearing structure according to an embodiment of the present invention;
fig. 30 is a schematic view showing protection of the position of the opening of the side wall bearing structure according to one embodiment of the invention;
FIG. 31 is a schematic illustration of a heat shield and support fixture positioning in accordance with an embodiment of the present invention;
FIG. 32 schematically illustrates a test set according to an embodiment of the invention.
FIG. 33 is a schematic view showing the arrangement of steel wires on the surface of a heat shielding structure according to an embodiment of the present invention;
fig. 34 is a schematic view showing the arrangement of steel wires on the surface of a side wall bearing structure according to one embodiment of the invention;
FIG. 35 is a schematic view showing the pressurization of the thermal protection structure with the side wall load-bearing structure according to one embodiment of the present invention;
fig. 36, 37 and 38 are schematic views of three views, respectively, during the fitting process in accordance with an embodiment of the present invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
In describing embodiments of the present invention, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in an orientation or positional relationship that is based on the orientation or positional relationship shown in the associated drawings, which is for convenience and simplicity of description only, and does not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus, the above-described terms should not be construed as limiting the present invention.
The present invention is described in detail below with reference to the drawings and the specific embodiments, which are not repeated herein, but the embodiments of the present invention are not limited to the following embodiments.
The method for preparing the revolved body heat-proof suit is suitable for the field of low-density heat protection structure forming and can be used for forming the heat protection structure of the revolved body return cabin of an asteroid detection and deep space detection aircraft. The method comprises the steps of firstly manufacturing a prefabricated body (blank) of the heat-proof structure 1, then processing a molded surface and a supporting tool 2 of the prefabricated body, then performing trial assembly on the heat-proof structure 1 and the side wall bearing structure 3, and finally performing assembly on the heat-proof structure 1 and the side wall bearing structure 3.
Referring to fig. 1, the fabrication of the preform of the heat shielding structure 1 includes molding, curing by dipping, and drying. In order to meet the design requirement of controlling the density of the side wall heat-proof structure 1, the forming control of the fiber preform and the uniformity control in the resin impregnation process of the preform are two important processes for ensuring that the density of the side wall heat-proof structure 1 meets the design requirement. Specifically, in the process of forming a preform of the NF3010 heat-proof structure 1, firstly, a female mold is formed according to the configuration size of a product, fiber mesh tires are laid on the surface of the female mold, and the mesh tire layers are connected through needling, so that the preform forms a three-dimensional mesh tire needled felt structure, as shown in fig. 2, the density, the needling depth, the needling density and the density uniformity of the mesh tire surface are strictly controlled in the forming process, the forming process is monitored, and the control of the density and the uniformity of the preform is realized.
And (3) after the preform is formed, the preform is subjected to flaw detection by a nondestructive testing means in a factory, and the internal forming quality of the preform is detected according to NF series heat-proof material X-ray detection Specifications (BYWYZ 0175). As shown in FIG. 3, the internal quality was good after flaw detection, and defects such as voids, inclusions, and density unevenness were not found. Then, according to the requirement of controlling the density of the side wall preform, in the preform impregnation process, calculating and configuring resin impregnation glue, and placing the molded fiber preform in an impregnation tool and sealing, as shown in fig. 4 and 5. And the resin glue solution is gradually impregnated from the bottom to the upper part of the prefabricated body to completely submerge the top of the prefabricated body by vacuumizing, so that the prefabricated body is fully and uniformly impregnated by the phenolic resin. And then, placing the whole tool in an oven D, baking by using the oven until the glue solution reacts to form gel, and finishing gum dipping and curing in the preform. Wherein the weight change during the preform impregnation is shown in the following table 1:
TABLE 1 recording table of impregnation process of preform
And finally, after the gel reaction of the preform is finished, disassembling the dipping tool, cleaning redundant gel blocks on the periphery of the preform, then placing the treated preform in the tool for drying treatment, and connecting the preform with a thermocouple C, as shown in fig. 6 and 7, thereby finishing the molding preparation of the NF3010 heat-proof structure 1. Wherein, the data of the blank drying process are shown in the following table 2:
table 2 record table of blank drying process
And then, in order to meet the requirement of the glue joint gap between the heat-proof structure 1 of the side wall structure and the force-bearing structure 3 of the side wall, namely, in the suit glue joint process, the glue joint quality control of the glue joint gap between the heat-proof structure 1 and the force-bearing structure 3 of the side wall is also carried out. According to the technical requirements of the sleeving of the lateral wall structure of the re-entry capsule, a technical scheme of the sleeving of the heat-proof structure 1 and the bearing structure, the installation of the small-end heat-proof assembly, the integral processing and the like is formulated, as shown in fig. 8 and 9.
