阅读说明：本技术 一种运载火箭跨部件取样导管预制制造方法 (Carrier rocket cross-component sampling conduit prefabricating and manufacturing method ) 是由 魏强 苏再为 林彦龙 王露予 刘含伟 宫海铭 王惠苗 李销函 穆菁 武浩男 王静 于 2020-07-31 设计创作，主要内容包括：本发明提供了一种运载火箭跨部件取样导管预制制造方法,包括以下步骤：S1、利用扫描设备进行实物扫描,创建部件点云模型,所述部件点云模型包括后过渡段侧点云模型和发动机侧点云模型；S2、再利用软件将两段点云模型进行虚拟连接,以连接的部件组点云模型为基础建立导管模型；S3、将导管模型导入弯管机加工。本发明所述的运载火箭跨部件取样导管预制制造方法解决了须两部件连接后方可上箭铝丝取样的传统手工加工方式,实现了取样导管预先制造,打破了取样导管与箭体总装串行加工方式。(The invention provides a carrier rocket cross-component sampling pipe prefabricating and manufacturing method, which comprises the following steps: s1, performing real object scanning by using scanning equipment, and creating a component point cloud model, wherein the component point cloud model comprises a rear transition section side point cloud model and an engine side point cloud model; s2, virtually connecting the two point cloud models by using software, and establishing a catheter model on the basis of the connected component group point cloud models; and S3, guiding the catheter model into a pipe bender for machining. The carrier rocket cross-component sampling guide pipe prefabricating manufacturing method solves the problem that the traditional manual processing mode that an aluminum wire can be used for sampling after two components are connected is solved, the sampling guide pipe is manufactured in advance, and the serial processing mode of the sampling guide pipe and rocket body assembly is broken through.)

1. A carrier rocket cross-component sampling pipe prefabricating and manufacturing method is characterized by comprising the following steps:

s1, performing real object scanning by using scanning equipment, and creating a component point cloud model, wherein the component point cloud model comprises a rear transition section side point cloud model and an engine side point cloud model;

s2, virtually connecting the two point cloud models by using software, and establishing a catheter model on the basis of the connected component group point cloud models;

and S3, guiding the catheter model into a pipe bender for machining.

2. The method for prefabricating and manufacturing a carrier rocket cross-member sampling pipe according to claim 1, wherein in step S1, the method is specifically performed as follows:

selecting a strong exposure mode for scanning equipment, and scanning valve bodies related to the installation of the guide pipes in the engine and the rear transition section, reference planes related to the connection of the engine and the rear transition section and positioning holes respectively;

and scanning the relevant boundary of the rear transition section side and the installation of the guide pipe to form a rear transition section side point cloud model, and forming an engine side point cloud model for the relevant boundary condition of the engine side and the installation of the guide pipe.

3. The method of pre-fabricating a launch vehicle cross-component sampling pipe according to claim 1 or 2, wherein: the scanning device includes, but is not limited to, a laser scanning device;

the distance between the scanning device and the measured object is 1-3.5 m.

4. The method for prefabricating and manufacturing a carrier rocket cross-member sampling pipe according to claim 1, wherein the specific implementation method of the step S2 is as follows:

s201, importing the post-transition section side point cloud model and the engine side point cloud model which are obtained by scanning in the step S1 into software;

s202, selecting any 3 points on a reference plane connected with the engine side from a point cloud model at the rear transition section side by using software, and establishing a plane by using a multipoint plane establishing command;

s203, selecting a border on a reference hole connected with the engine side by using software, projecting the border on a plane, and establishing the reference hole by using a contour circle creating command;

s204, selecting 3 reference holes by using software, and establishing a large circle center by using a three-point circle establishing command, namely establishing a reference circle center;

s205, establishing a reference plane, a reference hole and a reference circle center of the point cloud model at the engine side according to the steps S202-S204;

s206, the rear transition section of the rocket and the engine are all cylindrical parts with the same outer diameter, a common plane and a reference hole in a specific direction are arranged on the butt joint surface of the rear transition section and the engine, the reference planes, the reference holes and the reference circle centers of the rear transition section side and the engine side are selected in software to be respectively paired, and the virtual connection of the rear transition section side and the engine side is realized by using a reference alignment command.

