Composite type fixture tool for riveting structural cabin section of carrier rocket

Abstract

The utility model discloses a composite type fixture tool for riveting a structural cabin section of a carrier rocket, which relates to the technical field of rocket assembly and comprises a lower platform, an upper platform, a plurality of upright posts and a plurality of positioning tools, during use, a plurality of supporting legs are evenly arranged at the lower end of the lower platform, and the upper end of the lower platform is detachably connected with the lower end of the upper platform through one stand column selected from the multiple stand columns according to the assembly mode. One or more positioning tools selected from the multiple positioning tools according to the assembly mode are installed at the upper end of the lower platform; the lower end part of the structural cabin section is connected with the lower platform, and the upper end part of the structural cabin section is connected with the upper platform. The device can meet the riveting assembly work of cabin sections of various structures, is convenient to cooperate with production scheduling, and can reduce the production cost and improve the production efficiency.

Description

Technical Field

[0001] The present application relates to the field of rocket assembly technology, and in particular to a composite jig tool for riveting structural compartments of launch vehicles. Background Art

[0002] The riveting assembly of the launch vehicle's structural compartment is to assemble the scattered parts, components and assemblies that make up the rocket's structural compartment into a "metal hard shell" structure with very high requirements for positional dimensional accuracy according to the designed assembly relationship and dimensional position accuracy requirements.

[0003] At present, in the riveting assembly process of the structural compartment of the launch vehicle, the shape and position dimensional accuracy of the overall assembly is usually guaranteed by relying solely on the processing accuracy of the scattered parts, components and assemblies themselves. However, the processing dimensional accuracy of each part, component and assembly is uneven, and there is no assembly benchmark related to the theory of the overall missile body assembly. Therefore, the shape and position dimensional accuracy of the overall assembly cannot be guaranteed.

[0004] In addition, although domestic rocket production units use integrated jigs for cabin structure assembly, individual cabins need to be assembled using separate jigs. Although the existing rocket structural cabin riveting assembly uses jigs to avoid the problem of low overall assembly shape and position dimensional accuracy caused by the lack of assembly reference relative to the overall missile body due to part processing errors during the assembly of scattered parts, the existing jigs can only be used for the assembly of one structural cabin, that is, the production of different structural cabins requires the manufacture of a jig dedicated to assembling the structural cabin, which greatly wastes production space and time and increases material costs. Utility Model Content

[0005] The purpose of the present application is to provide a composite jig for riveting launch vehicle structural compartment segments, which can meet the riveting and assembly work of various structural compartment segments, facilitate production scheduling, reduce production costs and improve production efficiency.

[0006] To achieve the above-mentioned purpose, the present application provides a composite jig for riveting the structural compartment of a launch vehicle, comprising: a lower platform, an upper platform, a plurality of columns and a plurality of positioning jigs; when in use, a plurality of legs are evenly arranged at the lower end of the lower platform, and the upper end of the lower platform is detachably connected to the lower end of the upper platform by a column selected from a plurality of columns according to an assembly mode; one or more positioning jigs selected from a plurality of positioning jigs according to the assembly mode are installed on the upper end of the lower platform; the lower end parts of the structural compartment are connected to the lower platform, and the upper end parts of the structural compartment are connected to the upper platform; wherein the plurality of columns at least comprise: a plurality of first columns, a plurality of second columns and a plurality of third columns; the size of the first column, the size of the second column and the size of the third column are all different; the plurality of positioning jigs at least comprise: a plurality of rolling control bearing positioning jigs, a plurality of intermediate frame positioning jigs, a plurality of reverse thrust small rocket bracket positioning jigs, a side thrust small rocket bracket positioning jigs and a multi-functional positioning jig; the assembly mode The assembly mode at least includes: a first-stage tail section assembly mode, a second-stage and third-stage interstage section assembly mode and a multi-functional cabin assembly mode; when the assembly mode is the first-stage tail section assembly mode, the upper end of the lower platform is detachably connected to the lower end of the upper platform through the first column; multiple rolling bearing positioning tooling is evenly arranged at the upper end of the lower platform and is detachably connected to the lower platform; when the assembly mode is the second-stage and third-stage interstage section assembly mode, the upper end of the lower platform is detachably connected to the lower end of the upper platform through the second column; multiple intermediate frame positioning tooling is evenly arranged at the upper end of the lower platform and is detachably connected to the lower platform; multiple reverse thrust small rocket bracket positioning tooling is evenly arranged at the upper end of the lower platform and is detachably connected to the lower platform; the side thrust small rocket bracket positioning tooling is arranged at the upper end of the lower platform and is detachably connected to the lower platform; when the assembly mode is the multi-functional cabin assembly mode, the upper end of the lower platform is detachably connected to the lower end of the upper platform through the third column; the multi-functional positioning tooling is arranged at the upper end of the lower platform and is detachably connected to the lower platform.

