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Solid rocket engine shell, solid rocket engine and manufacturing method thereof

A technology for engine shells and solid rockets, which is applied to rocket engine devices, machines/engines, mechanical equipment, etc. It can solve problems such as inability to perform real-time in-situ monitoring and early warning, and solid rocket engine monitoring lag, and achieve enhanced engine state prediction ability, reducing the difficulty of inspection and fault identification, and ensuring safety and stability

Active Publication Date: 2020-10-16
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

[0004] The embodiment of the present application provides a solid rocket motor casing, a solid rocket motor and a manufacturing method thereof, so as to solve the problems in the related art that the internal monitoring of the solid rocket motor lags behind and cannot perform real-time in-situ monitoring and early warning

Method used

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  • Solid rocket engine shell, solid rocket engine and manufacturing method thereof
  • Solid rocket engine shell, solid rocket engine and manufacturing method thereof
  • Solid rocket engine shell, solid rocket engine and manufacturing method thereof

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Embodiment 1

[0057] see figure 1 As shown, Embodiment 1 of the present application provides a solid rocket motor casing, which can solve the problems in the related art that the monitoring of the interior of the solid rocket motor lags behind and that real-time in-situ monitoring and early warning cannot be performed.

[0058] A solid rocket motor housing provided in Example 1 of the present application includes a thermal insulation structure 1, a winding layer 6, a plurality of optical fibers 4 and a plurality of sensors 5, and the thermal insulation structure 1 has a charging space for accommodating propellant grains 2 10, and the thermal insulation structure 1 is provided with an optical path channel 3 extending along the circumferential direction of the thermal insulation structure 1. The optical path channel 3 is the space occupied by the optical fiber 4 itself. After the optical fiber 4 enters the optical path channel 3, the optical path channel 3 is closed. 4 and the thermal insulat...

Embodiment 2

[0065] The basic content of embodiment 2 of the present application is the same as embodiment 1, and difference is:

[0066] see figure 2 As shown, the optical path channel 3 is formed by the end faces of the column section 11 and the rear head section 13 connected to each other, and the embedded end 41 extends along the generatrix direction of the rear head section 13 to be embedded in the optical path channel 3 . The optical fiber 4 penetrates into the heat insulation structure 1 from the junction of the rear head section 13 and the column section 11, and the junction of the rear head section 13 and the column section 11 is not in contact with the high-temperature gas until the engine is near the end of operation, which has a short exposure time , high reliability and long test time range. However, since the manufacturing process of the heat insulating structure 1 is to manufacture the front head section 12 first, it is more practical that the optical path channel 3 is for...

Embodiment 3

[0068] The basic content of embodiment 3 of the present application is the same as embodiment 1, and the difference is:

[0069] see figure 2 As shown, the optical path channel 3 is formed by the end face connecting the column section 11 and the front head section 12, and the end surface connecting the column section 11 and the rear head section 13, and the embedded end 41 extends along the generatrix direction of the front head section 12 To be embedded in the optical path channel 3 formed by the column section 11 and the front head section 12, and the embedded end 41 extends along the generatrix direction of the rear head section 13 to be embedded in the rear head section 13 and the front head section 12 to form within channel 3 of the optical path. The form of embedding the front head section 12 and the rear head section 13 inside the thermal insulation structure 1 can greatly increase the success rate of the optical fiber 4 embedding, and can monitor both sections of the...

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Abstract

The invention relates to a solid rocket engine shell, a solid rocket engine and a manufacturing method thereof. The solid rocket engine shell comprises a winding layer, a heat insulation structure, aplurality of optical fibers and a plurality of sensors; the heat insulation structure is internally provided with a propellant storing space used for containing a propellant grain and is provided witha light path channel extending in the circumferential direction of the heat insulation structure; and the winding layer is wound around the outside of the heat insulation structure. The multiple optical fibers are arranged in the outer circumferential direction of the heat insulation structure at intervals, the optical fibers and the heat insulation structure are bonded together, the optical fibers comprises leading-out ends and built-in ends, the leading-out ends extend out of the heat insulation structure, the built-in ends extend into and are embedded into the light path channel in the busdirection of the heat insulation structure and extend into the propellant storing space, and the built-in ends of the optical fibers are connected with the sensors; and the sensors are used for monitoring the propellant grain (a propellant storing interface or propellant grain interior). The solid rocket engine comprises the solid rocket engine shell and the propellant grain filled in the propellant storing space.

Description

technical field [0001] The present application relates to the technical field of solid rocket motors, in particular to a solid rocket motor casing, a solid rocket motor and a manufacturing method thereof. Background technique [0002] At present, rocket engines are commonly used power devices for various missile weapons and aerospace vehicles. Due to the relatively poor process stability of composite materials, engine propellants are prone to defects such as inclusions, pores, delamination, and interface debonding during casting. . Moreover, due to temperature, vibration, collision and other reasons, these defects have a tendency to expand continuously during the storage, transportation and use of the engine. If they are not monitored and controlled, it may cause the solid rocket motor to produce "super" combustion surface. And other problems, which pose a great threat to the engine, significantly affect the reliability and safety of solid rocket motors, serious and may eve...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/34F02K9/10F02K9/96G02B6/46B29C69/02
CPCB29C69/02B29L2031/3097F02K9/10F02K9/34F02K9/96G02B6/46
Inventor 武丹陈文杰周睿司学龙钟志文张志强
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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