CN115673691A - Propellant storage tank flange appearance and mounting hole precision mounting guaranteeing method - Google Patents
Propellant storage tank flange appearance and mounting hole precision mounting guaranteeing method Download PDFInfo
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- CN115673691A CN115673691A CN202211438051.3A CN202211438051A CN115673691A CN 115673691 A CN115673691 A CN 115673691A CN 202211438051 A CN202211438051 A CN 202211438051A CN 115673691 A CN115673691 A CN 115673691A
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Abstract
The application relates to the technical field of storage tank processing and manufacturing, in particular to a propellant storage tank flange appearance and mounting hole precision mounting and guaranteeing method, which comprises the following steps: step 1: processing titanium alloy raw materials for manufacturing a propellant storage tank and a flange; step 2: machining the flange; and step 3: assembling and welding the flange and the propellant storage tank shell; and 4, step 4: carrying out vacuum thermal shape correction treatment on the assembled and welded storage tank flange; and 5: finely adjusting the appearance of the flange, and marking the center reference of the mounting hole on the lug of the flange; step 6: carrying out reference positioning on the mounting hole and machining; and 7: and detecting the appearance of the flange and the machined mounting hole accurately. The difficult problem of flange appearance and mounting hole precision assurance that propellant storage tank caused because of thin wall casing welding deformation and flange rigidity are not enough has effectively been solved in this application, can satisfy processing and the precision assurance of titanium alloy propellant storage tank flange and mounting hole.
Description
Technical Field
The application relates to the technical field of storage tank machining and manufacturing, in particular to a propellant storage tank flange appearance and mounting hole precision mounting guaranteeing method.
Background
The propellant storage box is a core component of the satellite, is arranged in a satellite bearing cylinder through a flange, and is used for storing and managing the propellant and providing the propellant without air entrapment for an engine or a thruster under the conditions of specified flow and acceleration. The flange appearance precision and the mounting hole position precision are decisive factors for determining whether the storage tank can be smoothly mounted, but a propellant storage tank shell and a flange are both of titanium alloy thin-wall structures, the shell thickness is generally 0.8-2 mm, the flange thickness is generally 2-8 mm, gaps are uniformly distributed in the circumferential direction, the storage tank is of a full-welding structure, and the storage tank flange appearance and the mounting hole precision are ensured to be an important problem in the storage tank manufacturing process due to welding deformation of the thin-wall shell and insufficient flange rigidity.
The propellant storage tank is limited by a thin-wall structure and an overall dimension, the processing and detection of a flange and a mounting hole after the whole storage tank is welded are difficult to complete by using high-precision numerical control processing equipment, the traditional process method mostly adopts allowance-reserving repeated processing, manual filing correction and the like, the method has the defects of low processing efficiency and low precision, the storage tank and a satellite bearing cylinder are difficult to complete at one time, and the flange structure and the internal quality defects are easily caused by repeated processing and filing correction, so that the method has higher quality risk.
In recent years, with the increasing demands of large-scale, batch-production and fast-paced tasks of propellant storage tanks, the traditional process method is difficult to be applied to the production and processing of the propellant storage tanks under new conditions, so that the process method capable of ensuring the appearance and the mounting hole precision of the flange of the storage tank with high quality and high efficiency is a key measure for ensuring the smooth production and delivery of the storage tank.
Disclosure of Invention
The application provides a method for guaranteeing the installation accuracy of the flange appearance and the installation hole of the propellant storage tank, which can solve the problem of guaranteeing the accuracy of the flange appearance and the installation hole of the propellant storage tank caused by welding deformation of a thin-wall shell and insufficient rigidity of the flange.
In order to achieve the purpose, the application provides a propellant storage tank flange appearance and mounting hole precision mounting and ensuring method, which comprises the following steps: step 1: processing titanium alloy raw materials for manufacturing a propellant storage tank and a flange; and 2, step: machining the flange; and 3, step 3: assembling and welding a flange and a propellant storage tank shell: and 4, step 4: carrying out vacuum thermal shape correction treatment on the assembled and welded storage tank flange; and 5: finely adjusting the appearance of the flange, and marking the center reference of the mounting hole on the lug plate of the flange; step 6: carrying out reference positioning on the mounting hole and machining; and 7: and detecting the appearance of the flange and the machined mounting hole accurately.