[0007] As above, wherein a plurality of groups of lower component holes are arranged on the lower platform, and each group of lower component holes includes: at least one lower component positioning hole for positioning the lower end components of the structural compartment and at least one lower component bolt hole for fixing the lower end components of the structural compartment; the lower end components of the structural compartment are connected to the lower component positioning hole through the lower component positioning pin, and are connected to the lower component bolt hole through the lower component bolt; a plurality of groups of upper component holes are arranged on the upper platform, and each group of upper component holes includes: at least four upper component positioning holes for positioning the upper end components of the structural compartment and at least four upper component bolt holes for fixing the upper end components of the structural compartment; the upper end components of the structural compartment are positioned through the upper component positioning pin and the upper component positioning hole, and are connected to the upper component bolt hole through the upper component bolt.

[0008] As above, a plurality of lower lifting ears are evenly arranged on the upper end of the lower platform; a plurality of upper lifting ears are evenly arranged on the upper end of the upper platform.

[0009] As above, the upper end of each leg is connected to the lower end of the lower platform, and the lower end of each leg is provided with a pad or gasket for adjusting the height.

[0010] As above, wherein a plurality of groups of first tooling holes are evenly arranged at the upper end of the lower platform, and each group of first tooling holes includes: at least one first tooling positioning hole and at least one first tooling bolt hole; one rolling control support positioning tool corresponds to one group of first tooling holes, and the rolling control support positioning tool is positioned through the first tooling positioning pin and the first tooling positioning hole, and is connected to the first tooling bolt hole through the first tooling bolt.

[0011] As above, wherein a plurality of groups of second tooling holes are evenly arranged at the upper end of the lower platform, and each group of second tooling holes includes: at least one second tooling positioning hole and at least one second tooling bolt hole; one middle frame positioning tool corresponds to one group of second tooling holes, and the middle frame positioning tool is positioned through the second tooling positioning pin and the second tooling positioning hole, and is connected to the second tooling bolt hole through the second tooling bolt.

[0012] As above, wherein, a plurality of groups of third tooling holes are evenly arranged at the upper end of the lower platform, and each group of third tooling holes includes: at least one third tooling positioning hole and at least one third tooling bolt hole; one reverse thrust small rocket bracket positioning tool corresponds to one group of third tooling holes, and the reverse thrust small rocket bracket positioning tool is positioned with the third tooling positioning hole through the third tooling positioning pin, and is connected with the third tooling bolt hole through the third tooling bolt.

[0013] As above, wherein at least one group of fourth tooling holes is evenly arranged at the upper end of the lower platform, and each group of fourth tooling holes includes: at least one fourth tooling positioning hole and at least one fourth tooling bolt hole; the side thrust small rocket bracket positioning tooling is positioned through the fourth tooling positioning pin and the fourth tooling positioning hole, and is connected to the fourth tooling bolt hole through the fourth tooling bolt.

[0014] As above, wherein at least one group of fifth tooling holes is evenly arranged at the upper end of the lower platform, and each group of fifth tooling holes includes: at least one fifth tooling positioning hole and at least one fifth tooling bolt hole; the multifunctional positioning tool is positioned through the fifth tooling positioning pin and the fifth tooling positioning hole, and is connected to the fifth tooling bolt hole through the fifth tooling bolt.

[0015] As above, an upper positioning mark is provided at the lower end of the upper platform, and a lower positioning mark is provided at the upper end of the lower platform. After the upper end of the lower platform is detachably connected to the lower end of the upper platform by a column selected from a plurality of columns according to an assembly mode, the upper positioning mark and the lower positioning mark are aligned with each other.

[0016] The beneficial effects achieved by this application are as follows:

[0017] (1) The composite jig for riveting launch vehicle structural compartments of the present application enables a single jig to have the function of satisfying the riveting assembly of various rocket structural compartments by replacing columns and positioning jigs.

[0018] (2) The composite jig tooling for riveting the launch vehicle structural compartment of the present application can adjust the horizontality of the lower platform through the support legs and pads / gaskets.

[0019] (3) The composite jig tooling used for riveting the launch vehicle structural compartment of the present application can meet the precise shape and position dimensional accuracy of the parts through the corresponding positioning tooling, thereby being able to meet the special assembly requirements of different structural compartments.

[0020] (4) The composite jig used for riveting the launch vehicle structural compartment of the present application ensures that the scattered parts have an overall positioning reference with the overall missile body after riveting and assembly. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present application. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.

[0022] Figure 1 The schematic diagram of the structure of an embodiment of a composite jig tool for riveting a launch vehicle structural compartment;

[0023] Figure 2 It is a structural schematic diagram of an embodiment of a composite jig tooling for riveting a launch vehicle structural compartment section in a first stage tail section assembly mode;

[0024] Figure 3 It is a structural schematic diagram of an embodiment of a composite jig tooling for riveting a launch vehicle structural compartment section in a second- and third-stage interstage assembly mode;

[0025] Figure 4 The present invention is a schematic structural diagram of an embodiment of a composite jig tooling for riveting structural compartment sections of a launch vehicle when it is in a multifunctional compartment assembly mode. DETAILED DESCRIPTION

