Low temperature resistant flexible joint forming method for solid rocket motor

A low-temperature flexible, solid rocket technology, applied in the field of structural parts molding, can solve the problems of lower production efficiency and product quality, low strength of cold-bonded interface, narrow applicable temperature range of connecting parts, etc., and achieve improved production efficiency and product quality, good Mechanical properties and manufacturability, and the effect of improving field adaptability

Active Publication Date: 2019-04-12
湖北三江航天江北机械工程有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this forming method has the following disadvantages: 1) The resulting joint has a narrow applicable temperature range and poor low temperature resistance; 2) The cold bonding interface strength of the front and rear flanges is lower than the hot bonding strength. It is easy to cause air leakage, debonding and unstable swing torque, which greatly reduces production efficiency and product quality; 3) It is inconvenient to operate, and at least two sets of tooling should be borrowed during molding

Method used

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  • Low temperature resistant flexible joint forming method for solid rocket motor

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Experimental program
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Effect test

Embodiment 1

[0024] For such as figure 1 For a certain type of flexible joint shown, the forming process includes the following steps:

[0025] 1) According to the requirements of the flexible joint structure, 10 concentric ring-shaped metal reinforcements 1 with a thickness of 3 mm and different diameters are processed. The metal reinforcements 1 are processed from 30CrMnSiA forgings. According to the structure of the flexible joint, 30CrMnSiA forgings are used to process the fixed rear joint 4 and the movable inverted cone shell 3, and 16 threaded holes are evenly distributed on the end surface. The low-temperature-resistant butadiene is produced into sheets using an open mill, and 11 annular elastic members 2 with a thickness of 2.0-2.10 mm are cut out according to the size requirements.

[0026] 2) Perform sandblasting on both sides of the metal reinforcement, joints after fixing, and the adhesive surface of the movable inverted cone shell, and clean the metal reinforcement after sand...

Embodiment 2

[0034] A method for forming a low-temperature-resistant flexible joint for solid rocket motors, comprising the following steps:

[0035] 1) According to the requirements of the flexible joint structure, a plurality of concentric ring-shaped metal reinforcements with a thickness of 3 mm and different diameters are processed. The metal reinforcements are processed from 30CrMnSiA forgings. According to the flexible joint structure, the fixed rear joint and the movable inverted cone shell are processed by 30CrMnSiA forging, and the end surface is evenly distributed with threaded holes. Use an open mill to produce low-temperature-resistant butadiene sheets, and cut out multiple annular elastic parts with different diameters and thicknesses of 2.0-2.10mm according to the size requirements.

[0036] 2) Perform sandblasting on both sides of the metal reinforcement, joints after fixing, and the adhesive surface of the movable inverted cone shell, and clean the metal reinforcement after...

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Abstract

The invention discloses a forming method for a low-temperature-resistant flexible connector for a solid rocket engine. The forming method includes the steps that (1) a plurality of annular metal reinforcement parts and elastic parts are prepared; (2) the elastic parts and the metal reinforcement parts are bonded to the surface of a fixed rear connector / movable inverted cone shell alternately, the innermost side and the outermost side directly bonded with the fixed rear connector / movable inverted cone shell are provided with the elastic parts, and finally the movable inverted cone shell / fixed rear connector is bonded with the elastic parts on the outermost side to form an integrated part; and (3) the integrated part is put into a mould and subjected to sulfidizing treatment, the temperature is 145-155 DEG C, the pressure is 5-10 MPa, the heat preservation time is 30-60 min, and the flexible connector is obtained after demoulding. According to the forming method for the low-temperature-resistant flexible connector for the solid rocket engine, the movable inverted cone shell, the fixed rear connector, the elastic parts and the metal reinforcement parts are subjected to hot sticking forming overall, the phenomena that an existing flexible connector is prone to cause air leakage, prone to sticking failure, and unstable in shaking moment are solved, and the flexible connector can be used at the temperature of minus 40-50 DEG C for a long time.

Description

technical field [0001] The invention relates to a structural part forming technology, in particular to a forming method for a low temperature resistant flexible joint used in a solid rocket motor. Background technique [0002] The flexible joint on the solid rocket motor is used to connect the movable part of the nozzle with the fixed part, and realize the sealing between the movable part and the fixed part, which is widely used in many missile models. As the connection between the fixed body and the movable body of the flexible nozzle of the solid rocket motor, the flexible joint bears the pressure of the combustion chamber, the asymmetric force and the acceleration load when the nozzle swings. [0003] Flexible joints are the main structural form of solid rocket motor thrust vector control, so the structure and forming process of flexible joints are very important. At present, the molding of flexible joints is generally formed by first hot-bonding the reinforcement / elasto...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C65/70B29C65/52B29C35/02
CPCB29C35/02B29C65/52B29C65/70B29C66/02245B29C66/026B29C66/742
Inventor 肖雯静谭云水张志斌邓德凤曾甜甜
Owner 湖北三江航天江北机械工程有限公司
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