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Inter-stage seal structure device of double-pulse solid rocket engine

A solid rocket and interstage sealing technology, which is applied to rocket engine devices, machines/engines, jet propulsion devices, etc., can solve problems such as high cost, engine scratches, and poor workmanship of ceramic partitions, so as to achieve simple structure and avoid blockage open effect

Active Publication Date: 2018-03-09
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

), the device can achieve interstage separation and sealing, but the ceramic partition is poor in manufacturability and high in cost, and the ceramic fragments generated after breaking open may cause scratches to the downstream part of the engine and affect the performance of the engine

Method used

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  • Inter-stage seal structure device of double-pulse solid rocket engine
  • Inter-stage seal structure device of double-pulse solid rocket engine
  • Inter-stage seal structure device of double-pulse solid rocket engine

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Embodiment 1

[0025] A double-pulse solid rocket motor interstage sealing structure device of the present invention comprises: a metal blocking plate 2 , a non-metallic blocking plate 3 , a blocking plate diaphragm 4 , diaphragm bolts 5 , and an O-shaped sealing ring 6 .

[0026] Connection relationship: the metal blocking plate 2 has 4 stepped through holes uniformly distributed in the circumferential direction, the non-metallic blocking plate 3 has a cylindrical step structure, and the four non-metallic blocking plates 3 and the 4 stepped through holes on the metal blocking plate 2 are connected. Gap fit, the gap is coated with sealant for sealing, and the step structure is used to realize the axial limit and fixation; the blocking plate diaphragm 4 is a very thin (0.3mm) circular cake-shaped structure, and 4 semicircles are evenly distributed in the circumferential direction near the outermost ring Groove, the end face of the large hole of the metal blocking plate 2 is uniformly distribut...

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Abstract

The invention relates to an inter-stage sealing structure device of a double-pulse solid rocket engine, and belongs to the field of solid rocket engines. The device mainly comprises a combustion chamber casing, a metal blocking plate, non-metal plugs, a blocking plate membrane, membrane bolts and an O-shaped sealing ring. The non-metal plugs, the metal blocking plate, the blocking plate membrane and the membrane bolts are reasonably combined and then fixed in a combustion chamber of the solid rocket engine to separate combustion chambers of the solid rocket engine. According to the device, thetwo combustion chambers of the double-chamber dual-thrust solid rocket engine can be separated by use of the inter-stage sealing structure consisting of the metal blocking plate and the non-metal plugs, and the purposes of forward sealing and blocking and reverse circulation of gas flow in the two combustion chambers are achieved by the structural specialty of the plugs. The device is simple in structure, and provides a safe and reliable inter-stage sealing structure to guarantee the good working characteristics of the double-pulse solid rocket engine.

Description

technical field [0001] The invention relates to a double-pulse solid rocket motor interstage sealing structure device, which belongs to the field of solid rocket motors. Background technique [0002] In order to realize the energy controllability of solid rocket motors and improve the full utilization of energy, it is necessary to carry out multi-pulse design for solid rocket motors. For a double-pulse solid rocket motor, the propellant required for two pulses is located in two independent combustion chambers. The general structure is: the two combustion chambers are separated one after the other, and one pulse is connected to the nozzle. When working, the first pulse is ignited first, and the second pulse is not affected in the project that requires the first pulse to work; after the first pulse is over, the second pulse is ignited, and the gas of the second pulse passes through the first pulse combustion chamber from the nozzle discharge. [0003] In order to realize the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/34
CPCF02K9/343
Inventor 梅开李军伟张智慧王国兴刘玉群王宁飞
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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