According to the invention, the assembly is tried before assembly, the gap between the heat-proof structure 1 and the side wall bearing structure 3 is uniformly adjusted, the height position between the end of the heat-proof structure 1 and the plane of the tool is determined, and finally the gluing assembly state and the pressurizing in-place position are determined. In the gluing process, steel wires with the same height are uniformly spread on the surface of the heat-proof structure 1 and the surface of the side wall force bearing structure 3 of the gluing layer to control the uniformity and thickness of gluing. The sleeving process adopts a special sleeving tool for pressurization, the heat-proof structure 1 is sleeved on the side wall bearing structure 3 along the positioning pin 23 of the sleeving tool, and the pressing head of the sleeving tool is used for spinning to the height position confirmed by the trial sleeving to complete the sleeving.
In the processing of the profile of the prefabricated body, according to the characteristics and the processing requirements of the heat-proof structure 1, a route of firstly performing rough processing and then performing finish processing is adopted. Wherein, during rough machining, a 32 diamond ball cutter is adopted, the rotating speed is 3500r/min, the feed is 3000mm, the cutting depth is 2mm, during finish machining, a diamond particle grinding head is adopted, the rotating speed is 3500r/min, the feed is 1500mm, and the grinding amount is 0.5-1 mm.
Referring to fig. 10 to 12, first, the small end of the preform is placed on the table of the machine tool with the small end facing upward, and the small end face 1a is roughly swept to be flat. And then placing the small end of the prefabricated body downwards on the table top of the machine tool, and using the small end datum plane A to make a table to align the conical shaft center datum B. And then, processing the large end surface 1B of the prefabricated body, and processing 8 first positioning through holes 11 with phi of 20mm uniformly at the periphery of the large end flanging according to the axis reference B for subsequently installing and positioning aluminum blocks 12. The inner profile 1c of the preform was machined to a dimension of 11mm based on the axis reference B so that the half-cone angle of the inner profile was 31 ° (-1' -0) and the overall profile of the inner profile was 0.1 mm. Wherein, when processing the inner profile of the prefabricated body, rough milling is carried out firstly, 2mm allowance is left, then grinding is carried out by adopting a grinding wheel until the processing size is reached, and the tool cutting amount of each tool is not more than 0.5 mm. And then, turning the prefabricated body, aligning the axis according to the circle center of the first positioning through hole 11 at the position 8, processing the outer molded surface, and flattening. Subsequently, the upturn 1E of the large end face of the preform is processed to form the heat-proof structure 1, and the heat-proof structure is unclamped and cleaned, and the preform is provided with a check template E inside, as shown in fig. 13 and 14. Finally, as shown in fig. 15 and 17, 3 diagonal positions are selected from the 8 first positioning through holes 11 of the large-end flanging, and the aluminum block 12 is positioned by adopting J-133 glue joint.
Referring to fig. 18 to 21, the support tool 2 is processed and the side wall load-bearing structure 3 is installed. Specifically, a datum is established on the surface of the support tool 2, namely the support tool 2 is machined by taking pin holes at two positions of the large end of the side wall bearing structure 3 as a datum, and a machining datum plane and an quadrant hole 21 are established on the upper surface and the lower surface of a flanging of the support tool 2. Then, the bottom surface of the flanging of the supporting tool 2 is processed, and the flatness is better (smaller) than 0.1 mm. Then the supporting tool 2 is turned over, the axis is aligned according to the small end flanging excircle, and two positioning pin holes 24 with phi 5(0 +0.05) are processed according to requirements, wherein the distance is 600 +/-0.02 mm. Then, uniformly processing 8 phi 4.5 second positioning through holes 22 at the position of the reference circle phi 600mm, and matching with phi 5 positioning pins 23; and machining 4 phi 20 quadrant holes 21 at the positions with the reference circles phi 850 to ensure that the reference circles where the quadrant holes 21 are located are concentric with the reference circle where the second positioning through hole 22 is located, and making quadrant marks on the surface of the tool for later use. The threaded through hole 26 of M10 at 8 is machined at reference circle Φ 764. The upper surfaces of the small end and the large end of the processing supporting tool 2 are 0.05mm in flatness, and the distance between the upper end surface and the lower end surface is 98 +/-0.1 mm. Then, the side wall force bearing structure 3 is cleaned completely by using alcohol or acetone. And the side wall force-bearing structure 3 is fixedly connected with the support tool 2 through a bottom large-end connecting hole by adopting an M4 screw, a nut and a phi 5 positioning pin 23.