Further, in step 1, the titanium alloy raw material is processed in the following way: step 1.1: firstly, roughly processing a titanium alloy raw material, wherein the single-side processing allowance of a blank is less than or equal to 10mm; step 1.2: after the processing is finished, performing stress annealing on the blank, wherein the heating temperature is 600-650 ℃, and the heat preservation time is 2-3 h; step 1.3: and (4) performing finish machining on the propellant storage box shell according to a design drawing.
Further, in step 2, the flange is machined in the following manner: step 2.1: performing finish machining on the inner surface, the outer surface and the wall thickness of the flange according to a design drawing; step 2.2: cutting the lug plates at all positions of the flange by adopting a linear cutting mode, wherein the linear cutting speed is less than or equal to 1600-2500mm 2 Min; step 2.3: and after the machining is finished, detecting the geometric dimension, form and position tolerance and surface roughness of the flange.
Further, in step 3, the welding flange and the propellant tank shell are assembled in the following way: step 3.1: cleaning and purifying the flange part to ensure that the welding opening of the flange and the storage tank is clean and has no pollution which influences the quality of the welding seam; step 3.2: assembling the flange and the storage box shell according to a design drawing; step 3.3: checking gaps and misalignment at the welding seams after assembly; step 3.4: and after the gap and the misalignment amount are less than or equal to 0.2mm, spot welding is firstly carried out, the number of welding spots is 4-16, and then welding is carried out according to the sequence of sectional symmetrical and uniform distribution.
Further, in step 4, the vacuum thermal sizing treatment is performed in the following manner: step 4.1: placing the reference ring on the mounting bracket, placing the storage tank flange into the reference ring, and fixing and pressing the storage tank flange by using a fixing ring and a bolt assembly; step 4.2: the storage box and the fixing tool are arranged in heat treatment equipment; step 4.3: according to the vacuum degree of less than or equal to 2 x 10 -3 Pa, heating at 600-650 ℃, and carrying out heat treatment for 2-3 h; step 4.4: and after the heat treatment is finished, taking out the storage tank flange, and taking down the fixing ring.
Further, in step 5, the shape of the flange is finely adjusted and marked in the following way: step 5.1: measuring the overall dimension and the flatness of the flange by taking the reference ring as a reference, and if the overall dimension and the flatness do not meet the requirements, performing local filing; step 5.2: after the requirements are met, the center of the mounting hole is marked on the upper surface of the lug of the flange according to a design drawing; step 5.3: in the marking process, the center reference circle marking line is marked firstly, then the center line uniformly distributed by the lug pieces is marked, and the intersection point of the two lines is the center hole reference.
Further, in step 6, the mounting hole is subjected to datum positioning and machining in the following way: step 6.1: installing the bracket and the drill bushing installation ring on the working table of the processing equipment; step 6.2: aligning the rotation axis of the workbench and the axis of the drill bushing mounting ring, and clamping the fixed support after the coaxiality of the rotation axis and the axis of the drill bushing mounting ring is less than or equal to 0.1 mm; step 6.3: mounting a storage tank flange into a drill bushing mounting ring, sequentially aligning the reference of each central hole and the axis of the drill bushing hole, and fixing the storage tank by using a compression ring after the coaxiality deviation is less than or equal to 0.05 mm; step 6.4: starting processing equipment to sequentially process each mounting hole to a designed size, drilling a bottoming hole in the processing process, and then finely processing the inner diameter or the thread of the hole to a designed tolerance size; step 6.5: and after the processing is finished, the storage box flange is detached from the tool.
Further, in step 7, the shape and the mounting hole of the flange are accurately detected in the following manner: step 7.1: firstly, checking whether the dimensional tolerance and the form and position tolerance of the flange appearance and the mounting hole meet the dimension of a design drawing according to the design drawing; step 7.2: then hoisting the storage box into a calibration tool, and performing trial assembly on the flange and the calibration tool; step 7.3: in the trial assembly process, the flange and the mounting hole are required to have no interference with the calibration tool, the threaded hole is free of stagnation in installation, each lug of the flange is free of distortion after the installation is finished, and the flange is qualified in detection if the requirements are met.
Furthermore, the wall thickness of the storage tank shell is 0.6mm-2mm, and the flange is of an annular thin-wall structure and is 1mm-10mm thick.
