A method for assembling a carrier rocket oblique nose cone

Abstract

The invention discloses a method for assembling a launch vehicle oblique nose cone, which belongs to the field of rocket assembly technology, and comprises assembling the parts required in assembling the launch vehicle oblique nose cone, and cleaning the assembling parts; constructing a main binding structure and an oblique nose cone skeleton structure; laying a skin to a corresponding position on the outer side of the oblique nose cone skeleton, and fixing the skin by riveting to complete the assembly of the launch vehicle oblique nose cone. The invention can be applied to the commercial aerospace field, and improve the assembly quality and efficiency of the oblique nose cone.

Description

Technical Field

[0001] The invention relates to the technical field of rocket assembly, and in particular to an assembling method of an inclined nose cone of a carrier rocket. Background Art

[0002] With the rapid development of commercial aerospace, the carrying capacity and low cost of launch vehicles have become one of the main research contents of structural design. The skin truss structure in the launch vehicle structure has the characteristics of excellent load-bearing efficiency, light weight and low cost.

[0003] The commonly used core stage skin stringer riveting process is to first position the skin and the supporting structure, and then carry out the fastening operation. The fastening operation includes: riveting operation, interference fit bolt operation, etc. The skin stringer structure of the oblique cone structure of the launch vehicle has the characteristics of large size, oblique cone angle, many parts, and high precision of part installation position. The commonly used core stage skin stringer riveting process is difficult to meet the requirements of the launch vehicle oblique cone structure assembly.

[0004] In view of this, it is necessary to provide a new technical solution to solve the above problems. Summary of the invention

[0005] In order to solve the above-mentioned technical problems, the present application provides a method for assembling a launch vehicle oblique nose cone, which can be applied to the assembly of a rocket oblique nose cone with a skin truss structure in a commercial launch vehicle, and improves the assembly quality and efficiency of the oblique nose cone.

[0006] A method for assembling a launch vehicle oblique nose cone, comprising:

[0007] Align the parts needed for the assembling of the launch vehicle's oblique nose cone and clean the aligned parts;

[0008] Build the main binding structure and oblique cone skeleton structure;

[0009] The skin is laid to the corresponding position of the outer side of the oblique nose cone frame and fixed by riveting to complete the assembly of the oblique nose cone of the launch vehicle.

[0010] Preferably, the main bundling structure includes a bundling shell, a main bundling joint and a crossbeam; the opening of the main bundling joint is arranged on the outer side of the bundling shell; the crossbeam is fixed in the bundling shell; the main bundling joint and the crossbeam are arranged on the same straight line; one end of the crossbeam is fixedly connected to the non-open end of the main bundling joint.

[0011] Preferably, the oblique cone skeleton is a cage-type structure, including a lower end frame, a plurality of longitudinal structural members and a plurality of annular frames; the plurality of annular frames are arranged parallel to each other; the lower end of the longitudinal structural member is fixedly connected to the lower end frame; the longitudinal structural member passes through the annular frame and is fixedly connected to the annular frame.

[0012] Preferably, the construction of the main binding structure and the oblique cone skeleton structure includes:

[0013] Position and install the main binding joint and the frame;

[0014] Punch holes between the main binding joints that have been positioned and installed, the binding shells and the cross beams, clean the excess material produced after the punching, and assemble the main binding joints, the binding shells and the cross beams;

[0015] Position and install the lower end frame and the frame;

[0016] Carry out the matching of the connection holes of the longitudinal structural parts and the connection holes of the skin, and handle the excess materials generated by the matching of the connection holes;

[0017] Based on the positioning function of the main bundling structure and the lower end frame, a longitudinal structural member is placed and installed between the bundling shell and the lower end frame;

[0018] The annular frame is positioned using a positioning fixture, and the process skin and longitudinal structural members are used for pre-positioning, and the annular frame is installed.

[0019] Preferably, after the main binding joints and the jig are positioned and installed, the method further includes: using a laser tracker to perform inspection, and if the assembly accuracy does not meet the design requirements, the main binding joints and the jig need to be re-positioned and installed.

[0020] Preferably, the step of laying the skin to the corresponding position of the outer side surface of the oblique nose cone frame and fixing the skin by riveting includes:

[0021] Lay the skin to the corresponding position of the outer side of the oblique nose cone frame and position it using process standard parts;

[0022] After the riveted skin is positioned, check whether there is a gap between adjacent riveted structural parts;

[0023] After ensuring that there is no gap between the skins to be riveted, expand the holes of the parts and perform formal riveting;

[0024] After the skin riveting is completed, clean the excess materials generated during the hole expansion and riveting process.

[0025] Preferably, the parts required for assembling the oblique nose cone of the launch vehicle are put together, and the aligned parts are cleaned, and the parts include oblique nose cone assembly parts and standard parts.

[0026] Preferably, after laying the skin to the corresponding position of the outer side of the oblique nose cone skeleton and fixing the skin by riveting to complete the assembly of the carrier rocket oblique nose cone, it also includes: inspecting the assembled carrier rocket oblique nose cone by using a laser tracker, and storing the carrier rocket oblique nose cone that meets the inspection standards in a warehouse.