5. The method of pre-fabrication of a launch vehicle cross-component sample tube according to claim 2, wherein: in step S2, a specific method for creating a catheter model is as follows:

selecting a valve body end surface and circumferential data by using software and taking a valve body in a virtually connected component group point cloud model as a boundary, establishing an end surface plane 1 and a center line 1, and establishing a center point 1 by using a facial line intersection point establishing command; combining the design of the size of the catheter model, translating the plane 1 by 800mm to establish a plane 2, intersecting the plane 2 with the central line 1 to establish a central point 2, similarly, establishing a central point 3 of the valve body 2 and a central point 4 of the translation plane on the other side of the component group, connecting the central points 1, 2, 3 and 4, guiding round corners through line sections, and sweeping a circular ring to obtain a new catheter model.

6. The method of pre-fabrication of a launch vehicle cross-component sample tube according to claim 1, wherein: after the pipe bending machine is used for machining, the method further comprises a checking process, and specifically comprises the following steps:

scanning the processed sampling guide pipe by adopting scanning equipment, creating a point cloud model, comparing the point cloud model with a new guide pipe model by using software, and judging that the bent pipe is qualified if the deviation value is within a set range, or else, judging that the bent pipe is unqualified.

Technical Field

The invention belongs to the technical field of carrier rockets, and particularly relates to a carrier rocket cross-component sampling pipe prefabricating and manufacturing method.

Background

The guide pipe is an important component of the carrier rocket, is called as a 'blood vessel' of the carrier rocket, mainly plays roles in fuel conveying, pressurizing, pressure measuring, blowing and the like, and plays a decisive role in the success or failure of the carrier rocket in flight. The guide pipe can be divided into a prefabricated guide pipe and a sampling guide pipe according to the manufacturing time, wherein the prefabricated guide pipe is a product which can be directly processed according to a design model, and the sampling guide pipe is a product which can not be processed according to the design model and needs to be processed by combining the actual installation condition of an arrow body due to the processing error of components. The sampling guide pipe is serially connected with the rocket body assembly, and the cycle speed of the rocket body is greatly influenced.

The prior sampling guide pipe has two manufacturing modes, one mode is that an aluminum wire is manually bent on an arrow of a general assembly workshop to simulate the guide pipe trend, and the guide pipe is bent according to the aluminum wire after returning to a guide pipe workshop; and the other method is that the space position of the installation condition of the guide pipe is scanned by laser on an arrow in the final assembly workshop, the installation condition of the guide pipe in the final assembly workshop is reproduced by a robot in the return guide pipe workshop, and then the guide pipe is produced by a method of manually bending an aluminum wire to simulate the trend of the guide pipe.

No matter the direct manual sampling of the aluminum wire is carried out on the arrow in the general assembly workshop or the indirect manual sampling of the aluminum wire is carried out by using a robot in the guide pipe workshop, the processing modes are still in series with the general assembly of the arrow body, and the general assembly speed of the arrow body is limited. The deviation of the part real object from the design model is the root of the failure of the catheter to be processed by the design model.

Disclosure of Invention

In view of the above, the present invention is directed to a method for prefabricating and manufacturing a cross-component sampling guide tube of a launch vehicle, in which a scanning device and a dedicated software are used to perform physical scanning before components are delivered to a final assembly workshop, and the two components are virtually connected by the dedicated software in a computer to establish an accurate component group model, and a new guide tube model is designed based on the model to obtain a guide tube model in advance for manufacturing, so as to solve the problem that the serial connection between the sampling guide tube and an arrow body final assembly restricts the arrow body final assembly speed.

In order to achieve the purpose, the technical scheme of the invention is realized as follows:

a carrier rocket cross-component sampling pipe prefabricating and manufacturing method comprises the following steps:

s1, performing real object scanning by using scanning equipment, and creating a component point cloud model, wherein the component point cloud model comprises a rear transition section side point cloud model and an engine side point cloud model;

s2, virtually connecting the two point cloud models by using software, and establishing a catheter model on the basis of the connected component group point cloud models;

and S3, guiding the catheter model into a pipe bender for machining.

Further, in step S1, the specific implementation method is as follows:

selecting a strong exposure mode for scanning equipment, and scanning valve bodies related to the installation of the guide pipes in the engine and the rear transition section, reference planes related to the connection of the engine and the rear transition section and positioning holes respectively;

and scanning the boundary of the relevant conditions of installation of the rear transition section side and the guide pipe to form a point cloud model of the rear transition section side, and scanning the point cloud of the relevant conditions of installation of the engine side and the guide pipe to form a point cloud model of the engine side.

Further, the scanning device includes, but is not limited to, a laser scanning device;

the distance between the scanning device and the measured object is 1-3.5 m.

Further, the specific implementation method of step S2 is as follows:

s201, importing the post-transition section side point cloud model and the engine side point cloud model which are obtained by scanning in the step S1 into software;

s202, selecting any 3 points on a reference plane connected with the engine side from a point cloud model at the rear transition section side by using software, and establishing a plane by using a multipoint plane establishing command;

s203, selecting a border on a reference hole connected with the engine side by using software, projecting the border on a plane, and establishing the reference hole by using a contour circle creating command;

s204, selecting 3 reference holes by using software, and establishing a large circle center by using a three-point circle establishing command, namely establishing a reference circle center;

s205, establishing a reference plane, a reference hole and a reference circle center of the point cloud model at the engine side according to the steps S202-S204;

s206, the rear transition section of the rocket and the engine are all cylindrical parts with the same outer diameter, a common plane and a reference hole in a specific direction are arranged on the butt joint surface of the rear transition section and the engine, the reference planes, the reference holes and the reference circle centers of the rear transition section side and the engine side are selected in software to be respectively paired, and the virtual connection of the rear transition section side and the engine side is realized by using a reference alignment command.

Further, in step S2, a specific method for creating a catheter model is as follows:

selecting a valve body end surface and circumferential data by using software and taking a valve body in a virtually connected component group point cloud model as a boundary, establishing an end surface plane 1 and a center line 1, and establishing a center point 1 by using a facial line intersection point establishing command; combining the design of the size of the catheter model, translating the plane 1 by 800mm to establish a plane 2, intersecting the plane 2 with the central line 1 to establish a central point 2, similarly, establishing a central point 3 of the valve body 2 and a central point 4 of the translation plane on the other side of the component group, connecting the central points 1, 2, 3 and 4, guiding round corners through line sections, and sweeping a circular ring to obtain a new catheter model.

Further, after the pipe bending machine is used for machining, the method further comprises a checking process, and the checking process specifically comprises the following steps:

scanning the processed sampling guide pipe by adopting scanning equipment, creating a point cloud model, comparing the point cloud model with a new guide pipe model by using software, and judging that the bent pipe is qualified if the deviation value is within a set range, or else, judging that the bent pipe is unqualified.

Compared with the prior art, the method for prefabricating and manufacturing the carrier rocket cross-component sampling pipe has the following advantages:

the carrier rocket cross-component sampling pipe prefabricating manufacturing method provided by the invention utilizes scanning equipment and special software to realize virtual connection of two components in a computer, and establishes a new pipe model for pipe processing on the basis of the virtual connection, so that the traditional manual processing mode that the two components are connected and then can be used for rocket aluminum wire sampling is solved, the sampling pipe prefabricating is realized, and the serial processing mode of the sampling pipe and rocket body assembly is broken through.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:

FIG. 1 is a flow chart of a method for prefabricating and manufacturing a carrier rocket cross-member sampling pipe according to an embodiment of the invention;

FIG. 2 is an assembly view of a plenum duct according to an embodiment of the present invention;

FIG. 3 is a diagram of a component point cloud model according to an embodiment of the present invention;

FIG. 4 is a schematic diagram of creating a plane according to an embodiment of the present invention;

FIG. 5 is a schematic diagram of creating a reference hole (small circle center) according to an embodiment of the present invention;

FIG. 6 is a schematic diagram of creating a reference circle center (large circle center) according to an embodiment of the present invention;

FIG. 7 is a schematic diagram of a virtual connection according to an embodiment of the present invention;

FIG. 8 is a schematic diagram illustrating center point establishment according to an embodiment of the present invention;

FIG. 9 is a schematic view of a catheter model according to an embodiment of the present invention;

fig. 10 is a schematic view of trial assembly on an arrow according to an embodiment of the present invention.

Detailed Description

It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.

The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.

