CN112178298A - Rocket engine pipeline manufacturing process and rocket engine pipeline - Google Patents
Rocket engine pipeline manufacturing process and rocket engine pipeline Download PDFInfo
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- CN112178298A CN112178298A CN202010926086.6A CN202010926086A CN112178298A CN 112178298 A CN112178298 A CN 112178298A CN 202010926086 A CN202010926086 A CN 202010926086A CN 112178298 A CN112178298 A CN 112178298A
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- rocket engine
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L9/00—Rigid pipes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- Bending Of Plates, Rods, And Pipes (AREA)
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Abstract
The invention discloses a rocket engine pipeline manufacturing process and a rocket engine pipeline, which mainly comprise the following steps: establishing a three-dimensional model of a rocket engine pipeline; acquiring characteristic coordinates of a pipeline interface position of an actual rocket engine product; carrying out process parameter correction on a three-dimensional model of the rocket engine pipeline according to the characteristic coordinates, so that the corresponding position in the three-dimensional model is consistent with the characteristic coordinates; compared with the prior art, the method has reasonable design and can improve the working efficiency and the pipeline assembly quality.
Description
The application is filed in 2019, 9, 10 and 10, and is filed in divisional application with the application number of 201910851904.8 and the name of a preparation method of a rocket engine pipeline, the rocket engine pipeline and an engine.
Technical Field
The invention relates to the technical field of structural design of liquid rocket engines, in particular to a rocket engine pipeline manufacturing process and a rocket engine pipeline.
Background
With the rapid development of the aerospace industry, all the technologies related to the rocket field also realize the sudden flying and leap forward, and a rocket engine is the only power source of the rocket and determines the safety and the reliability of the flight.
The pipeline is used as a conveying device for working media such as gas, liquid and the like in the rocket engine, has the characteristics of light weight, easiness in processing, low cost and the like, and is widely applied to various rocket engine products. The quality of the pipeline assembly is directly related to the quality, reliability and service life of the product. The rocket engine pipeline has the characteristics of complex space trend and high working medium pressure.
In the working process of the rocket engine, the pipeline is used as a pressure boundary of working media and is also suitable for the working environment with severe temperature and vibration conditions. The traditional pipeline installation method adopts the steps that a sample piece is bent in advance, filing allowance is reserved at two ends of a pipeline during bending, then the pipeline is repaired and positioned on an engine through an actual interface position, then the pipeline is taken down and welded with pipeline connecting pieces at the two ends, and finally the pipeline is assembled on the engine.
Because the interface position all can have the deviation at every turn, the pipe of bending in advance according to the appearance piece is difficult to guarantee that the interface position satisfies the operation requirement, has increased the work load of repairing, simultaneously because welding deformation is unknown, need carry out many times repair, location and welding, work load multiplication, work efficiency are low, seriously influence the production progress. In addition, the traditional pipeline installation method is difficult to effectively control the installation position degree of the pipeline, is not beneficial to reducing the assembly stress of the pipeline and improves the assembly quality.
Therefore, how to provide a novel pipeline preparation method which has reasonable design and can improve the working efficiency and the pipeline assembly quality is a problem to be solved at present.
Disclosure of Invention
The invention aims to provide a rocket engine pipeline manufacturing process and a rocket engine pipeline.
In order to achieve the purpose, the invention provides the following technical scheme: a manufacturing process of a rocket engine pipeline is characterized by establishing a three-dimensional model of the rocket engine pipeline; acquiring characteristic coordinates of a pipeline interface position of an actual rocket engine product; carrying out process parameter correction on a three-dimensional model of the rocket engine pipeline according to the characteristic coordinates, so that the corresponding position in the three-dimensional model is consistent with the characteristic coordinates; the method comprises the steps of producing an actual pipeline of the rocket engine according to a corrected three-dimensional model of a pipeline of the rocket engine, carrying out reverse modeling on the actual pipeline of the rocket engine before producing the actual pipeline of the rocket engine according to the corrected three-dimensional model of the pipeline of the rocket engine, obtaining the three-dimensional model of the actual pipeline of the rocket engine, carrying out first comparison on the three-dimensional model of the actual pipeline of the rocket engine and the corrected three-dimensional model of the pipeline of the rocket engine to obtain a deviation amount of product process parameters, adjusting parameters of the three-dimensional model according to the deviation amount, and obtaining the corrected three-dimensional model after the first comparison.
Preferably, after obtaining the three-dimensional model after the first comparison, the method further includes: and carrying out secondary comparison on the three-dimensional model of the actual pipeline of the rocket engine and the three-dimensional model corrected after the primary comparison to obtain the deviation of the technological parameters of the product, and adjusting the parameters of the three-dimensional model again according to the deviation.
Preferably, the three-dimensional model of the rocket engine pipeline is established by a rocket engine digital prototype.
Preferably, the coordinates of the center of the actual rocket motor pipeline interface obtained by scanning.
Preferably, the process parameters include a bending radius, a length of a straight line segment, a bending angle and a torsion angle.
Preferably, the characteristic coordinates are obtained by three-dimensionally scanning the actual rocket engine pipeline interface position through a three-dimensional scanning device, and the three-dimensional scanning device comprises a laser vector measuring instrument.
Preferably, the producing the actual pipeline of the rocket engine according to the corrected three-dimensional model of the pipeline of the rocket engine further comprises: and performing reverse modeling on the actual pipeline of the rocket engine, namely acquiring a three-dimensional model of the actual pipeline of the rocket engine, and comparing the three-dimensional model of the actual pipeline of the rocket engine with the corrected three-dimensional model of the pipeline of the rocket engine to obtain the deviation of the product process parameters.
Preferably, the actual pipeline of the rocket engine is scanned by a three-dimensional scanning device to obtain a three-dimensional model of the actual pipeline of the rocket engine.
Preferably, the rocket engine pipeline comprises a conduit and a pipeline connecting piece, and the conduit and the pipeline connecting piece which are actually produced are welded together through a positioning tool platform before reverse modeling.
The embodiment also provides a rocket engine pipeline which is obtained by adopting the manufacturing process of the rocket engine pipeline.
Compared with the prior art, the invention has the beneficial effects that: a manufacturing process of a rocket engine pipeline comprises the following specific steps of establishing a three-dimensional model of the rocket engine pipeline; secondly, acquiring characteristic coordinates of the pipeline interface position of an actual rocket engine product; thirdly, correcting process parameters of a three-dimensional model of the rocket engine pipeline according to the characteristic coordinates to enable the corresponding position in the three-dimensional model to be consistent with the characteristic coordinates; fourthly, reverse modeling is carried out on the actual pipeline of the rocket engine, a three-dimensional model of the actual pipeline of the rocket engine is obtained, the three-dimensional model of the actual pipeline of the rocket engine is compared with the corrected three-dimensional model of the pipeline of the rocket engine for the first time, deviation of technological parameters of products is obtained, parameters of the three-dimensional model are adjusted according to the deviation, and the corrected three-dimensional model after the first comparison is obtained; and fifthly, producing the actual pipeline of the rocket engine according to the corrected three-dimensional model of the pipeline of the rocket engine. The method is characterized in that a three-dimensional model of the rocket engine pipeline is consistent with characteristic coordinates of an actual pipeline interface of the engine by modeling the rocket engine pipeline and adjusting process parameters, so that the three-dimensional model of the rocket engine pipeline is produced, and the actual rocket engine conduit is fixedly connected with the engine pipeline interface. The invention solves the problem of accurate forming and installation of pipelines in a complex space of the rocket engine, improves the working efficiency, can quantitatively control the assembly position, effectively reduces the assembly stress of the pipelines, improves the assembly quality, has strong applicability, and can be used for manufacturing and assembling all pipelines of the rocket engine.
Drawings
FIG. 1 is a flow chart of a process for manufacturing rocket engine pipelines according to the present invention;
FIG. 2 is a perspective view of a three-dimensional model of a rocket motor pipeline of the present invention;
FIG. 3 is a front view of a conduit of the rocket motor circuit of the present invention;
FIG. 4 is a left side view of a conduit of the rocket motor line of the present invention;
FIG. 5 is a schematic structural view of characteristic coordinates of a pipeline interface location of an actual rocket engine product of the present invention;
FIG. 6 is a schematic structural view of a three-dimensional model of a rocket engine pipeline for process parameter modification in accordance with the present invention;
description of reference numerals:
1 pipeline connector and 2 guide pipe
3 interface center coordinate position
Detailed Description
For the purpose of promoting a clear understanding of the objects, aspects and advantages of the embodiments of the invention, reference will now be made to the drawings and detailed description, wherein there are shown in the drawings and described in detail, various modifications of the embodiments described herein, and other embodiments of the invention will be apparent to those skilled in the art.
The exemplary embodiments of the present invention and the description thereof are provided to explain the present invention and not to limit the present invention. Additionally, the same or similar numbered elements/components used in the drawings and the embodiments are used to represent the same or similar parts.
As used herein, the terms "first," "second," …, etc., do not denote any order or sequence, nor are they used to limit the present invention, but rather are used to distinguish one element from another or from another element or operation described in the same technical language.
With respect to directional terminology used herein, for example: up, down, left, right, front or rear, etc., are simply directions with reference to the drawings. Accordingly, the directional terminology used is intended to be illustrative and is not intended to be limiting of the present teachings.
As used herein, the terms "comprising," "including," "having," "containing," and the like are open-ended terms that mean including, but not limited to.
As used herein, "and/or" includes any and all combinations of the described items.
As used herein, the terms "substantially", "about" and the like are used to modify any slight variation in quantity or error that does not alter the nature of the variation. Generally, the range of slight variations or errors modified by such terms may be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments, or other values. It should be understood by those skilled in the art that the aforementioned values can be adjusted according to actual needs, and are not limited thereto.
Certain words used to describe the present application are discussed below or elsewhere in this specification to provide additional guidance to those skilled in the art in describing the present application.
Embodiments of the present invention provide a process for fabricating rocket motor lines, as shown in figures 1, 2 and 6,
establishing a three-dimensional model of a rocket engine pipeline;
acquiring characteristic coordinates of a pipeline interface position of an actual rocket engine product;
carrying out process parameter correction on a three-dimensional model of the rocket engine pipeline according to the characteristic coordinates, so that the corresponding position in the three-dimensional model is consistent with the characteristic coordinates;
and producing the actual pipeline of the rocket engine according to the corrected three-dimensional model of the pipeline of the rocket engine.
Specifically, the method comprises the following steps: the manufacturing process of the rocket engine pipeline comprises the following steps: firstly, establishing a three-dimensional model of a rocket engine pipeline; secondly, acquiring characteristic coordinates of the pipeline interface position of an actual rocket engine product; thirdly, correcting process parameters of a three-dimensional model of the rocket engine pipeline according to the characteristic coordinates to enable the corresponding position in the three-dimensional model to be consistent with the characteristic coordinates; fourthly, reverse modeling is carried out on the actual pipeline of the rocket engine, a three-dimensional model of the actual pipeline of the rocket engine is obtained, the three-dimensional model of the actual pipeline of the rocket engine is compared with the corrected three-dimensional model of the pipeline of the rocket engine for the first time, deviation of technological parameters of products is obtained, parameters of the three-dimensional model are adjusted according to the deviation, and the corrected three-dimensional model after the first comparison is obtained; and fifthly, producing the actual pipeline of the rocket engine according to the corrected three-dimensional model of the pipeline of the rocket engine. The method is characterized in that a three-dimensional model of the rocket engine pipeline is consistent with characteristic coordinates of an actual pipeline interface of the engine by modeling the rocket engine pipeline and adjusting process parameters, so that the three-dimensional model of the rocket engine pipeline is produced, and the actual rocket engine conduit is fixedly connected with the engine pipeline interface. The invention solves the problem of accurate forming and installation of pipelines in a complex space of the rocket engine, improves the working efficiency, can quantitatively control the assembly position, effectively reduces the assembly stress of the pipelines, improves the assembly quality, has strong applicability, can be used for manufacturing and assembling all pipelines of the rocket engine, and has reasonable design.
It should be noted that, for convenience of modeling, a three-dimensional model of the rocket engine pipeline is established by a rocket engine digital prototype. Further, the position of the pipeline interface of the actual rocket engine is scanned in three dimensions by the three-dimensional scanning equipment, and characteristic coordinates are obtained. In the present embodiment, for accurate scanning, the three-dimensional scanning apparatus may employ a laser vector meter.
In addition, obtaining the three-dimensional model after the first comparison further comprises: and carrying out secondary comparison on the three-dimensional model of the actual pipeline of the rocket engine and the three-dimensional model corrected after the primary comparison to obtain the deviation of the technological parameters of the product, and adjusting the parameters of the three-dimensional model again according to the deviation.
In addition, as shown in fig. 5, in the present embodiment, for convenience of positioning, the characteristic coordinates include a coordinate position 3 of the center of the pipeline interface of the actual rocket engine obtained by scanning. It should be noted that the characteristic coordinates of the actual rocket engine pipeline may be changed according to the actual situation, for example, the characteristic coordinates may also be the position of the end face of the actual rocket engine pipeline.
It should be noted that, as shown in fig. 3, 4 and 6, for convenience of measurement, the three-dimensional model of the rocket engine pipeline is convenient to adjust, and the process parameters include a bending radius R, a straight line segment length Y, a bending angle B and a torsion angle C.
After the rocket engine pipeline is produced, reverse modeling is carried out on the actual pipeline of the rocket engine, namely a three-dimensional model of the actual pipeline of the rocket engine is obtained, and the three-dimensional model of the actual pipeline of the rocket engine is compared with the corrected three-dimensional model of the rocket engine pipeline to obtain the deviation amount of the product process parameters. For example, the deviation amounts can be stored for later use, for example, parameters of the three-dimensional model can be further adjusted according to the deviation amounts, and by repeatedly iterating and repeatedly adjusting theoretical model parameters, the precision of rocket engine pipelines in subsequent actual production can be higher, and meanwhile, the workload can be reduced, and the production efficiency can be improved.
As mentioned above, the three-dimensional model of the rocket engine pipeline with reverse modeling is compared with the three-dimensional model of the engine pipeline after correction, and the deviation of the process parameters of the rocket engine pipeline and the engine pipeline is obtained. For example, the process parameters may include the deviation amounts of the axial tightness a, the radial tightness B and the deflection tightness C of the product, so that the corrected three-dimensional model may be further adjusted according to the deviation amounts to reduce the deviation amount between the actual three-dimensional model and the corrected three-dimensional model.
In order to not affect the working efficiency obviously, a better three-dimensional model can be obtained through 3-4 times of iterative comparison and correction. After the deviation is obtained for the first time, the model is reversely adjusted according to the deviation, the rocket engine pipeline is continuously produced according to the model after the secondary adjustment, then the actual three-dimensional modeling is carried out on the pipeline after the secondary production, and the deviation is obtained by comparing with the model after the secondary adjustment. And judging whether the previous adjusting direction is correct or not according to the change of the deviation amount, if the deviation amount is further reduced, the previous adjusting direction is correct, and further adjusting on the basis until the deviation amount starts to increase so as to obtain the optimal three-dimensional model. For example, the three-dimensional model may be used as a production basis for subsequent rocket engine lines. According to the pipeline preparation method provided by the embodiment of the invention, through repeated comparison of the theoretical model and the actual model, the difference between the theoretical model and the actual product model can be reduced to the maximum extent, the optimal theoretical model is obtained, and the product quality of the actual rocket engine pipeline is improved.
As shown in fig. 3, 4 and 6, wherein: (the relationship of these parameters in the present invention is described below)
M-the maximum axial clearance between the connecting pieces when the pipeline is in the free position;
n-minimum axial clearance between the connecting pieces when the pipeline is in a free position;
when L-corresponds to the M, N position, the maximum radial offset of the connecting piece is outwards supported;
a-axial tightness, a ═ M + N)/2;
b-radial tightness, B ═ L;
c skew tightness, C ═ M-N
It is specifically noted that the process parameters of the three-dimensional model of the rocket engine pipeline may also be replaced by coordinate points.
Specifically, as shown in fig. 2, 3 and 4, the actual pipeline of the rocket engine may be scanned by a three-dimensional scanning device to obtain a three-dimensional model of the actual pipeline of the rocket engine. In addition, the rocket engine pipeline contains pipeline connecting piece 1 and pipe 2, before reverse modeling, in order to reduce deformation of the pipeline connecting piece 1 and the pipe 2 in the welding process, the pipeline connecting piece 1 and the pipe 2 which are actually produced need to be placed on a positioning tool platform for welding. In order to ensure that the pipeline connecting piece 1 and the conduit 2 are tight and more firm in fixation and avoid deformation, the pipeline connecting piece and the conduit can be integrally formed. It is worth mentioning that before the pipeline connecting piece 1 and the conduit 2 are welded, the conduit 2 needs to be subjected to flaw scanning through an infrared scanner, cracks or leak holes are avoided, the conduit 2 is ensured to be intact, it needs to be noted that in order to meet different requirements of the rocket engine pipeline, the wall thickness, the rigidity and the like of the pipeline connecting piece 1 and the conduit 2 can be recorded in process parameters, the use is convenient, and the comprehensiveness of a three-dimensional model of the rocket engine is improved.
The above embodiments may be combined with each other with corresponding technical effects.
The embodiment also provides a rocket engine pipeline which is obtained by adopting the manufacturing process of any one of the rocket engine pipelines.
The foregoing is merely an illustrative embodiment of the present invention, and any equivalent changes and modifications made by those skilled in the art without departing from the spirit and principle of the present invention should fall within the protection scope of the present invention.
Claims (10)
1. A rocket engine pipeline manufacturing process is characterized in that:
establishing a three-dimensional model of a rocket engine pipeline;
acquiring characteristic coordinates of a pipeline interface position of an actual rocket engine product;
carrying out process parameter correction on a three-dimensional model of the rocket engine pipeline according to the characteristic coordinates, so that the corresponding position in the three-dimensional model is consistent with the characteristic coordinates;
producing an actual pipeline of the rocket engine according to the corrected three-dimensional model of the pipeline of the rocket engine;
before the actual pipeline of the rocket engine is produced according to the corrected three-dimensional model of the rocket engine pipeline, reverse modeling is carried out on the actual pipeline of the rocket engine to obtain the three-dimensional model of the actual pipeline of the rocket engine, the three-dimensional model of the actual pipeline of the rocket engine is compared with the corrected three-dimensional model of the rocket engine pipeline for the first time to obtain the deviation amount of the technological parameters of the product, the parameters of the three-dimensional model are adjusted according to the deviation amount, and the corrected three-dimensional model after the first comparison is obtained.
2. A rocket engine conduit fabrication process according to claim 1, wherein: after obtaining the three-dimensional model after the first comparison, the method further comprises the following steps:
and carrying out secondary comparison on the three-dimensional model of the actual pipeline of the rocket engine and the three-dimensional model corrected after the primary comparison to obtain the deviation of the technological parameters of the product, and adjusting the parameters of the three-dimensional model again according to the deviation.
3. A rocket engine conduit fabrication process according to claim 1, wherein: and the three-dimensional model of the rocket engine pipeline is established by a rocket engine digital prototype.
4. A rocket engine conduit fabrication process according to claim 1, wherein: the characteristic coordinates include center coordinates of the actual rocket engine pipeline interface obtained by scanning.
5. A rocket engine conduit fabrication process according to claim 1, wherein: the technological parameters comprise bending radius, straight line segment length, bending angle and torsion angle.
6. A rocket engine conduit fabrication process according to claim 1, wherein: and three-dimensional scanning is carried out on the position of the actual rocket engine pipeline interface through a three-dimensional scanning device to obtain the characteristic coordinates, wherein the three-dimensional scanning device comprises a laser vector measuring instrument.
7. A rocket engine conduit fabrication process according to claim 1, wherein: the producing the actual pipeline of the rocket engine according to the corrected three-dimensional model of the pipeline of the rocket engine further comprises: and performing reverse modeling on the actual pipeline of the rocket engine, namely acquiring a three-dimensional model of the actual pipeline of the rocket engine, and comparing the three-dimensional model of the actual pipeline of the rocket engine with the corrected three-dimensional model of the pipeline of the rocket engine to obtain the deviation of the product process parameters.
8. A rocket engine pipeline manufacturing process according to claim 7, wherein: and scanning the actual pipeline of the rocket engine through a three-dimensional scanning device to obtain a three-dimensional model of the actual pipeline of the rocket engine.
9. A rocket engine conduit fabrication process according to claim 7, wherein: the rocket engine pipeline comprises a guide pipe and a pipeline connecting piece, and the guide pipe and the pipeline connecting piece which are actually produced are welded together through a positioning tool platform before reverse modeling.
10. A rocket engine pipeline, characterized in that: obtained by a process for manufacturing rocket engine pipelines according to any one of claims 1-9.
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| CN202010926086.6A CN112178298B (en) | 2019-09-10 | 2019-09-10 | Preparation method of rocket engine pipeline, rocket engine pipeline and engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910851904.8A CN110748709B (en) | 2019-09-10 | 2019-09-10 | Preparation method of rocket engine pipeline, rocket engine pipeline and engine |
| CN202010926086.6A CN112178298B (en) | 2019-09-10 | 2019-09-10 | Preparation method of rocket engine pipeline, rocket engine pipeline and engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115130352A (en) * | 2022-07-14 | 2022-09-30 | 北京航空航天大学 | Automatic modeling and analyzing method for complex pipeline system of rocket engine |
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Also Published As
| Publication number | Publication date |
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| CN110748709A (en) | 2020-02-04 |
| CN110748709B (en) | 2021-03-19 |
| CN112178298B (en) | 2022-06-17 |
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