Referring to fig. 22 to 24, subsequently, the contour degree detection and correction of the side wall force-bearing structure 3 and the heat protection structure 1 are performed. Specifically, the surface of the side wall force bearing structure 3 is subjected to three-dimensional measurement of the profile degree to form a three-dimensional virtual model, and a profile value is recorded on the surface of the structure; and (3) carrying out three-dimensional scanning measurement on the profile tolerance of the heat-proof structure 1 to form a three-dimensional virtual model, and recording the profile tolerance on the inner surface of the heat-proof structure 1. The three-dimensional scanning model of the side wall bearing structure 3 and the heat-proof structure 1 is virtually sleeved, the optimal combination position of the side wall bearing structure 3 and the heat-proof structure 1 is adjusted according to the profile value, the surface of the side wall bearing structure 3 is marked with profile adjustment marks, and a detection point F is shown in figure 25. According to the contour detection of the side wall bearing structure 3, if the contour of the whole circle of the edge of the large end and the contour of the local part of the middle part do not meet the requirement of the contour (-0.5, 0) mm, the side wall bearing structure 3 does not have the state of being sleeved and glued with the heat-proof structure 1. According to the content of the harmonizing single XTT-1.XT21002170, the material which is the same as that of the heat-proof structure 1 is adopted to carry out contour degree correction on the side wall force-bearing structure 3. According to the metal surface mark points and the contour value of the side wall force-bearing structure 3, 20 × 2mmNF3010 heat-proof material sheets G (or called repair sheets) are attached to the mark positions smaller than minus 0.5mm, then the whole machine is polished to ensure the contour of the side wall force-bearing structure 3 repaired by the heat-proof material, the contour of the side wall force-bearing structure 3 is corrected to minus 0.5, 0mm, and the states before and after the correction of the side wall force-bearing structure 3 are shown in fig. 26 to 28.
Referring to fig. 27 and 28, 12K carbon wires 31 are adhered and paved on a marking area at the negative difference position of the side wall force bearing structure 3 by using J-133 glue, the carbon wires 31 are arranged at intervals of 10mm, the height of the carbon wires 31 is measured and polished after curing, and the contour value meeting the marking area is corrected. The outer surface of the side wall bearing structure 3 is fully polished, the upper end face and the lower end face are protected during polishing, and the upper end face and the lower end face are fully cleaned by using alcohol or acetone.
Referring to fig. 29 and 30, the corresponding side wall force-bearing structure 3 of the invention is provided with a large round hole 33, a square hole 34, an elliptical hole 35 and a small round hole 36. The invention carries out corresponding treatment on the open pore on the surface of the metal cabin. Specifically, two layers of Teflon plugs are attached to large openings at 4 positions on the lateral side of the side wall force bearing structure 3, so that glue pollution is prevented. And finally, attaching Teflon cloth to the inner part and the bottom edge of the small hole 14 below the wall of the side wall force bearing structure 3 for protection for later use. Subsequently, the profile tolerance of the heat-proof structure 1 and the side wall force-bearing structure 3 is adjusted, the positioning pin 23 penetrates through the first positioning through hole 11 at the 3 flanged large end of the heat-proof structure 1, the bottom surface of the positioning pin 23 is bonded and fixed with the surface of the supporting tool 2, the distance between the position of the first positioning through hole 11 flanged on the large end of the heat-proof structure 1 and the plane of the supporting tool 2 is measured, and the height limiting block 4 is processed accordingly. When specifically carrying out the suit of heat protection structure 1 and 3 try on of lateral wall load-bearing structure, correspond lateral wall load-bearing structure 3 with support frock 2 quadrants, the main aspects is connected fixedly through 2 locating pins 23 and 8 screws and support frock 2. Openings at the side 4 of the surface of the side wall force-bearing structure 3, holes at the lower part 14, the upper end surface and the lower end surface of the side wall force-bearing structure 3 and the like are protected by Teflon to prevent glue solution pollution, as shown in figure 30.
Referring to fig. 31, the heat protection structure 1 is fitted on the side wall force-bearing structure 3, so that the positioning pin 23 (or referred to as a guide pin) passes through the first positioning through hole 11 with the positioning aluminum block 12 at three positions of the large-end flange of the heat protection structure 1, and the bottom surface of the positioning pin 23 is bonded and fixed with the surface of the support tool 2 by using 502 glue. Evenly get 8 points and measure the clearance between 1 and the lateral wall load-carrying structure 3 of heat protection structure to it is unanimous to adjust clearance to 8 point position clearances, and final dimension is: 0.2mm, 0.2mm, 0.2mm, 0.2mm, 0.2mm, 0.2mm, 0.2mm, 0.2 mm. Subsequently, the distance between the typical position of the upturn at the large end of the heat protection structure 1 (i.e. the position of the opening at 8) and the plane of the support tool 2 is measured, and height-limiting blocks 4 at different positions with the same height as the distance are processed according to the distance for standby, and the trial-assembly state is shown in fig. 32.