As shown in fig. 1, a method for prefabricating and manufacturing a carrier rocket cross-member sampling pipe comprises the following steps:

the method comprises the steps of establishing a part real object point cloud model by scanning equipment, virtually connecting the part point cloud models by software, establishing a new guide pipe model on the basis of the connected part group point cloud model, guiding the guide pipe model into a pipe bender for machining, scanning a bent part by the scanning equipment, comparing the new guide pipe model with the point cloud model by the software to ensure that the guide pipe is machined to be qualified, loading a rocket on the detected qualified guide pipe for trial installation, and verifying the feasibility of the method.

The method comprises the following specific steps:

1. establishing a component point cloud model

The design method is carried out by taking a certain type of carrier rocket pressurization conduit as an object, wherein one part of the conduit is arranged on an engine, the other part of the conduit is arranged on a rear transition section, the conduit belongs to a typical rocket body crossing sampling conduit, and a product design model is shown in figure 2.

And (3) adopting laser scanning equipment, wherein the distance between the equipment and the measured object is 1-3.5m, 2.5m is the most appropriate, and selecting a strong exposure mode to scan a valve body relevant to the installation of the guide pipe in the engine and the rear transition section, and a reference plane and a positioning hole relevant to the connection of the engine and the rear transition section respectively. The scanning results are shown in fig. 3, wherein a) is the results of the boundary scanning on the rear transition section side and the duct installation, and b) is the results of the boundary scanning on the engine side and the duct installation.

2. Component point cloud model stitching

And importing the point cloud model at the side of the rear transition section and the point cloud model at the side of the engine into special software. Selecting any 3 points on a reference plane connected with the engine side by using special software in a rear transition section side point cloud model, and establishing a plane 1 by using a multipoint plane creation command, as shown in fig. 4; selecting a border on a reference hole connected with the engine side by using special software, projecting the border on the reference hole to the plane 1, and establishing a reference hole (small circle center) by using a contour circle creation command, as shown in fig. 5; special software is used to select 3 reference holes (small circle centers) and a three-point circle establishment command is used to establish a large circle center, as shown in fig. 6. Thus, the creation of the reference plane, the reference hole (direction) and the reference circle center is completed. And establishing a reference plane, a reference hole (direction) and a reference circle center of the point cloud model at the side of the engine in the same way.

The rear transition section and the engine are cylindrical components with the same outer diameter, and a common plane and a reference hole in a specific direction are arranged on the butt joint surface of the cylindrical components. Therefore, the reference planes, the reference holes, and the reference circle centers on the rear transition section side and the engine side are selected in the dedicated software to be paired, and the virtual connection between the rear transition section side and the engine side is realized by the reference alignment command, as shown in fig. 7.

3. Establishing a catheter model

Taking a valve body 1 in a virtually connected component group point cloud model as a boundary, selecting valve body end face and circumferential data by using special software, establishing an end face plane 1 and a center line 1, and establishing a center point 1 by using a facial line intersection point establishing command; combining the design of the size of a catheter model, translating a plane 1 by 800mm to establish a plane 2, intersecting the plane 2 with a central line 1 to establish a central point 2, and similarly establishing a central point 3 of a valve body 2 and a central point 4 of a translation plane on the other side of a component group, as shown in fig. 8. Connecting the central points 1, 2, 3 and 4, and then sweeping a circular ring (the outer diameter of the conduit product) through a line section fillet (the bending radius of the conduit product) to obtain a new conduit model, as shown in fig. 9.

4. Catheter processing and trial fitting

And (3) guiding the new conduit model into a numerical control pipe bender for processing, scanning the bent piece by adopting scanning equipment, comparing the point cloud model of the bent piece with the new conduit model by utilizing special software, and considering the bent pipe to be qualified when the deviation is within the range of +/-1 mm. After the engine is connected with the rear transition section in a real object manner, the guide pipe which is qualified in comparison is subjected to arrow trial installation, as shown in fig. 10.

The method for setting the common reference coordinate for measuring the major components for detection is innovatively applied to the method that a scanning device and special software are utilized, two point cloud models of the major components to be connected of a carrier rocket are virtually butted in a computer, a new guide pipe model is established for subsequent processing on the basis of the point cloud models, and the pre-manufacturing of the carrier rocket sampling guide pipe is realized. The method is the first time at home and abroad.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.