[0027] Compared with the prior art, this application has at least the following beneficial effects:

[0028] 1. The present invention can be applied to the assembly of a rocket oblique nose cone having a skin truss structure in a commercial launch vehicle, and improves the assembly quality and efficiency of the oblique nose cone.

[0029] 2. The riveting assembly method adopted by the present invention can effectively improve the assembly quality and reduce the production cost of the oblique cone head. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Hereinafter, some specific embodiments of the present invention will be described in detail in an exemplary and non-limiting manner with reference to the accompanying drawings. The same reference numerals in the accompanying drawings indicate the same or similar components or parts. It should be understood by those skilled in the art that these drawings are not necessarily drawn to scale. In the accompanying drawings:

[0031] Figure 1 This is a flow chart of the method for assembling the oblique nose cone of a carrier rocket of the present invention;

[0032] Figure 2 It is a schematic diagram of the external structure of the oblique nose cone of the launch vehicle of the present invention;

[0033] Figure 3 It is a schematic diagram of the internal structure of the oblique nose cone of the launch vehicle of the present invention.

[0034] The above drawings include the following reference numerals:

[0035] 1. Main bundling structure; 2. Oblique cone skeleton structure; 3. Skin; 11. Bundling shell; 12. Main bundling joint; 13. Crossbeam; 21. Longitudinal structural member; 22. Annular frame; 23. Lower end frame. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical solution and advantages of the present application clearer, the technical solution of the present application will be clearly and completely described below in combination with the specific embodiments of the present application and the corresponding drawings. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present application. Example 1

[0037] like Figure 1 As shown, a method for assembling a carrier rocket oblique nose cone comprises:

[0038] Step S1, aligning the parts required for assembling the oblique nose cone of the launch vehicle, and cleaning the aligned parts;

[0039] Step S2, constructing the main binding structure and the oblique head cone skeleton structure;

[0040] Step S3, laying the skin to the corresponding position of the outer side surface of the oblique nose cone frame, and fixing the skin by riveting, so as to complete the assembly of the oblique nose cone of the launch vehicle. Example 2

[0041] like Figure 2 and Figure 3 As shown, a method for assembling a carrier rocket oblique nose cone is used to assemble the carrier rocket oblique nose cone, wherein the carrier rocket oblique nose cone includes: a main bundling structure 1, an oblique nose cone skeleton structure 2 and a skin 3, the skin 3 is arranged on the outer side surface of the oblique nose cone skeleton structure 2, and is fixedly connected to the oblique nose cone skeleton structure 2 by riveting.

[0042] Specifically, the main bundling structure 1 includes a bundling shell 11, a main bundling joint 12 and a crossbeam 13. The opening of the main bundling joint 12 is arranged on the outer side of the bundling shell 11, and the crossbeam 13 is fixed in the bundling shell 11. The main bundling joint 12 and the crossbeam 13 are arranged on the same straight line, and one end of the crossbeam 13 is fixedly connected to the non-open end of the main bundling joint 12.

[0043] The oblique head cone skeleton structure 2 is a cage structure, including a plurality of longitudinal structural members 21, a plurality of annular frames 22 and a lower end frame 23. The longitudinal structural members 21 are longitudinally arranged beams. The plurality of annular frames 22 are arranged parallel to each other. The lower end of the longitudinal structural member 21 is fixedly connected to the lower end frame 23, and at the same time, the longitudinal structural member 21 passes through the annular frame 22 and is fixedly connected to the annular frame 22.

[0044] In this embodiment, the method for assembling the oblique nose cone of a launch vehicle includes:

[0045] Align the parts, inspect the materials and clean the aligned parts.

[0046] The components include the oblique head cone installation parts and standard parts. The oblique head cone installation parts include the main binding structure 1, the oblique head cone skeleton structure 2 and the skin 3 parts.

[0047] Positioning of the main bundling joint 12. The main bundling joint 12 parts are positioned and installed with the jig, and inspected with a laser tracker. If the assembly accuracy does not meet the design requirements, re-positioning and installation are required. Among them, the jig is a positioning tool for the oblique nose cone of the launch vehicle, which can provide a positioning reference for the oblique nose cone of the launch vehicle. It should be noted that during the assembly process of the oblique nose cone of the launch vehicle, according to the process requirements, the parts of the main bundling structure 1, the oblique nose cone skeleton structure 2 and the skin 3 can also be fixed to the jig to achieve the positioning and assembly of the parts in the oblique nose cone of the launch vehicle.

[0048] The main bundling structure 1 is assembled. After the main bundling joint 12 and the jig are positioned and installed, holes are punched between the main bundling joint 12 and the bundling shell 11 and the crossbeam 13, and the aluminum chips and dust generated by the punching are cleaned, and the main bundling joint 12, the bundling shell 11 and the crossbeam 13 are assembled.

[0049] The lower end frame 23 is positioned. The lower end frame 23 is positioned and installed with the jig. Connection holes are punched on the binding shell 11 and the lower end frame 23 for positioning and installing the longitudinal structural member 21 and the connecting skin. After the connection holes are punched, the aluminum chips and dust generated by the punching are processed.