Referring to fig. 33 to 35, after the adjustment of the profile degrees of the heat protection structure 1 and the side wall load-bearing structure 3, the heat protection structure 1 and the side wall load-bearing structure 3 are sleeved. Specifically, the heat-proof structure 1 is wiped with alcohol to remove dirt on the surface for standby. Brushing a layer of PR1200 base glue on the glue joint surface of the side wall bearing structure 3 and the heat-proof structure 1, and airing at normal temperature for 0.5h to dry the base glue for later use. The first steel wires 32 with the interval of 50mm are uniformly wound and fixed on the surface of the side wall force bearing structure 3, and the second steel wires 12 with the interval of 0.1mm are wound and fixed on the inner surface of the heat-proof structure 1 along the generatrix ring direction with the interval of 50 mm. As a component A (RTV 560): the weight ratio of the component B (DBT) is 100: 0.5, preparing RTV560 glue solution, wherein the component B is calculated according to 0.022g of each drop, added dropwise and fully stirred until the color is uniform visually. In thatThe adhesive surface of the side wall bearing structure 3 and the heat-proof structure 1 is not less than 250g/m2The RTV560 glue is applied evenly and the wire is then taken out ready for sheathing.
And then, placing the supporting tool 2 provided with the side wall force bearing structure 3 in the center of the surface of the base 61 of the sleeving pressurization tool 6, and placing the height limiting block 4 on the surface of a flanging of the supporting tool 2. And (3) penetrating three first positioning through holes 11 of the large-end flanging of the heat-proof structure 1 through three positioning pins 23 on the surface of the supporting tool 2, so that the heat-proof structure is sleeved on the surface of the side wall force-bearing structure 3. A layer of steel plate 63 is arranged between a pressure head 62 of the sleeving and pressurizing tool 6 and the heat-proof structure 1, a pressure sensor 64 is arranged at the center of the steel plate 63 and the pressure head 62, and two layers of fluorine cloth are padded between the pressure sensor 64 and the pressure head 62 to avoid the rotation of a pressurizing process sensor. Make heat-proof structure 1 along suit locating pin 23 natural location on metallic structure, utilize the pressure head 62 of frock upper end to the tip turn-ups of tip slowly pressurize 10kg, if the heat-proof structure of pressurization process 1 does not have the decline, then place pressure-equalizing aluminum plate 66 on big end turn-ups surface, be connected bolt 661 on the pressure-equalizing aluminum plate 66 with the screw thread through-hole 26 that supports the frock 2 surfaces, the symmetry fastening bolt all around, adjust the height of big end turn-ups and support frock 2 through pressure-equalizing aluminum plate 66, until heat-proof structure 1 reaches height limiting block 4 positions and contacts with it, the suit pressurization stops, the suit is accomplished. The entire process takes about 50 minutes and the glue package is completed before the glue begins to cure (about 2 hours), as shown in fig. 36-38. And finally, enabling the glue solution to slowly flow out from the large end side, wherein the glue solution overflow area H is as shown in figure 37, timely cleaning the glue solution in the period, and curing for 24 hours at room temperature. And then, carrying out physical and chemical detection on the sleeved structure, carrying out ultrasonic flaw detection on the glued joint surface, and issuing a detection report.
The above description is only one embodiment of the present invention, and is not intended to limit the present invention, and it is apparent to those skilled in the art that various modifications and variations can be made in the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A method for preparing a heat-proof sleeve of a revolving body comprises the following steps:
a. manufacturing a prefabricated body of the heat-proof structure (1);
b. processing a molded surface and a supporting tool (2) of the prefabricated body;
c. the heat-proof structure (1) and the side wall bearing structure (3) are subjected to trial assembly;
d. the heat-proof structure (1) is sleeved with the side wall bearing structure (3).
2. The method according to claim 1, wherein in the step (a), the fabricating of the preform of the heat shielding structure (1) comprises molding, dip curing and drying.
3. The method of claim 2, wherein the female mold is formed, a fiber mesh is laid on the surface of the female mold, the mesh layers are connected by needling, and the preform is inspected after being formed;
preparing resin impregnation glue solution, placing the prefabricated body in an impregnation tool and sealing, gradually impregnating the resin glue solution from the bottom of the prefabricated body to the top of the prefabricated body through vacuumizing, and baking by using an oven until the glue solution forms gel;
cleaning the gel block at the periphery of the preform, and drying the preform.
4. The method of claim 1, wherein in step (b), the profiling of the preform comprises:
placing the small end of the prefabricated part upwards on the table surface of a machine tool, and processing the end surface of the small end;
placing the small end of the prefabricated body downwards on the table top of a machine tool, and marking a table on the reference surface of the small end to align the center reference of the conical shaft;
processing the end face of the large end of the prefabricated body, and uniformly processing 8 first positioning through holes (11) with phi of 20mm at the periphery of the large end flanging according to the axis reference;
machining the inner molded surface of the prefabricated part according to the axis standard, wherein the machining size is 11mm, the half cone angle of the inner molded surface is 31 degrees, and the overall profile degree of the inner molded surface is 0.1 mm;
roughly milling when processing the inner profile of the prefabricated body, reserving 2mm of allowance, and then grinding to a processing size by using a grinding wheel, wherein the tool cutting amount of each tool is not more than 0.5 mm;
turning over the prefabricated body, aligning the axis according to the circle center of the first positioning through hole (11), and processing an outer molded surface;
and (3) processing the large end of the prefabricated body to be turned up to form a heat-proof structure (1), and unloading and cleaning.