Furthermore, in step 5.3, the number of the center hole reference points is 4-16, and the center hole reference points are uniformly distributed along the axis of the storage tank.
The method for ensuring the shape and the mounting hole precision of the propellant storage tank flange provided by the invention has the following beneficial effects:
the method effectively solves the problem of ensuring the precision of the flange appearance and the mounting hole of the propellant storage tank due to welding deformation of a thin-wall shell and insufficient flange rigidity by utilizing the technological characteristics of titanium alloy raw materials and the appearance structure of the storage tank flange and adopting the technological methods of fine correction of a thin-wall structure, kong Gaojing degree installation, simulation trial assembly inspection and the like, has simple and efficient flow and strong universality, and can meet the requirements of machining and precision guarantee of the flange and the mounting hole of the titanium alloy propellant storage tank with any appearance size and similar installation principle. In addition, compared with the traditional process method, the flange processes the shape dimension in place at one time at the part stage, the shape accuracy is guaranteed through shape correction and local finishing carving, the accuracy of the mounting hole is guaranteed through a processing tool and equipment after the shape accuracy meets the requirement, the quality risk caused by repeated processing and shape correction in the traditional method is eliminated, and the production and processing of the propellant storage box under the conditions of large scale, batch production and fast pace can be met.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, serve to provide a further understanding of the application and to enable other features, objects, and advantages of the application to be more apparent. The drawings and the description of the exemplary embodiments of the present application are provided for explaining the present application and do not constitute an undue limitation on the present application. In the drawings:
FIG. 1 is a schematic flow chart of a method for ensuring accurate installation of a flange shape and an installation hole of a propellant tank according to an embodiment of the present application;
FIG. 2 is a schematic structural view of a flange and a mounting hole of a propellant tank provided according to an embodiment of the present application;
FIG. 3 is a schematic structural diagram of a vacuum thermal sizing tooling assembly for a flange of a propellant tank provided in accordance with an embodiment of the present application;
in the figure: 1-a storage tank shell, 2-a flange, 3-a lug, 4-a mounting hole, 5-a welding line, 6-a fixing ring, 7-a reference ring, 8-a bolt component and 9-a mounting bracket.
Detailed Description
In order to make the technical solutions of the present application better understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only some embodiments of the present application, and not all embodiments. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present application without making any creative effort shall fall within the protection scope of the present application.
It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It should be understood that the data so used may be interchanged under appropriate circumstances such that embodiments of the application described herein may be used. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
In this application, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings. These terms are used primarily to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to a particular orientation or to be constructed and operated in a particular orientation.
Moreover, some of the above terms may be used to indicate other meanings besides the orientation or positional relationship, for example, the term "on" may also be used to indicate some kind of attachment or connection relationship in some cases. The specific meaning of these terms in this application will be understood by those of ordinary skill in the art as appropriate.
In addition, the term "plurality" shall mean two as well as more than two.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1, the propellant tank flange appearance and mounting hole precision installation guarantee method provided by the embodiment of the present application can ensure the production of the propellant tank and the assembly with the satellite with high quality and high efficiency, the propellant tank flange 2 manufactured by the installation guarantee method provided by the embodiment of the present application has an appearance size meeting the requirement of ± 0.1, a flatness meeting the requirement of not more than 0.2mm, and a mounting hole 4 position meeting the requirement of being better than 0.1mm, and specifically includes the following steps:
step 1: processing titanium alloy raw materials for manufacturing the propellant storage tank and the flange 2; in the embodiment of the present application, the titanium alloy raw material is preferably a TC4 titanium alloy raw material, and the raw material is subjected to rough machining and then to stress relief heat treatment, specifically as follows: step 1.1: firstly, roughly processing a titanium alloy raw material, wherein the single-side processing allowance of a blank is less than or equal to 10mm; step 1.2: after the processing is finished, performing stress annealing on the blank, wherein the heating temperature is 600-650 ℃, and the heat preservation time is 2-3 h; step 1.3: and (3) performing finish machining on the propellant storage tank shell 1 according to a design drawing, and ensuring that the wall thickness of the storage tank shell 1 is between 0.6mm and 2 mm.
