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Ultra-large solid rocket engine sectional composite shell and manufacture method thereof

A technology of solid rockets and composite materials, which is applied to the field of segmented composite material shells of super-large solid rocket motors and its manufacturing field, can solve the problems of high cost, high propellant price, and propellant cannot be poured at one time, and reduces the The effect of waste, simple and efficient assembly, and transportation cost saving

Active Publication Date: 2019-04-26
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] 1) Due to the safety requirements of propellant production and the capacity limitation of pouring equipment, propellants of more than 100 tons generally cannot be poured at one time;
[0004] 2) The propellant is expensive. After the propellant is poured as a whole, if it is scrapped due to quality problems, the cost will be too high

Method used

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  • Ultra-large solid rocket engine sectional composite shell and manufacture method thereof
  • Ultra-large solid rocket engine sectional composite shell and manufacture method thereof
  • Ultra-large solid rocket engine sectional composite shell and manufacture method thereof

Examples

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Effect test

Embodiment 1

[0056] see Figure 1-2As shown, Embodiment 1 of the present invention provides a segmented composite shell of an ultra-large solid rocket motor, which includes a shell body 1, and openings 10 are provided at both ends of the shell body 1, and the shell body 1 is composed of a plurality of The prefabricated parts are assembled, and the multiple prefabricated parts include the middle section 11 and the front head section 12 and the rear head section 13 connected to the two ends of the middle section 11 respectively, the middle section 11, the front head section 12 and the rear head section 13 It can be manufactured at the launch site or manufactured in sections at the factory and then transported to the launch site. Two openings 10 are respectively set on the front head section 12 and the rear head section 13. The shell body 1 is a cavity connected at both ends, which is convenient for manufacturing. During the solid rocket motor, the propellant is poured in the cavity; the end ...

Embodiment 2

[0061] Embodiment 2 of the present invention provides a method for manufacturing a solid rocket motor using a super-large solid rocket motor segmented composite shell, see Figure 1-2 As shown, the super-large solid rocket motor segmented composite material casing provided includes a casing body 1, and openings 10 are opened at both ends of the casing body 1, and the casing body 1 is assembled from a plurality of prefabricated parts. A prefabricated part comprises a middle section 11 and a front head section 12 and a rear head section 13 which are respectively connected to the two ends of the middle section 11. The middle section 11, the front head section 12 and the back head section 13 can be manufactured at the launch site or in a factory. Manufactured in sections and then transported to the launch site, two openings 10 are respectively arranged in the front head section 12 and the rear head section 13, and the inside of the shell body 1 is a cavity connected at both ends, w...

Embodiment 3

[0077] A method for manufacturing a solid rocket motor using a segmented composite shell of an ultra-large solid rocket motor comprises the following steps:

[0078] S1. Wrap the outer surface of the front head section 12 along the hoop direction for the first time to form the first winding layer 16, and wrap the middle section 11 on its outer surface along the hoop direction for the first time to form the first winding layer. 16. The rear head section 13 is wrapped around its outer surface for the first time in the circumferential direction to form the first winding layer 16;

[0079] S2. After the first wrapping layer 16 of the front head section 12, the middle section 11 and the rear head section 13 is solidified, pour propellant into the front head section 12, the middle section 11 and the back head section 13 respectively, After the propellant is solidified, the grain column in the front head section 12 has a through cavity extending along its axial direction, the grain c...

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Abstract

The invention discloses an ultra-large solid rocket engine sectional composite shell. The ultra-large solid rocket engine sectional composite shell is characterized in that the ultra-large solid rocket engine sectional composite shell comprises a shell body, the two ends of the shell body are each provided with an opening, the shell body is formed by assembling multiple prefabricated members, themultiple prefabricated members comprise a middle section and a front sealing head section and a back sealing head section which are connected to the two ends of the middle section separately, and thetwo openings are formed in the front sealing head section and the back sealing head section separately; and the end faces of the middle section and the front sealing head section which are connected form a mutual cooperative tongue-and-groove structure, and the end faces of the middle section and the back sealing head section which are connected form a mutual cooperative tongue-and-groove structure.

Description

technical field [0001] The invention relates to the technical field of manufacturing solid rocket motors, in particular to a segmented composite shell of a super-large solid rocket motor and a manufacturing method thereof. Background technique [0002] Super-large solid rocket motor is the auxiliary propulsion or main propulsion device of a large launch vehicle. The total propellant weight of super-large solid rocket motors often exceeds 100 tons, which leads to the following problems in the manufacture and molding of super-large solid rocket motors: [0003] 1) Due to the safety requirements of propellant production and the capacity limitation of pouring equipment, propellants of more than 100 tons generally cannot be poured at one time; [0004] 2) The propellant is expensive. After the propellant is poured as a whole, if it is scrapped due to quality problems, the cost will be too high. [0005] At present, ultra-large solid rocket motors generally use metal shells for ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/34F02K9/24
CPCF02K9/24F02K9/34
Inventor 郑振兴张志强陈文杰周睿柳青司学龙
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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