[0026] The following is a clear and complete description of the technical solutions in the embodiments of the present invention in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0027] like Figure 1-4 As shown, the present application provides a composite jig for riveting the structural compartment of a launch vehicle, comprising: a lower platform 1, an upper platform 2, a plurality of columns 3 and a plurality of positioning jigs 4. When in use, a plurality of legs 5 are evenly arranged at the lower end of the lower platform 1, and the upper end of the lower platform 1 is detachably connected to the lower end of the upper platform 2 through a column 3 selected from a plurality of columns 3 according to an assembly mode; one or more positioning jigs 4 selected from a plurality of positioning jigs 4 according to an assembly mode are installed on the upper end of the lower platform 2; the lower end parts of the structural compartment are connected to the lower platform 1, and the upper end parts of the structural compartment are connected to the upper platform 2. Among them, the plurality of columns 3 at least include: a plurality of first columns 31, a plurality of second columns 32 and a plurality of third columns 33; the size of the first column 31, the size of the second column 32 and the size of the third column 33 are all different. The various positioning fixtures 4 at least include: multiple rolling bearing positioning fixtures 41, multiple middle frame positioning fixtures 42, multiple reverse thrust small rocket bracket positioning fixtures 43, side thrust small rocket bracket positioning fixtures 44 and multifunctional positioning fixtures 45. The assembly modes at least include: the first-stage tail section assembly mode, the second- and third-stage interstage assembly mode and the multifunctional cabin assembly mode. When the assembly mode is the first-stage tail section assembly mode, the upper end of the lower platform 1 is detachably connected to the lower end of the upper platform 2 through the first column 31; multiple rolling bearing positioning fixtures 41 are evenly arranged on the upper end of the lower platform 1 and are detachably connected to the lower platform 1. When the assembly mode is the second- and third-stage interstage assembly mode, the upper end of the lower platform 1 is detachably connected to the lower end of the upper platform 2 through the second column 32; multiple intermediate frame positioning fixtures 42 are evenly arranged at the upper end of the lower platform 1 and are detachably connected to the lower platform 1; multiple reverse thrust small rocket bracket positioning fixtures 43 are evenly arranged at the upper end of the lower platform 1 and are detachably connected to the lower platform 1; side thrust small rocket bracket positioning fixture 44 is arranged at the upper end of the lower platform 1 and is detachably connected to the lower platform 1. When the assembly mode is the multifunctional cabin assembly mode, the upper end of the lower platform 1 is detachably connected to the lower end of the upper platform 2 through the third column 33; the multifunctional positioning fixture 45 is arranged at the upper end of the lower platform 1 and is detachably connected to the lower platform 1.

[0028] Specifically, the lower platform 1 is used as a positioning reference base for positioning and installing the lower end components, columns 3 and various positioning fixtures 4 of the structural compartment. The installation surface of the lower platform 1 must be guaranteed to be horizontal and meet the set flatness requirements. Therefore, the lower platform 1 is preferably a cast iron part, but is not limited to a cast iron part. The lower platform 1 can be installed horizontally on the support legs 5. The upper platform 2 is used as a reference for positioning and installing the upper end components of the structural compartment. The lower plane of the upper platform 2 must be horizontal and meet the set flatness requirements. Therefore, the upper platform 2 is positioned with the lower platform 1 through the columns 3 to ensure that the reference torsion angles of the upper platform 2 and the lower platform 1 meet the requirements.

[0029] Furthermore, the upper end of the column 3 is connected to the column positioning hole of the upper platform 2 through a column positioning pin, and the lower end of the column 3 is connected to the column positioning hole of the lower platform 1 through a column positioning pin.

[0030] Specifically, the column 3 serves as a positioning load-bearing member of the upper platform 4. The installation position of the column 3 is positioned by the column positioning holes on the lower platform 1, the column positioning holes on the upper platform 2, and the column positioning pins. The specific size of the column 3 is set according to the assembly height requirements of different compartments. The columns of different sizes included in the column 3 are not limited to three types. The present application preferably has three types. The three different sizes of columns 3 are respectively the first column 31, the second column 32, and the third column 33. By replacing the columns 3 of different heights, the riveting assembly of different compartments can be achieved. The specific number of the first column 31, the specific number of the second column 32, and the specific number of the third column 33 are all determined according to the actual situation. The present application preferably has four or six.

[0031] Furthermore, the planes of the upper and lower ends of the column 3 need to meet set flatness and parallelism and have set bending stiffness requirements. Therefore, the column 3 is preferably made by welding square steel tubes and steel plates, but is not limited to being made by welding square steel tubes and steel plates.

[0032] Furthermore, the upper end of the column 3 is connected to the column bolt hole of the upper platform 2 through a column bolt, and the lower end of the column 3 is connected to the column bolt hole of the lower platform 1 through a column bolt.

[0033] Specifically, the column 3 is fixed by means of the column bolts, the column bolt holes of the upper platform 2 and the column bolt holes of the lower platform 1 .

[0034] Among them, the assembly coordination of the column locating pins at the upper end of each column 3, the column locating holes of the upper platform 2, the column locating pins at the lower end of each column 3, the column locating holes of the lower platform 1, the column bolts at the upper end of each column 3, the column bolt holes of the upper platform 2, the column bolts at the lower end of each column 3 and the column bolt holes of the lower platform 1 needs to meet the set requirements. After replacing the columns 3, the assembled jig tooling can still maintain the design dimensional accuracy requirements.

[0035] Furthermore, a leg positioning hole and a leg bolt hole for positioning and installing the leg 5 are provided on the lower platform 1. The leg 5 is connected to the leg positioning hole through a leg positioning pin, and the leg 5 is connected to the leg bolt hole through a leg bolt.