And a positioning aluminum block (12) is arranged at the opposite angle of the first positioning through hole (11) on the large flanging at the position 3.
5. The method according to claim 1, characterized in that in the step (b), the support tool (2) is machined according to pin holes at two large ends of the side wall force bearing structure (3) as references, and machining reference surfaces and quadrant marks are established on the upper and lower surfaces of a flanging of the support tool (2).
6. The method according to claim 5, characterized in that the bottom surface of the flanging of the supporting tool (2) is processed, and the flatness is less than 0.1 mm;
turning the supporting tool (2), aligning the axis according to the small end flanging excircle, and processing two positioning pin holes (24) with the diameter of phi 5 at the distance of 600 +/-0.02 mm;
processing a second positioning through hole (22) with phi 4.5 at 8 positions at the position with the reference circle phi 600mm, and matching with a positioning pin (23) with phi 5;
machining a quadrant hole (21) with phi 20 at the position of 4 at the position of a reference circle phi 850, and marking a quadrant on the surface of the tool;
machining a threaded through hole (26) of M10 at 8 at a reference circle phi 764;
the upper surfaces of the small end and the large end of the processing supporting tool (2) are 0.05mm in flatness, and the distance between the upper end surface and the lower end surface is 98 mm.
7. The method according to claim 1, wherein in the step (c), the sidewall load-bearing structure (3) is cleaned with alcohol or acetone;
connecting and fixing the side wall force-bearing structure (3) with the support tool (2) through a bottom large-end connecting hole by adopting an M4 screw, a nut and a positioning pin (23);
carrying out three-dimensional measurement on the surface of the side wall bearing structure (3) to form a three-dimensional virtual model, and recording a contour value on the surface of the side wall bearing structure (3);
carrying out three-dimensional scanning measurement on the profile degree of the heat-proof structure (1) to form a three-dimensional virtual model, and recording the profile degree value on the inner surface of the heat-proof structure (1);
virtually sleeving a three-dimensional scanning model of the side wall bearing structure (3) and the heat-proof structure (1), adjusting the combination position of the side wall bearing structure (3) and the heat-proof structure (1) according to the contour degree value, and making contour degree adjustment marks on the surface of the side wall bearing structure (3);
according to the mark points and the profile value of the surface of the side wall bearing structure (3), 20-2 mm heat-proof material sheets are pasted at the mark positions below-0.5 mm, then the whole grinding is carried out, and the profile value of the side wall bearing structure is corrected to (-0.5, 0) mm;
bonding 12K carbon wires (31) in a marking area at the negative difference position of the side wall bearing structure (3), wherein the interval between the carbon wires (31) is 10mm, measuring the height of the carbon wires (31) after curing, polishing and correcting the profile value meeting the marking area;
and (3) polishing the outer surface of the side wall bearing structure (3), and completely cleaning the upper end face and the lower end face by using alcohol or acetone.
8. The method of claim 7, characterized in that two layers of Teflon plugs are stuck to the large opening 4 of the lateral wall force-bearing structure (3) in the lateral direction, and Teflon cloth is stuck to the inner part and the bottom edge of the small hole 14 under the lateral wall force-bearing structure (3);
after the profile tolerance of the heat-proof structure (1) and the side wall bearing structure (3) is adjusted, the positioning pin (23) penetrates through the first positioning through hole (11) at the 3 positions of the large-end flanging of the heat-proof structure (1), the bottom surface of the positioning pin (23) is fixedly bonded with the surface of the supporting tool (2), the distance between the position of the first positioning through hole (11) at the large end of the heat-proof structure (1) and the plane of the supporting tool (2) is measured, and the height limiting block (4) is processed accordingly.
9. The method according to claim 8, characterized in that the side wall force-bearing structure (3) corresponds to the support tool (2) in quadrant, and the large end is connected and fixed with the support tool (2) through 2 positioning pins (23) and 8 screws;
openings are arranged at the lateral direction 4 of the surface of the side wall force bearing structure (3), holes are arranged at the lower part 14, and the upper end surface and the lower end surface of the side wall force bearing structure (3) are protected by Teflon.
The heat-proof structure (1) is sleeved on the side wall bearing structure (3) in a trial manner, so that the positioning pin (23) penetrates through a hole with a positioning aluminum block (12) at the large-end flanging of the heat-proof structure (1);
uniformly taking 8 points to measure the gaps between the heat-proof structure (1) and the side wall bearing structure (3), and adjusting the gaps to be 0.2 mm;
and (3) measuring the distance between the typical position of the upturning edge at the large end of the heat-proof structure (1) and the plane of the supporting tool (2), and processing a height limiting block (4) equal to the distance.