[0050] Positioning of the longitudinal structural member 21. After the above process, the main binding structure 1 and the lower end frame 23 have been positioned and installed. Based on its positioning function, the upper and lower installation references of the longitudinal structural member 21 have been determined, and the longitudinal structural member 21 is installed with the binding shell 11 and the lower end frame 23.

[0051] The annular frame 22 is positioned. The annular frame 22 is positioned using a positioning tool and pre-positioned using a process skin and the longitudinal structural member 21 .

[0052] At this point, the oblique head cone skeleton structure 2 is completed.

[0053] Positioning the skin 3. Lay the skin 3 to the corresponding position of the oblique cone skeleton structure 2 and position it using process standard parts.

[0054] After the skin 3 to be riveted is positioned, check whether there are gaps caused by processing tolerances and positioning tolerances between adjacent skins 3, between the skin 3 and the oblique cone skeleton structure 2, and between the skin 3 and the binding shell 11. After ensuring that there are no gaps between adjacent structural parts to be riveted, expand the parts and perform formal riveting.

[0055] Excess material treatment. After the skin 3 riveting is completed, the aluminum chips, discarded standard parts and other excess materials and dust generated during the part expansion and riveting are cleaned.

[0056] As another embodiment of the present invention, a method for assembling a carrier rocket oblique nose cone further includes:

[0057] The assembled launch vehicle oblique nose cone is inspected using a laser tracker, and the launch vehicle oblique nose cone that meets the inspection standards is stored in the warehouse.

[0058] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0059] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0060] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein.

[0061] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A method for assembling a launch vehicle oblique nose cone, characterized in that: include: Align the parts needed for the assembling of the launch vehicle's oblique nose cone and clean the aligned parts; Build the main binding structure and oblique cone skeleton structure; The skin is laid to the corresponding position of the outer side of the oblique nose cone frame, and the skin is fixed by riveting to complete the assembly of the oblique nose cone of the launch vehicle; The construction of the main binding structure and the oblique cone skeleton structure includes: Position and install the main binding joint and the frame; Punch holes between the main binding joints that have been positioned and installed, the binding shells and the cross beams, clean the excess material produced after the punching, and assemble the main binding joints, the binding shells and the cross beams; Position and install the lower end frame and the frame; Carry out the matching of the connection holes of the longitudinal structural parts and the connection holes of the skin, and handle the excess materials generated by the matching of the connection holes; Based on the positioning function of the main bundling structure and the lower end frame, a longitudinal structural member is placed and installed between the bundling shell and the lower end frame; The annular frame is positioned using a positioning fixture, and the process skin and longitudinal structural members are used for pre-positioning, and the annular frame is installed.

2. The launch vehicle oblique nose cone assembly method according to claim 1, characterized in that: The main bundling structure includes a bundling shell, a main bundling joint and a crossbeam; the opening of the main bundling joint is arranged on the outer side of the bundling shell; the crossbeam is fixed in the bundling shell; the main bundling joint and the crossbeam are arranged on the same straight line; one end of the crossbeam is fixedly connected to the non-open end of the main bundling joint.

3. The launch vehicle oblique nose cone assembly method according to claim 2, characterized in that: The oblique head cone skeleton is a cage-type structure, including a lower end frame, a plurality of longitudinal structural members and a plurality of annular frames; the plurality of annular frames are arranged parallel to each other; the lower end of the longitudinal structural member is fixedly connected to the lower end frame; the longitudinal structural member passes through the annular frame and is fixedly connected to the annular frame.

4. The method for assembling a launch vehicle oblique nose cone according to claim 3, characterized in that: After the main bundling joints and the jigs are positioned and installed, the following steps are also included: inspection is performed using a laser tracker. If the assembly accuracy does not meet the design requirements, the main bundling joints and the jigs need to be re-positioned and installed.

5. The method for assembling the oblique nose cone of a launch vehicle according to claim 4, characterized in that: The method of laying the skin to the corresponding position of the outer side surface of the oblique head cone frame and fixing the skin by riveting includes: Lay the skin to the corresponding position of the outer side of the oblique nose cone frame and position it using process standard parts; After the riveted skin is positioned, check whether there is a gap between adjacent riveted structural parts; After ensuring that there is no gap between the skins to be riveted, proceed with part hole expansion and formal riveting; After the skin riveting is completed, the excess materials generated during the hole expansion and riveting process are cleaned.

6. The launch vehicle oblique nose cone assembly method according to claim 1, characterized in that: The parts required for assembling the oblique nose cone of the carrier rocket are assembled in a complete manner, and the assembled parts are cleaned. The parts include oblique nose cone assembly parts and standard parts.

7. The method for assembling a launch vehicle oblique nose cone according to any one of claims 1 to 6, characterized in that: After the skin is laid to the corresponding position of the outer side of the oblique nose cone skeleton and fixed by riveting to complete the assembly of the oblique nose cone of the carrier rocket, the method also includes: using a laser tracker to inspect the assembled oblique nose cone of the carrier rocket, and storing the oblique nose cone of the carrier rocket that meets the inspection standards.

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