[0036] Furthermore, the multiple legs 5 are evenly distributed on the reinforcement ribs of the lower platform 1, which can evenly distribute the weight of the composite jig tooling for riveting the entire launch vehicle structural compartment, thereby improving stability and bearing capacity.

[0037] Specifically, the specific number of the legs 5 is determined according to the actual situation. A plurality of legs 5 are evenly distributed at the lower end of the lower platform 1, and are used to lift the lower platform 1 to a height suitable for workers to operate.

[0038] Furthermore, the upper end of each supporting leg 5 is connected to the lower end of the lower platform 1 , and the lower end of each supporting leg 5 is provided with a pad or a gasket for adjusting the height.

[0039] Furthermore, a plurality of groups of lower component holes are provided on the lower platform 1, and each group of lower component holes includes: at least one lower component positioning hole for positioning the lower end components of the structural compartment and at least one lower component bolt hole for fixing the lower end components of the structural compartment; the lower end components of the structural compartment are connected to the lower component positioning hole through a lower component positioning pin, and are connected to the lower component bolt hole through a lower component bolt.

[0040] Specifically, the lower component holes are used to locate and connect the lower end components of the structural compartment. The specific number of groups of the lower component holes is determined according to the actual situation. The present application preferably has three groups, and the three groups of lower component holes are evenly distributed on the lower platform 1. The specific number of lower component positioning holes in each group of lower component holes and the specific number of lower component bolt holes are determined according to the actual situation.

[0041] Furthermore, a plurality of groups of upper component holes are provided on the upper platform 2, and each group of upper component holes includes: at least four upper component positioning holes for positioning the upper end components of the structural compartment and at least four upper component bolt holes for fixing the upper end components of the structural compartment; the upper end components of the structural compartment are positioned through the upper component positioning pins and the upper component positioning holes, thereby realizing the positioning of the upper end components of the structural compartment and the upper platform 2, and are connected through the upper component bolts and the upper component bolt holes, thereby realizing the connection between the upper end components of the structural compartment and the upper platform 2.

[0042] Specifically, the upper component holes are used to locate and connect the upper end components of the structural compartment. The specific number of groups of upper component holes is determined according to the actual situation. The present application preferably has three groups, and the three groups of upper component holes are evenly distributed on the upper platform 2. The specific number of upper component positioning holes and the specific number of upper component bolt holes in each group of upper component holes are determined according to the actual situation.

[0043] Furthermore, the multiple groups of lower component holes of the lower platform 1 and the multiple groups of upper component holes of the upper platform 2 need to meet the set requirements of parallelism, roundness, coaxiality and reference torsion angle.

[0044] Furthermore, a plurality of lower lifting ears 11 are evenly arranged on the upper end of the lower platform 1 .

[0045] Specifically, the lower platform 1 is hoisted by the lower lifting lugs 11. The specific number of the lower lifting lugs 11 is determined according to actual conditions.

[0046] Furthermore, a plurality of upper lifting ears 21 are evenly arranged on the upper end of the upper platform 2 .

[0047] Specifically, the upper platform 2 is hoisted by the upper hoisting lugs 21. The specific number of the upper hoisting lugs 21 is determined according to actual conditions.

[0048] Furthermore, a plurality of groups of first tooling holes are evenly arranged at the upper end of the lower platform 1, and each group of first tooling holes includes: at least one first tooling positioning hole and at least one first tooling bolt hole. One rolling control support positioning tool 41 corresponds to one group of first tooling holes, and the rolling control support positioning tool 41 is positioned with the first tooling positioning hole through the first tooling positioning pin, and connected with the first tooling bolt hole through the first tooling bolt.

[0049] Specifically, the first tooling hole is used to position and install the rolling control support positioning tooling 41, and the specific number of groups of the first tooling holes is determined according to the actual situation. The specific number of the first tooling positioning holes in each group of first tooling holes and the specific number of the first tooling bolt holes are determined according to the actual situation. The rolling control support positioning tooling 41 is used to meet the installation requirements of rolling control. The specific number of the rolling control support positioning tooling 41 is determined according to the actual situation.

[0050] Furthermore, a plurality of groups of second tooling holes are evenly arranged on the upper end of the lower platform 1, and each group of second tooling holes includes: at least one second tooling positioning hole and at least one second tooling bolt hole. One middle frame positioning tool 42 corresponds to one group of second tooling holes, and the middle frame positioning tool 42 is positioned with the second tooling positioning hole by the second tooling positioning pin, and connected with the second tooling bolt hole by the second tooling bolt.

[0051] Specifically, the second tooling holes are used to position and install the middle frame positioning tooling 42, and the specific number of groups of the second tooling holes is determined according to the actual situation. The specific number of the second tooling positioning holes in each group of second tooling holes and the specific number of the second tooling bolt holes are determined according to the actual situation. The middle frame positioning tooling 42 can provide height positioning for the middle frame so that the middle frame meets the assembly requirements. The specific number of the middle frame positioning tooling 42 is determined according to the actual situation.