10. The method according to claim 1, wherein in step (d), the surface of the heat protective structure (1) is wiped with alcohol to remove dirt;
brushing PR1200 base glue on the glue joint surface of the side wall bearing structure (3) and the heat-proof structure (1), and airing at normal temperature for 0.5 h;
the first steel wire (32) with the interval of 50mm and the 0.2mm is wound on the surface of the side wall force bearing structure (3), and the second steel wire (12) with the interval of 50mm and the 0.1mm is wound on the inner surface of the heat-proof structure (1) along the circumferential direction;
according to the weight ratio of the component A RTV560 to the component B DBT of 100: 0.5, preparing RTV560 glue solution, wherein the component B is calculated according to 0.022g per drop, added dropwise, and fully and uniformly stirred;
the adhesive surface of the side wall bearing structure (3) and the heat-proof structure (1) is not less than 250g/m2Coating RTV560 glue and taking out the steel wire;
placing a supporting tool (2) provided with a side wall bearing structure (3) on the surface of a base (61) of a sleeving pressurization tool (6), and placing a height limiting block (4) on the surface of a flanging of the supporting tool (2);
enabling a first positioning through hole (11) at the large-end flanging 3 of the heat-proof structure (1) to penetrate through a positioning pin (23) at 3 on the surface of the supporting tool (2);
a layer of steel plate (63) is arranged between a pressure head (62) of the sleeved pressurizing tool (6) and the heat-proof structure (1), a pressure sensor (64) is arranged at the center of the steel plate (63) and the pressure head (62), and two layers of fluorine cloth are padded between the pressure sensor (64) and the pressure head (62);
and (3) pressurizing the small end flanging by 10kg, if the heat-proof structure (1) does not fall in the pressurizing process, placing a pressure equalizing aluminum plate (66) on the surface of the large end flanging until the heat-proof structure (1) is contacted with the height limiting block (4), so that glue solution slowly flows out from one side of the large end, and then curing at room temperature for 24 hours.
And (5) carrying out physical and chemical detection on the sleeved structure, carrying out ultrasonic flaw detection on the glued joint surface, and issuing a detection report.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111368773.1A CN114229044B (en) | 2021-11-18 | 2021-11-18 | Preparation method of revolving body heat-proof suit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111368773.1A CN114229044B (en) | 2021-11-18 | 2021-11-18 | Preparation method of revolving body heat-proof suit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114229044A true CN114229044A (en) | 2022-03-25 |
| CN114229044B CN114229044B (en) | 2023-07-25 |
Family
ID=80749951
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111368773.1A Active CN114229044B (en) | 2021-11-18 | 2021-11-18 | Preparation method of revolving body heat-proof suit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114229044B (en) |
Citations (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19832441C1 (en) * | 1998-07-18 | 2000-01-05 | Daimler Chrysler Aerospace | Stringer-reinforced shell production with double curvature using fibrous composite materials, without risk of warping |
| WO2002055954A2 (en) * | 2000-08-29 | 2002-07-18 | Hrl Laboratories, Llc | Method for obtaining reduced thermal flux in a composite |
| US20030052132A1 (en) * | 2001-09-20 | 2003-03-20 | A. Raymond & Cie | Sealing cover for a processing hole in aluminum sheet metal |
| US6692681B1 (en) * | 1997-01-29 | 2004-02-17 | Raytheon Aircraft Company | Method and apparatus for manufacturing composite structures |
| WO2008041556A1 (en) * | 2006-09-29 | 2008-04-10 | Toray Industries, Inc. | Shaping mold and process for the production of preforms and fiber-reinforced plastics with the mold |
| WO2014080216A1 (en) * | 2012-11-22 | 2014-05-30 | Mantaray Innovations Limited | Flexible pipe and coupling therefor |
| CN103950205A (en) * | 2014-03-18 | 2014-07-30 | 沈阳飞机工业（集团）有限公司 | Molding method of composite material part with T-shaped cross section annular revolving body structure |
| CN104369874A (en) * | 2014-10-28 | 2015-02-25 | 上海卫星工程研究所 | Integrated heat control device for aircraft with complex external strength bearing cylinder structure |
| CN104494276A (en) * | 2014-12-18 | 2015-04-08 | 北京卫星制造厂 | Honeycomb core end surface gridding sizing process method based on adhesive film thermal fracture |