Step 2: machining the flange 2; the method is characterized in that a TC4 titanium alloy raw material after heat treatment is utilized to finish machining to manufacture a flange 2, the flange 2 is of an annular thin-walled structure, the thickness of the flange is 1mm-10mm, the inner and outer surfaces and the wall thickness of the flange 2 are firstly finished to the required size, and then the appearance of the lug 3 is machined by linear cutting, and the specific mode is as follows: step 2.1: finish machining the inner surface, the outer surface and the wall thickness of the flange 2 according to a design drawing; step 2.2: cutting the lug pieces 3 at all positions of the flange 2 by adopting a linear cutting mode, wherein the linear cutting speed is less than or equal to 1600-2500mm 2 Min, reducing machining deformation and ensuring the requirement of machining surface roughness; step 2.3: after the machining is completed, the geometric dimension, form and position tolerance and surface roughness of the flange 2 are detected.
And step 3: assembling and welding the flange 2 and the propellant storage tank shell 1; firstly, the flange 2 is cleaned and purified, and then the flange 2 and the propellant storage tank shell 1 are assembled and welded, as shown in fig. 2, the specific mode is as follows: step 3.1: cleaning and purifying the flange 2 part to ensure that the welding opening of the flange 2 and the storage tank is clean and has no pollution which influences the quality of the welding line 5; step 3.2: assembling the flange 2 and the storage tank shell 1 according to a design drawing; step 3.3: checking the gap and the misalignment amount at the welding seam 5 after assembly; step 3.4: and after the gap and the misalignment are less than or equal to 0.2mm, tack welding is firstly carried out, the number of welding points is 4-16, and then welding is carried out according to the sequence of sectional symmetrical and uniform distribution.
And 4, step 4: carrying out vacuum thermal sizing treatment on the assembled and welded storage tank flange 2; firstly, placing the storage tank flange 2 on a tool for fixing, as shown in fig. 3, then placing the storage tank flange 2 and the tool into vacuum heat treatment equipment together for vacuum heat shape correction treatment, wherein the specific mode is as follows: step 4.1: placing the reference ring 7 on the mounting bracket 9, installing the tank flange 2 into the reference ring 7, fixing and pressing the tank flange 2 by using the fixing ring 6 and the bolt assembly 8, wherein the reference ring 7 is installedThe mounting bracket 9 is used for supporting the storage tank and preventing the storage tank from colliding with the surface of the storage tank, the reference ring 7 is used for providing a thermal correction reference and a fine adjustment measurement reference for the overall dimension of the flange 2, and the fixing ring 6 is used for fixing and pressing the storage tank flange 2 and limiting the axial displacement and the radial displacement of the storage tank; step 4.2: the storage box and the fixing tool are arranged in heat treatment equipment; step 4.3: according to the vacuum degree of less than or equal to 2 x 10 -3 pa, heating at 600-650 ℃, and carrying out heat treatment under the condition of heat preservation time of 2-3 h; step 4.4: after the heat treatment is completed, the tank flange 2 is taken out, and the fixing ring 6 is removed.
And 5: the appearance of the flange 2 is finely adjusted, and the central reference of the mounting hole 4 is marked on the lug 3 of the flange 2; after the vacuum thermal sizing is finished, the storage box flange 2 measures the overall dimension of the flange 2 and the flatness of each lug piece 3 by taking a sizing die as a reference, the overall dimension of the flange 2 is finely adjusted according to a measurement result, after the design requirement is met, the center reference is marked according to the design dimension of the mounting hole 4 and is a cross line or a sample punching hole, and the specific mode is as follows: step 5.1: measuring the overall dimension and the flatness of the flange 2 by taking the reference ring 7 as a reference, and if the overall dimension and the flatness do not meet the requirements, performing local filing; step 5.2: after the requirements are met, the center of the mounting hole 4 is marked on the upper surface of the lug 3 of the flange 2 according to a design drawing; step 5.3: in the marking process, the central reference circle marking line is marked firstly, then the central lines uniformly distributed on the lugs 3 are marked, the intersection point of the two lines is the center hole reference, the number of the center hole reference points is 4-16, and the center hole reference points are uniformly distributed along the axis of the storage tank.