[0052] Furthermore, a plurality of groups of third tooling holes are evenly arranged on the upper end of the lower platform 1, and each group of third tooling holes includes: at least one third tooling positioning hole and at least one third tooling bolt hole; one reverse thrust small rocket bracket positioning tool 43 corresponds to one group of third tooling holes, and the reverse thrust small rocket bracket positioning tool 43 is positioned with the third tooling positioning hole through the third tooling positioning pin, and is connected with the third tooling bolt hole through the third tooling bolt.

[0053] Specifically, the third tooling hole is used to position and install the reverse thrust small rocket bracket positioning tooling 43, and the specific number of groups of third tooling holes depends on the actual situation. The specific number of third tooling positioning holes in each group of third tooling holes and the specific number of third tooling bolt holes are determined according to the actual situation. The reverse thrust small rocket bracket positioning tooling 43 can position the reverse thrust small rocket bracket to meet the installation requirements of the reverse thrust small rocket. The specific number of reverse thrust small rocket bracket positioning tooling 43 depends on the actual situation.

[0054] Further, at least one set of fourth tooling holes is evenly arranged at the upper end of the lower platform 1, and each set of fourth tooling holes includes: at least one fourth tooling positioning hole and at least one fourth tooling bolt hole. The side thrust small rocket bracket positioning tool 44 is positioned by the fourth tooling positioning pin and the fourth tooling positioning hole, and is connected to the fourth tooling bolt hole by the fourth tooling bolt.

[0055] Specifically, the fourth tooling hole is used to position and install the side thrust small rocket bracket positioning tooling 44, and the specific number of groups of the fourth tooling holes is determined according to the actual situation. The specific number of the fourth tooling positioning holes in each group of fourth tooling holes and the specific number of the fourth tooling bolt holes are determined according to the actual situation. The side thrust small rocket bracket positioning tooling 44 can position the side thrust small rocket bracket to meet the installation requirements of the side thrust small rocket.

[0056] Furthermore, at least one group of fifth tooling holes is evenly arranged on the upper end of the lower platform 1, and each group of fifth tooling holes includes: at least one fifth tooling positioning hole and at least one fifth tooling bolt hole; the multifunctional positioning tool 45 is positioned with the fifth tooling positioning pin and the fifth tooling positioning hole, and is connected with the fifth tooling bolt hole through the fifth tooling bolt.

[0057] Specifically, the fifth tooling hole is used to position and install the multifunctional positioning tooling 45, and the specific number of groups of the fifth tooling holes is determined according to the actual situation. The specific number of the fifth tooling positioning holes in each group of the fifth tooling holes and the specific number of the fifth tooling bolt holes are determined according to the actual situation. The multifunctional positioning tooling 45 is equipped with a positioning bracket, and the internal installation platform of the structural cabin is positioned by the positioning bracket. The internal installation platform is used to install cabin components, such as cabin parts and explosive bolt boxes.

[0058] Furthermore, an upper positioning mark is provided at the lower end of the upper platform 2, and a lower positioning mark is provided at the upper end of the lower platform 1. After the upper end of the lower platform 1 is detachably connected to the lower end of the upper platform 2 by a column 3 selected from a plurality of columns 3 according to an assembly mode, the upper positioning mark and the lower positioning mark are aligned with each other.

[0059] Specifically, the assembly reference of the entire cabin section is ensured by the upper positioning mark and the lower positioning mark.

[0060] Furthermore, the upper positioning mark is four upper quadrant lines, but is not limited to four upper quadrant lines. The present application preferably uses four upper quadrant lines; the lower positioning mark is four lower quadrant lines, but is not limited to four lower quadrant lines. The present application preferably uses four lower quadrant lines.

[0061] Specifically, four upper quadrant lines are set at the lower end of the upper platform 2, and four lower quadrant lines are set at the upper end of the lower platform 1. After the upper end of the lower platform 1 is detachably connected to the lower end of the upper platform 2 by a column 3 selected from a variety of columns 3 according to the assembly mode, the four upper quadrant lines are aligned with the four lower quadrant lines, thereby ensuring the assembly reference of the entire cabin section.

[0062] Furthermore, the upper quadrant line is set on the upper platform 2 by carving, and the lower quadrant line is set on the lower platform 1 by carving, but it is not limited to the carving method. The present application prefers the carving method, which is convenient to set.

[0063] Furthermore, the side-thrust small rocket bracket positioning tool 44 is at a certain angle to the lower quadrant line, which can position the side-thrust small rocket bracket and meet the installation requirements of the side-thrust small rocket.

[0064] Specifically, the specific value of the angle is set according to the actual situation.

[0065] Specifically, Figure 2 The schematic diagram of the structure of a composite jig used for riveting the launch vehicle structural compartment is in the first stage tail section assembly mode. The operation flow of the first stage tail section assembly mode is:

[0066] S1: The outrigger 5 is connected to the outrigger positioning hole for positioning on the lower platform 1 through the outrigger positioning pin, and is connected to the outrigger bolt hole for installation on the lower platform 1 through the outrigger bolt. In order to adjust the plane level of the lower platform 1, the outrigger 5 needs to have the function of adjusting the height. Therefore, a pad with adjustable height is placed under the outrigger 5 for adjustment, or a gasket is added under the outrigger 5 to adjust the plane level of the lower platform 1. Among them, the lower platform 1 is hoisted by the lower lifting ear 11 to complete the installation of the lower platform 2.