| CN104875316A (en) * | 2015-06-15 | 2015-09-02 | 湖北三江航天江北机械工程有限公司 | Shaping method of sealing gasket between windows and covering cap of cone-cylinder-shaped thermal shield |
| CN105034355A (en) * | 2015-06-26 | 2015-11-11 | 上海复合材料科技有限公司 | Preparing method of bearing cylinder |
| US9440752B1 (en) * | 2013-03-14 | 2016-09-13 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration (Nasa) | Modification of surface density of a porous medium |
| JP2017114401A (en) * | 2015-12-25 | 2017-06-29 | 三菱航空機株式会社 | Pinching sheet of aircraft high temperature duct and structural member, aircraft duct, and aircraft |
| CN107328316A (en) * | 2017-08-16 | 2017-11-07 | 精功（绍兴）复合材料技术研发有限公司 | Preparation method of aerospace projectile body heat-proof structure |
| CN107514932A (en) * | 2016-06-17 | 2017-12-26 | 浙江鑫宙竹基复合材料科技有限公司 | Launch canister cylinder |
| CN108995243A (en) * | 2018-06-20 | 2018-12-14 | 航天材料及工艺研究所 | A kind of winding, molding method of taper mutation heat shield |
| CN109175236A (en) * | 2018-09-13 | 2019-01-11 | 湖北三江航天红阳机电有限公司 | The tapered whole shell section casting and molding method of large thin-wall aluminum alloy round |
| CN109263160A (en) * | 2018-07-23 | 2019-01-25 | 机械科学研究总院集团有限公司 | A kind of anti-heat-insulation composite material precursor structure of heterogenous multilayer and forming technology |
| CN109335028A (en) * | 2018-11-28 | 2019-02-15 | 航天材料及工艺研究所 | A kind of mars exploration landing rover solar heat protection outsole and its molding, assembly method |
| CN110027229A (en) * | 2019-04-04 | 2019-07-19 | 北京卫星制造厂有限公司 | A kind of defect mending method based on the integrally formed heat insulation material of recoverable airship |
| CN112303078A (en) * | 2020-09-30 | 2021-02-02 | 上海复合材料科技有限公司 | Glue joint assembly die for cylinder assembly and assembly method thereof |
| CN112916878A (en) * | 2021-01-22 | 2021-06-08 | 西安国宏天易智能科技有限公司 | Additive manufacturing ring-shaped part shape righting method |
| CN112975404A (en) * | 2021-02-08 | 2021-06-18 | 航天材料及工艺研究所 | Device and method for machining semi-conical wave-transparent radome |
| CN113401362A (en) * | 2020-03-16 | 2021-09-17 | 上海梅卿传媒集团有限公司 | Highly-generalized and light media micro-nano satellite structure platform |
| CN113501145A (en) * | 2021-07-07 | 2021-10-15 | 北京空间飞行器总体设计部 | Thermal protection device capable of adapting to various air pressure environments and forming method and design method thereof |
-
2021
- 2021-11-18 CN CN202111368773.1A patent/CN114229044B/en active Active
Patent Citations (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6692681B1 (en) * | 1997-01-29 | 2004-02-17 | Raytheon Aircraft Company | Method and apparatus for manufacturing composite structures |
| DE19832441C1 (en) * | 1998-07-18 | 2000-01-05 | Daimler Chrysler Aerospace | Stringer-reinforced shell production with double curvature using fibrous composite materials, without risk of warping |
| WO2002055954A2 (en) * | 2000-08-29 | 2002-07-18 | Hrl Laboratories, Llc | Method for obtaining reduced thermal flux in a composite |
| US20030052132A1 (en) * | 2001-09-20 | 2003-03-20 | A. Raymond & Cie | Sealing cover for a processing hole in aluminum sheet metal |
| WO2008041556A1 (en) * | 2006-09-29 | 2008-04-10 | Toray Industries, Inc. | Shaping mold and process for the production of preforms and fiber-reinforced plastics with the mold |
| WO2014080216A1 (en) * | 2012-11-22 | 2014-05-30 | Mantaray Innovations Limited | Flexible pipe and coupling therefor |
| US9440752B1 (en) * | 2013-03-14 | 2016-09-13 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration (Nasa) | Modification of surface density of a porous medium |
| CN103950205A (en) * | 2014-03-18 | 2014-07-30 | 沈阳飞机工业（集团）有限公司 | Molding method of composite material part with T-shaped cross section annular revolving body structure |
| CN104369874A (en) * | 2014-10-28 | 2015-02-25 | 上海卫星工程研究所 | Integrated heat control device for aircraft with complex external strength bearing cylinder structure |
| CN104494276A (en) * | 2014-12-18 | 2015-04-08 | 北京卫星制造厂 | Honeycomb core end surface gridding sizing process method based on adhesive film thermal fracture |
| CN104875316A (en) * | 2015-06-15 | 2015-09-02 | 湖北三江航天江北机械工程有限公司 | Shaping method of sealing gasket between windows and covering cap of cone-cylinder-shaped thermal shield |
| CN105034355A (en) * | 2015-06-26 | 2015-11-11 | 上海复合材料科技有限公司 | Preparing method of bearing cylinder |
| JP2017114401A (en) * | 2015-12-25 | 2017-06-29 | 三菱航空機株式会社 | Pinching sheet of aircraft high temperature duct and structural member, aircraft duct, and aircraft |
| CN107514932A (en) * | 2016-06-17 | 2017-12-26 | 浙江鑫宙竹基复合材料科技有限公司 | Launch canister cylinder |