Step 6: the mounting hole 4 is subjected to datum positioning and machining, and the specific mode is as follows: step 6.1: installing a support and a drill bushing installation ring on a working table of machining equipment, wherein a machining tool of an installation hole 4 is selected according to actual conditions, and like the tool in fig. 3, the machining tool comprises a support, the drill bushing installation ring, a compression ring and other part structures, wherein the support is used for supporting a storage tank and fixing the storage tank and the machining equipment; step 6.2: aligning the rotation axis of the workbench and the axis of the drill bushing mounting ring, and clamping the fixed support after the coaxiality of the rotation axis and the axis of the drill bushing mounting ring is less than or equal to 0.1 mm; step 6.3: the storage tank flange 2 is arranged in a drill bushing mounting ring, the reference of each central hole and the axis of the drill bushing hole are sequentially aligned, and after the coaxiality deviation is less than or equal to 0.05mm, the storage tank is fixed by using a compression ring; step 6.4: starting processing equipment to sequentially process each mounting hole 4 to a designed size, drilling a bottoming hole in the processing process, and then finely processing the inner diameter or the thread of the hole to the designed tolerance size; step 6.5: and after the machining is finished, the storage box flange 2 is detached from the tool.
And 7: the appearance of the flange 2 and the processed mounting hole 4 are subjected to precision detection, and the specific mode is as follows: step 7.1: firstly, checking whether the dimensional tolerance and the form and position tolerance of the appearance and the mounting hole 4 of the flange 2 meet the dimension of a design drawing according to the design drawing; step 7.2: then hoisting the storage box into a calibration tool, and performing trial assembly on the flange 2 and the calibration tool; step 7.3: in the trial assembly process, the verification tool is mainly used for simulating the mounting structure of the bearing cylinder and the storage box flange 2, the geometric tolerance and the geometric tolerance of the verification tool are superior to or equal to the actual geometric tolerance and the geometric tolerance of the bearing cylinder, the flange 2 and the mounting hole 4 are required to have no interference with the verification tool, the threaded hole is free from stagnation during mounting, each lug 3 of the flange 2 has no distortion and deformation after mounting is finished, and the detection is qualified if the requirements are met.
More specifically, in each step, the flange 2 is protected in the processes of installation, transportation, filing and the like of the storage tank flange 2, and permanent deformation and mechanical damage caused by extrusion and collision are prevented, the geometric dimensional tolerance and the form and position tolerance of the process assembly such as the reference ring 7, the drill bushing mounting ring and the checking tool used in each step are superior to the design value of the storage tank flange 2, and meanwhile, the process equipment can be used after being subjected to regular standard inspection, and the precision reduction caused by failure deformation and use abrasion is prevented.
The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (10)
1. A propellant storage tank flange appearance and mounting hole precision mounting guaranteeing method is characterized by comprising the following steps:
step 1: processing titanium alloy raw materials for manufacturing a propellant storage tank and a flange;
and 2, step: machining the flange;
and step 3: assembling and welding the flange and the propellant storage tank shell;
and 4, step 4: carrying out vacuum thermal shape correction treatment on the assembled and welded storage tank flange;
and 5: finely adjusting the appearance of the flange, and marking the center reference of the mounting hole on the lug plate of the flange;
step 6: carrying out reference positioning on the mounting hole and machining;
and 7: and detecting the appearance of the flange and the machined mounting hole accurately.
2. The propellant tank flange shape and mounting hole precision mounting ensuring method according to claim 1, characterized in that in the step 1, the titanium alloy raw material is processed in the following way:
step 1.1: firstly, roughly processing a titanium alloy raw material, wherein the single-side processing allowance of a blank is less than or equal to 10mm;
step 1.2: after the processing is finished, performing stress annealing on the blank, wherein the heating temperature is 600-650 ℃, and the heat preservation time is 2-3 h;
step 1.3: and (4) performing finish machining on the propellant storage box shell according to a design drawing.
3. The method for ensuring the precision installation of the flange shape and the installation hole of the propellant tank as claimed in claim 2, wherein in the step 2, the flange is machined in the following way:
step 2.1: finish machining the inner surface, the outer surface and the wall thickness of the flange according to a design drawing;
step 2.2: cutting and forming flange by adopting linear cutting modeThe linear cutting speed of each lug is less than or equal to 1600-2500mm 2 /min；
Step 2.3: and after the machining is finished, detecting the geometric dimension, form and position tolerance and surface roughness of the flange.