[0067] S2: The first column 31 is connected to the column positioning hole on the lower platform 1 through the column positioning pin, and is connected to the column bolt hole on the lower platform 1 through the column bolt.

[0068] S3: The first column 31 is connected to the column positioning hole on the upper platform 2 through the column positioning pin, and is connected to the column bolt hole on the upper platform 2 through the column bolt; wherein, the upper platform 2 is hoisted through the upper lifting ear 21 to complete the installation of the upper platform 2.

[0069] S4: Connect with the lower end parts of the structural compartment through multiple groups of lower component holes provided on the lower platform 1; connect with the upper end parts of the structural compartment through multiple groups of upper component holes provided on the upper platform 2, and form a positioning reference with the upper end parts and the lower end parts of the compartment, so as to accurately assemble the rocket compartment.

[0070] S5: After the installation of the upper and lower positioning reference components of the structural compartment is completed, the skin and stringers are laid through the positioning holes on the components to form a stable compartment reference skeleton, so that various components can continue to be assembled on the skeleton.

[0071] S6: The rolling control bearing positioning fixture 41 is installed on the lower platform 1 through the first fixture hole, and the rolling control bearing is installed on the rolling control bearing positioning fixture 41. The position of the rolling control bearing on the structural compartment is located using the positioning reference of the lower platform 1, and the positioning of the rolling control bearing needs to meet the set parallelism, verticality and angle requirements relative to the lower quadrant line on the lower platform 1.

[0072] S7: Based on the upper platform 2, the first column 31 and the lower platform 1, a stable positioning reference three-dimensional coordinate system is formed. After the cabin parts are positioned and installed, rivets and bolts are used to connect the parts. After the riveting assembly is completed, the finished cabin product produced has the characteristics that meet the higher shape, position and size requirements.

[0073] Figure 3 This is a schematic diagram of the structure of an embodiment of a composite jig tooling for riveting a launch vehicle structural compartment in the second and third stage interstage assembly mode. The operation flow of the second and third stage interstage assembly mode is:

[0074] T1: The outrigger 5 is connected to the outrigger positioning hole for positioning on the lower platform 1 through the outrigger positioning pin, and is connected to the outrigger bolt hole for installation on the lower platform 1 through the outrigger bolt. In order to adjust the plane level of the lower platform 1, the outrigger 5 needs to have the function of adjusting the height. Therefore, a height-adjustable pad is placed under the outrigger 5 for adjustment, or a gasket is added under the outrigger 5 to adjust the plane level of the lower platform 1. Among them, the lower platform 1 is hoisted by the lower lifting ear 11 to complete the installation of the lower platform 2.

[0075] T2: The second column 32 is connected to the column positioning hole on the lower platform 1 through the column positioning pin, and is connected to the column bolt hole on the lower platform 1 through the column bolt.

[0076] T3: The second column 32 is connected to the column positioning hole on the upper platform 2 through the column positioning pin, and is connected to the column bolt hole on the upper platform 2 through the column bolt; wherein, the upper platform 2 is hoisted through the upper lifting ear 21 to complete the installation of the upper platform 2.

[0077] T4: The middle frame positioning fixture 42 is connected to the lower platform 1 through multiple sets of second fixture holes. The middle frame is positioned to the set height dimension using the middle frame positioning fixture 42, fixed by the skin, and riveted and assembled after positioning, ensuring that the parallelism, height and coaxiality of the middle frame relative to the upper plane of the lower platform 1 meet the requirements.

[0078] T5: The reverse thrust small rocket bracket positioning fixture 43 is connected to the lower platform 1 through multiple sets of third fixture holes. The reverse thrust small rocket bracket is positioned and installed on the reverse thrust small rocket bracket positioning fixture 43 distributed in an array on the lower platform 1. The reverse thrust small rocket bracket is positioned by the reverse thrust small rocket bracket positioning fixture 43 to ensure that the height of the bracket and the torsion angle relative to the lower quadrant line of the lower platform 1 meet the requirements.

[0079] T6: The side-thrust small rocket bracket positioning fixture 44 is connected to the lower platform through at least one set of fourth fixture holes. The side-thrust small rocket bracket is installed on the side-thrust small rocket bracket positioning fixture 9, which ensures that the side-thrust small rocket bracket meets the deflection angle, relative height, and quadrant line torsion angle requirements relative to the lower platform.

[0080] T7: Connect with the lower end parts of the structural compartment through multiple groups of lower component holes set on the lower platform 1; connect with the upper end parts of the structural compartment through multiple groups of upper component holes set on the upper platform 2, and form a positioning reference with the upper and lower end parts of the compartment, so as to accurately assemble the rocket compartment.

[0081] T8: After the installation of the upper and lower positioning reference components of the structural compartment is completed, the skin and stringers are laid through the positioning holes on the components to form a stable compartment reference skeleton, so that the various components can continue to be assembled on the skeleton.

[0082] T9: Based on the upper platform 2, the second column 32 and the lower platform 1, a stable positioning reference three-dimensional coordinate system is formed. After the cabin parts are positioned and installed, rivets and bolts are used to connect the parts. After the riveting assembly is completed, the finished cabin product produced has the characteristics that meet the higher shape, position and size requirements.