| CN107328316A (en) * | 2017-08-16 | 2017-11-07 | 精功（绍兴）复合材料技术研发有限公司 | Preparation method of aerospace projectile body heat-proof structure |
| CN108995243A (en) * | 2018-06-20 | 2018-12-14 | 航天材料及工艺研究所 | A kind of winding, molding method of taper mutation heat shield |
| CN109263160A (en) * | 2018-07-23 | 2019-01-25 | 机械科学研究总院集团有限公司 | A kind of anti-heat-insulation composite material precursor structure of heterogenous multilayer and forming technology |
| CN109175236A (en) * | 2018-09-13 | 2019-01-11 | 湖北三江航天红阳机电有限公司 | The tapered whole shell section casting and molding method of large thin-wall aluminum alloy round |
| CN109335028A (en) * | 2018-11-28 | 2019-02-15 | 航天材料及工艺研究所 | A kind of mars exploration landing rover solar heat protection outsole and its molding, assembly method |
| CN110027229A (en) * | 2019-04-04 | 2019-07-19 | 北京卫星制造厂有限公司 | A kind of defect mending method based on the integrally formed heat insulation material of recoverable airship |
| CN113401362A (en) * | 2020-03-16 | 2021-09-17 | 上海梅卿传媒集团有限公司 | Highly-generalized and light media micro-nano satellite structure platform |
| CN112303078A (en) * | 2020-09-30 | 2021-02-02 | 上海复合材料科技有限公司 | Glue joint assembly die for cylinder assembly and assembly method thereof |
| CN112916878A (en) * | 2021-01-22 | 2021-06-08 | 西安国宏天易智能科技有限公司 | Additive manufacturing ring-shaped part shape righting method |
| CN112975404A (en) * | 2021-02-08 | 2021-06-18 | 航天材料及工艺研究所 | Device and method for machining semi-conical wave-transparent radome |
| CN113501145A (en) * | 2021-07-07 | 2021-10-15 | 北京空间飞行器总体设计部 | Thermal protection device capable of adapting to various air pressure environments and forming method and design method thereof |
Non-Patent Citations (3)
| Title |
|---|
| 刘强;崔赢午;陈志会;李妍;: "高气动加热环境下运载器局部防热设计与试验研究", 强度与环境, no. 01, pages 54 - 59 * |
| 吴国庭: "防热结构的局部防热研究", 中国空间科学技术, no. 01, pages 215 - 218 * |
| 王洪雨: "某型快速响应微小卫星平台结构研制", 航天制造技术, pages 64 - 68 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114229044B (en) | 2023-07-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110171579B (en) | Method for deeply repairing metal honeycomb structural part | |
| CN112077310B (en) | Method and tool for repairing tip of turbine rotor blade made of monocrystalline and directional solidification materials | |
| CN114060369B (en) | Bonding assembly tool and bonding method for radome and connecting ring | |
| CN114229044A (en) | Method for preparing heat-proof suit of revolving body | |
| CN109335028B (en) | Heat-proof outsole for Mars detection landing patrol and forming and assembling method thereof | |
| JP7144139B2 (en) | Method for preparing a wrinkle reference standard for inspection of composite structures | |
| CN108381188B (en) | Tool and method for repairing and grinding central hole of output shaft of aero-engine | |
| CN111299615B (en) | Machining method for aviation thin-wall part based on machine-clamp integrated clamping | |
| CN110285745B (en) | Method and system for detecting profile of rigid aerogel special-shaped component | |
| CN113001121A (en) | Processing method of titanium alloy bowl-shaped thin-wall part | |
| CN110666448B (en) | Method for forming small-caliber large-curvature ultra-precise antenna panel | |
| CN112157497B (en) | Precision grinding and polishing method for inner hole of large-diameter glass cylindrical window | |
| CN108569303B (en) | railway vehicle external wall panel mounting method | |
| CN110480076B (en) | Honeycomb core part machining method based on boss fixing | |
| CN115582879B (en) | Honeycomb core prefabrication method | |
| US4737211A (en) | Process for fabrication of graphite/epoxy tools | |
| CN115673691B (en) | Propellant storage tank flange shape and mounting hole precision mounting guaranteeing method | |
| CN113334511B (en) | Production process of decorative special-shaped density board | |
| CN117583847A (en) | Processing method of composite material-metal laminated irregular thin-wall cabin section | |
| CN213828715U (en) | Quick composite clamp | |
| CN117564751A (en) | Composite material-metal laminated irregular thin-wall cabin section machining tool | |
| CN114986325B (en) | Optical element full-caliber polishing local area constant temperature processing device and polishing machine | |
| CN111745475B (en) | Automatic trimming device for inner cavity of slender rod made of carbon fiber composite material and using method | |
| CN115847839A (en) | Method for controlling quality of frame sealing at end of large-sized bearing cylinder | |
| CN107175836B (en) | The production method of beam warper glass pressure roller |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |