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A rocket engine flange rapid design system based on a visual interface

A rocket engine and design system technology, which is applied in computing, instrumentation, electrical and digital data processing, etc., can solve the problems of long design cycle and complex design process of rocket engine flanges, and achieves improving design work efficiency, lowering the threshold and shortening the design. effect of cycles

Active Publication Date: 2019-06-18
北京宇航推进科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The technical problem to be solved by the present invention is to provide a rapid rocket engine flange design system based on a visual interface for the defects of long design cycle and complicated design process of rocket engine flanges in the prior art

Method used

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  • A rocket engine flange rapid design system based on a visual interface
  • A rocket engine flange rapid design system based on a visual interface
  • A rocket engine flange rapid design system based on a visual interface

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specific Embodiment approach 1

[0049] DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS One, the first aspect of the present invention provides a rocket engine flange rapid design system based on a visual interface, the system obtains a visual interface based on VB programming, combined figure 1 shown, including:

[0050] The material selection module 110 is used to determine the material of the flange and the conduit according to the maximum pressure of the engine system and the inner diameter of the conduit at the maximum pressure;

[0051] The conduit wall thickness calculation module 120 is used to calculate and obtain the conduit wall thickness according to the conduit design safety factor;

[0052] The flange structure parameter calculation module 130 is used to calculate and obtain the initial flange structure parameters according to the wall thickness of the conduit;

[0053] The graphite sealing ring parameter calculation module 140 is used to calculate and obtain the parameters of the graphite seal...

Embodiment

[0106] Embodiment: the highest pressure of the engine system of the flange to be designed is 15MPa, the operating temperature is 110K, and the inner diameter of the conduit at the highest pressure is 80mm;

[0107] Use the material selection module to determine that flanges, bolts, and piping materials are all GH4169; and then through the metal material manual, it is determined that the yield limit of GH4169 is about 1080Mpa at a temperature of 110K; when n is 2 and μ is 0.8, the conduit can be calculated Wall thickness δ i for:

[0108]

[0109] Here, the medium pressure at the flange is the same as the maximum pressure of the engine system, and the inner diameter of the conduit at the flange is the same as the inner diameter of the conduit at the highest pressure.

[0110] The wall thickness of the conduit is rounded to 2mm; Δδ is 1mm, and the thickness of the small end of the flange taper neck is δ 0 3mm; flange neck height h is 25mm; flange neck taper angle θ is 30°; ...

specific Embodiment approach 2

[0136] Embodiment 2. Another aspect of the present invention also provides a rapid design method for a rocket engine flange based on a visual interface, combining image 3 As shown, the method obtains a visual interface based on VB programming, including:

[0137] Using the material selection module, the step of determining the material of the flange and the conduit according to the maximum pressure of the engine system and the internal diameter of the conduit at said maximum pressure;

[0138] Using the conduit wall thickness calculation module to calculate and obtain the conduit wall thickness according to the conduit design safety factor;

[0139] using the flange structure parameter calculation module to calculate the initial flange structure parameters according to the conduit wall thickness;

[0140] Using the graphite sealing ring parameter calculation module to calculate and obtain the parameters of the graphite sealing ring according to the wall thickness of the cond...

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Abstract

The invention relates to a rocket engine flange rapid design system based on a visual interface. The method comprises steps of adopting a material selection module to determine a flange and a conduitmaterial according to the highest pressure of an engine system and the conduit inner diameter at the highest pressure; calculating the wall thickness of the catheter according to the designed safety factor of the catheter; calculating according to the wall thickness of the guide pipe to obtain initial flange structure parameters; calculating according to the wall thickness of the conduit to obtainparameters of the graphite sealing ring; finally, calculating according to the current flange structure parameters, and judging whether the current flange structure meets the flange strength safety factor design requirements or not; and if not, increasing the effective thickness of the flange according to a preset rule, and returning to a flange strength safety coefficient checking module to carry out judgment again until the current flange structure meets the flange strength safety coefficient design requirement. Structural design parameters of the flange can be rapidly and effectively obtained, and it is guaranteed that the finally-designed flange meets the strength safety coefficient design requirement.

Description

technical field [0001] The invention relates to the technical field of design of rocket engine flanges, in particular to a rapid design system for rocket engine flanges based on a visual interface. Background technique [0002] The flange connection structure is a commonly used connection structure on the cryogenic liquid rocket engine pipeline, and the graphite seal is a commonly used seal on the flange connection structure. The design process of the existing flange connection structure is: first select the parameter values ​​of the flange structure according to experience, and then perform finite element strength analysis on the designed flange connection structure, or check the strength of the flange through Excel to determine whether the flange strength is Meet the design requirements. If the designed flange structure does not meet the strength requirements, re-modify the parameters and re-check the analysis until the strength meets the design requirements. [0003] It...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 潘浩王明哲郭利明刘业奎李文鹏李强左安军孙侃余鹏冯磊
Owner 北京宇航推进科技有限公司
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