[0083] Specifically, the assembly coordination of the column positioning holes and the column bolt holes used for positioning the columns 3 of different sizes meets the set requirements, and the assembly of the completed jig after replacing the column can still maintain the design dimensional accuracy requirements.

[0084] Figure 4 The schematic diagram of the structure of a composite jig used for riveting the structural compartment of a launch vehicle in a multifunctional compartment assembly mode is shown in FIG. The operation flow of the multifunctional compartment assembly mode is as follows:

[0085] U1: The outrigger 5 is connected to the outrigger positioning hole for positioning on the lower platform 1 through the outrigger positioning pin, and is connected to the outrigger bolt hole for installation on the lower platform 1 through the outrigger bolt. In order to adjust the plane level of the lower platform 1, the outrigger 5 needs to have the function of adjusting the height. Therefore, a pad with adjustable height is placed under the outrigger 5 for adjustment, or a gasket is added under the outrigger 5 to adjust the plane level of the lower platform 1. Among them, the lower platform 1 is hoisted by the lower lifting ear 11 to complete the installation of the lower platform 2.

[0086] U2: The third column 33 is connected to the column positioning hole on the lower platform 1 through the column positioning pin, and is connected to the column bolt hole on the lower platform 1 through the column bolt.

[0087] U3: The third column 33 is connected to the column positioning hole on the upper platform 2 through the column positioning pin, and is connected to the column bolt hole on the upper platform 2 through the column bolt; wherein, the upper platform 2 is hoisted through the upper lifting ear 21 to complete the installation of the upper platform 2.

[0088] U4: The multifunctional positioning fixture 45 is connected to the lower platform 1 via at least one set of fifth fixture holes.

[0089] U5: It is connected with the lower end parts of the structural compartment through multiple groups of lower component holes set on the lower platform 1; it is connected with the upper end parts of the structural compartment through multiple groups of upper component holes set on the upper platform 2, and the upper end parts and lower end parts of the compartment form a positioning reference, so as to accurately assemble the rocket compartment.

[0090] U6: After the installation of the upper and lower positioning reference components of the structural compartment is completed, the skin and stringers are laid through the positioning holes on the components to form a stable compartment reference skeleton, so that various components can continue to be assembled on the skeleton.

[0091] U7: Based on the upper platform 2, the third column 33 and the lower platform 1, a stable positioning reference three-dimensional coordinate system is formed. After the cabin parts are positioned and installed, rivets and bolts are used to connect the parts. After the riveting assembly is completed, the finished cabin product produced has the characteristics that meet the higher shape, position and size requirements.

[0092] Specifically, in the present application, the positioning hole is used for positioning by means of a positioning pin, and the bolt hole is used for fastening by means of a bolt.

[0093] The beneficial effects achieved by this application are as follows:

[0094] (1) The composite jig for riveting launch vehicle structural compartments of the present application enables a single jig to have the function of satisfying the riveting assembly of various rocket structural compartments by replacing columns and positioning jigs.

[0095] (2) The composite jig tooling for riveting the launch vehicle structural compartment of the present application can adjust the horizontality of the lower platform through the support legs and pads / gaskets.

[0096] (3) The composite jig tooling used for riveting the launch vehicle structural compartment of the present application can meet the precise shape and position dimensional accuracy of the parts through the corresponding positioning tooling, thereby being able to meet the special assembly requirements of different structural compartments.

[0097] (4) The composite jig used for riveting the launch vehicle structural compartment of the present application ensures that the scattered parts have an overall positioning reference with the overall missile body after riveting and assembly.

[0098] Although the preferred embodiments of the present application have been described, those skilled in the art may make additional changes and modifications to these embodiments once they are aware of the basic creative concepts. Therefore, the scope of protection of the present application is intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present application. Obviously, those skilled in the art may make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the protection scope of the present application and its equivalent technology, the present application is also intended to include these modifications and variations.

Claims

1. A composite jig for riveting a launch vehicle structural compartment, characterized in that: include: Lower platform, upper platform, various columns and various positioning tools; When in use, a plurality of legs are evenly arranged at the lower end of the lower platform, and the upper end of the lower platform is detachably connected to the lower end of the upper platform through a column selected from a plurality of columns according to the assembly mode; one or more positioning tools selected from a plurality of positioning tools according to the assembly mode are installed on the upper end of the lower platform; the lower end parts of the structural compartment are connected to the lower platform, and the upper end parts of the structural compartment are connected to the upper platform; The plurality of columns at least include: a plurality of first columns, a plurality of second columns and a plurality of third columns; the sizes of the first columns, the sizes of the second columns and the sizes of the third columns are all different; The various positioning tools at least include: multiple rolling control support positioning tools, multiple intermediate frame positioning tools, multiple reverse thrust small rocket bracket positioning tools, side thrust small rocket bracket positioning tools and multifunctional positioning tools; The assembly modes include at least: the first-stage tail section assembly mode, the second- and third-stage interstage section assembly mode, and the multifunctional cabin assembly mode; When the assembly mode is the first-stage tail section assembly mode, the upper end of the lower platform is detachably connected to the lower end of the upper platform through the first column; a plurality of rolling bearing positioning tooling is evenly arranged on the upper end of the lower platform and is detachably connected to the lower platform; When the assembly mode is the second- and third-stage interstage assembly mode, the upper end of the lower platform is detachably connected to the lower end of the upper platform through the second column; multiple intermediate frame positioning tools are evenly arranged at the upper end of the lower platform and are detachably connected to the lower platform; multiple reverse thrust small rocket bracket positioning tools are evenly arranged at the upper end of the lower platform and are detachably connected to the lower platform; the side thrust small rocket bracket positioning tool is arranged at the upper end of the lower platform and is detachably connected to the lower platform; When the assembly mode is the multifunctional cabin assembly mode, the upper end of the lower platform is detachably connected to the lower end of the upper platform through the third column; the multifunctional positioning tooling is arranged at the upper end of the lower platform and is detachably connected to the lower platform.

2. The composite jig tool for riveting the structure compartment of a launch vehicle according to claim 1 is characterized in that: The lower platform is provided with a plurality of groups of lower component holes, each group of lower component holes includes: at least one lower component positioning hole for positioning the lower end components of the structural compartment section and at least one lower component bolt hole for fixing the lower end components of the structural compartment section; the lower end components of the structural compartment section are connected to the lower component positioning hole through the lower component positioning pin, and are connected to the lower component bolt hole through the lower component bolt; A plurality of groups of upper component holes are arranged on the upper platform, and each group of upper component holes includes: at least four upper component positioning holes for positioning the upper end components of the structural compartment and at least four upper component bolt holes for fixing the upper end components of the structural compartment; the upper end components of the structural compartment are positioned through the upper component positioning pins and the upper component positioning holes, and are connected to the upper component bolt holes through the upper component bolts.

3. The composite jig tool for riveting the structure compartment of a launch vehicle according to claim 1, characterized in that: A plurality of lower lifting ears are evenly arranged at the upper end of the lower platform; a plurality of upper lifting ears are evenly arranged at the upper end of the upper platform.

4. The composite jig tool for riveting the structure compartment of a launch vehicle according to claim 1, characterized in that: The upper end of each supporting leg is connected to the lower end of the lower platform, and the lower end of each supporting leg is provided with a pad or a gasket for adjusting the height.

5. The composite jig tool for riveting the structure compartment of a launch vehicle according to claim 1, characterized in that: A plurality of groups of first tooling holes are evenly arranged on the upper end of the lower platform, and each group of first tooling holes includes: at least one first tooling positioning hole and at least one first tooling bolt hole; A rolling control support positioning fixture corresponds to a group of first fixture holes. The rolling control support positioning fixture is positioned through the first fixture positioning pin and the first fixture positioning hole, and is connected with the first fixture bolt hole through the first fixture bolt.

6. The composite jig tool for riveting the structure compartment of a launch vehicle according to claim 1, characterized in that: A plurality of groups of second tooling holes are evenly arranged on the upper end of the lower platform, and each group of second tooling holes includes: at least one second tooling positioning hole and at least one second tooling bolt hole; One middle frame positioning fixture corresponds to a group of second fixture holes. The middle frame positioning fixture is positioned through the second fixture positioning pins and the second fixture positioning holes, and is connected with the second fixture bolt holes through the second fixture bolts.

7. The composite jig tool for riveting the structure compartment of a launch vehicle according to claim 1, characterized in that: A plurality of groups of third tooling holes are evenly arranged on the upper end of the lower platform, and each group of third tooling holes includes: at least one third tooling positioning hole and at least one third tooling bolt hole; A reverse thrust small rocket bracket positioning fixture corresponds to a group of third fixture holes. The reverse thrust small rocket bracket positioning fixture is positioned through the third fixture positioning pin and the third fixture positioning hole, and is connected to the third fixture bolt hole through the third fixture bolt.

8. The composite jig tool for riveting the structure compartment of a launch vehicle according to claim 1, characterized in that: At least one group of fourth tooling holes is evenly arranged at the upper end of the lower platform, and each group of fourth tooling holes includes: at least one fourth tooling positioning hole and at least one fourth tooling bolt hole; The side thrust small rocket bracket positioning tool is positioned by the fourth tool positioning pin and the fourth tool positioning hole, and is connected to the fourth tool bolt through the fourth tool bolt hole.

9. The composite jig tool for riveting the structure compartment of a launch vehicle according to claim 1, characterized in that: At least one group of fifth tooling holes is evenly arranged at the upper end of the lower platform, and each group of fifth tooling holes includes: at least one fifth tooling positioning hole and at least one fifth tooling bolt hole; The multifunctional positioning tool is positioned through the fifth tool positioning pin and the fifth tool positioning hole, and is connected with the fifth tool bolt hole through the fifth tool bolt.

10. The composite jig tool for riveting the structure compartment of a launch vehicle according to claim 1, characterized in that: An upper positioning mark is provided at the lower end of the upper platform, and a lower positioning mark is provided at the upper end of the lower platform. After the upper end of the lower platform is detachably connected to the lower end of the upper platform through a column selected from a variety of columns according to the assembly mode, the upper positioning mark and the lower positioning mark are aligned with each other.

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