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Preparation method for seal head-free fiber reinforced resin-based composite material combustion chamber shell of rocket projectile

A fiber-reinforced resin and composite material technology, which is applied in the field of polymer-based composite material preparation, can solve the problems of poor heat insulation, low blasting strength, heavy weight, etc., and achieve the effects of increasing strength, increasing blasting pressure, and increasing shear strength.

Active Publication Date: 2020-04-10
HARBIN FRP INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention aims to solve the technical problems of poor heat insulation, low blasting strength and heavy mass in the combustion chamber casing prepared by the existing method, and provides a fiber-reinforced resin-based composite combustion chamber casing for rockets without a head preparation method

Method used

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  • Preparation method for seal head-free fiber reinforced resin-based composite material combustion chamber shell of rocket projectile
  • Preparation method for seal head-free fiber reinforced resin-based composite material combustion chamber shell of rocket projectile
  • Preparation method for seal head-free fiber reinforced resin-based composite material combustion chamber shell of rocket projectile

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specific Embodiment approach 1

[0028] Embodiment 1: In this embodiment, a method for preparing a headless fiber-reinforced resin-based composite combustion chamber shell for rockets is specifically carried out in the following steps:

[0029] 1. Milling the surface of the outer ring of the metal ring to form a uniformly arranged wire hanging table to obtain a metal wire hanging ring;

[0030] 2. Assemble the inner lining material and the metal hanging wire ring on the mandrel to obtain the assembly parts;

[0031] 3. Put the fiber yarn into the modified epoxy resin glue for dipping, and then wrap it on the surface of the assembly obtained in step 2 to obtain the shell prefabricated part;

[0032] 4. Heat the shell preform to 90-100°C and keep it warm for 1-2 hours, then heat it to 110-120°C and keep it warm for 1-2 hours, then heat it up to 150-160°C and keep it warm for 4-6 hours, then cool and demould. The combustion chamber casing is obtained, and the preparation method of the headless fiber-reinforced ...

specific Embodiment approach 2

[0035] Embodiment 2: This embodiment differs from Embodiment 1 in that: in step 1, the material of the metal ring is 30CrMnSiA or TC4; the outer diameter of the metal ring is 68-200 mm, the wall thickness is 2-5 mm, and the width is 30-80 mm. Others are the same as in the first embodiment.

specific Embodiment approach 3

[0036] Embodiment 3: The difference between this embodiment and Embodiment 1 or 2 is that in step 1, the metal wire ring is obtained by cross milling, and the total number of wire hanging tables on the surface of the metal wire ring is 42 to 140. The number of wire hanging tables is 14 to 28, a total of 3 to 5 rings; the root of the wire hanging table is prismatic, the side length is 1 to 2 mm, the angle between adjacent sides is 45° to 90°, and the height of the wire hanging table is 0.5 ~1mm, and the upward "draft" slope is 1°~3°. Others are the same as in the first or second embodiment.

[0037] In this embodiment, the number of rings distributed on the surface of the metal wire hanging ring is 3 to 5 rings.

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Abstract

The invention discloses a preparation method for a seal head-free fiber reinforced resin-based composite material combustion chamber shell of a rocket projectile and belongs to the field of preparation methods of polymer-based composite materials. The preparation method aims to solve the technical problem that the combustion chamber shell prepared by an existing method is poor in heat isolating property, low in bursting strength and heavy in weight. The preparation method comprises the following steps of I, milling the outer side of a metal ring to obtain a metal wire hanging ring; II, assembling an assembling part; III, impregnating fiber yarns and then winding the surface of the assembling part; and IV, carrying out heating and curing and natural cooling and then drawing a mandrel to demould. An inside liner which has good properties can meet airtightness and ablation resistance in a combustion chamber grain combustion process. The demand on pressure resistance and rigidity is met bymeans of a wound and formed structural layer. The fiber yarns fall between wire hanging tables of the metal wire hanging ring in accordance with a rule, so that the connecting strength of a compositematerial and a metal and the bursting pressure of the shell are improved. The preparation method is used for preparing the seal head-free fiber reinforced resin-based composite material combustion chamber shell of the rocket projectile.

Description

technical field [0001] The invention relates to the field of methods for preparing polymer-based composite materials. Background technique [0002] The rocket is mainly composed of a warhead, a rocket engine, and a stabilizer. The warhead is a component that exerts combat effectiveness at the end of the trajectory. A rocket motor is a propulsion power device that enables a rocket to fly. At present, rockets mainly use solid rocket motors. The solid rocket motor is composed of a connecting bottom, a combustion chamber, a solid propellant charge, a charge support device, a nozzle, and an ignition device. According to the different types of launch platforms, rockets can be divided into army rockets, navy rockets and air force rockets. [0003] The structural design of solid rocket motor mainly includes combustion chamber, nozzle, charge support device and ignition device. The combustion chamber is one of the important parts of the solid rocket motor. It is composed of the c...

Claims

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Application Information

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IPC IPC(8): B29C70/32B29C70/54B29B11/00B29B11/04B29B15/12B29B15/14B29C33/38B29L31/30
CPCB29B11/00B29B11/04B29B15/125B29B15/14B29C33/3842B29C70/32B29C70/54B29L2031/3097
Inventor 孟玲宇费春东赵亮杨丽萍南田田
Owner HARBIN FRP INST
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