4. The method for ensuring the precise installation of the flange shape and the installation hole of the propellant tank as claimed in claim 3, wherein in the step 3, the welding flange and the propellant tank shell are assembled in the following way:
step 3.1: cleaning and purifying the flange part to ensure that the welding opening of the flange and the storage tank is clean and has no pollution which influences the quality of the welding seam;
step 3.2: assembling the flange and the storage box shell according to a design drawing;
step 3.3: checking gaps and misalignment at the welding seams after assembly;
step 3.4: and after the gap and the misalignment amount are less than or equal to 0.2mm, spot welding is firstly carried out, the number of welding spots is 4-16, and then welding is carried out according to the sequence of sectional symmetrical and uniform distribution.
5. The propellant tank flange shape and mounting hole precision mounting ensuring method according to claim 4, characterized in that in the step 4, the vacuum thermal sizing treatment is performed in the following way:
step 4.1: placing the reference ring on the mounting bracket, placing the storage tank flange into the reference ring, and fixing and pressing the storage tank flange by using a fixing ring and a bolt assembly;
and 4.2: the storage box and the fixing tool are arranged in heat treatment equipment;
step 4.3: according to the vacuum degree of less than or equal to 2 x 10 -3 Pa, heating at 600-650 ℃, and carrying out heat treatment for 2-3 h;
step 4.4: and after the heat treatment is finished, taking out the storage tank flange, and taking down the fixing ring.
6. The propellant tank flange shape and mounting hole precision mounting ensuring method according to claim 5, characterized in that in the step 5, the flange shape is finely adjusted and marked in the following way:
step 5.1: measuring the overall dimension and the flatness of the flange by taking the reference ring as a reference, and if the overall dimension and the flatness do not meet the requirements, performing local filing;
step 5.2: after the requirements are met, the center of the mounting hole is marked on the upper surface of the lug of the flange according to a design drawing;
step 5.3: in the marking process, the center reference circle marking line is marked firstly, then the center line uniformly distributed by the lug pieces is marked, and the intersection point of the two lines is the center hole reference.
7. The propellant tank flange shape and mounting hole precision installation assurance method of claim 6, characterized in that in step 6, mounting hole datum positioning and machining are performed as follows:
step 6.1: installing the bracket and the drill bushing installation ring on the working table of the processing equipment;
step 6.2: aligning the rotation axis of the workbench and the axis of the drill bushing mounting ring, and clamping the fixed support after the coaxiality of the rotation axis and the axis of the drill bushing mounting ring is less than or equal to 0.1 mm;
step 6.3: mounting a storage tank flange into a drill bushing mounting ring, sequentially aligning the datum of each central hole and the axis of the drill bushing hole, and fixing the storage tank by using a compression ring after the coaxiality deviation is less than or equal to 0.05 mm;
step 6.4: starting processing equipment to sequentially process each mounting hole to a designed size, drilling a bottoming hole in the processing process, and then finely processing the inner diameter or the thread of the hole to a designed tolerance size;
step 6.5: and after the processing is finished, the storage box flange is detached from the tool.
8. The propellant tank flange shape and mounting hole precision installation ensuring method according to claim 7, characterized in that in the step 7, the flange shape and mounting hole precision detection is carried out by adopting the following modes:
step 7.1: firstly, checking whether the dimensional tolerance and the form and position tolerance of the flange appearance and the mounting hole meet the dimension of a design drawing according to the design drawing;
step 7.2: then hoisting the storage box into a calibration tool, and performing trial assembly on the flange and the calibration tool;
step 7.3: in the trial assembly process, the flange and the mounting hole are required to be free of interference with the checking tool, the threaded hole is free of stagnation in installation, each lug of the flange is free of distortion after installation is completed, and the flange is qualified in detection if the requirements are met.
9. The propellant tank flange shape and mounting hole precision installation assurance method of claim 4, characterized in that the tank shell wall thickness is 0.6mm-2mm, the flange is of an annular thin-walled structure and is 1mm-10mm thick.
10. The propellant tank flange configuration and mounting hole accuracy installation assurance method of claim 6, characterized in that in step 5.3, the number of center hole reference points is 4-16, evenly distributed along the tank axis.
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