Dual-pulse solid rocket engine soft interlayer ablation test device

Abstract

The invention discloses a dual-pulse solid rocket engine soft interlayer ablation test device comprising an end combustion powder charging cavity, a test piece ablation cavity, a spray pipe cavity anda center cube connector (5). The end combustion powder charging cavity and the test piece ablation cavity are symmetrically installed at the two ends of a through hole of the center cube connector (5). The spray pipe cavity is connected with the third hole of the center cube connector (5). An end combustion powder charging cavity blocking cap (1), an end combustion powder charging cavity shell (2), the center cube connector (5), a spray pipe cavity shell (6), a spray pipe cavity rear section (9), a test piece ablation cavity shell (11) and a test piece ablation cavity blocking cap (14) of thetest device are all made of high-strength 45 steel material. An end combustion powder charging cavity liner (3), a spray pipe cavity liner (7), a spray pipe cavity rear section liner (10) and a testpiece ablation cavity liner (12) are all made of ethylene propylene terpolymer material. A spray pipe cavity throat liner (8) is made of graphite. Through the dual-pulse solid rocket engine soft interlayer ablation test device, the problems that the work process of a dual-pulse engine ii pulse soft interlayer is difficult to simulate and observe are solved.

Description

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AI Technical Summary

Benefits of technology

In this new testing apparatus that simulates two pulses' operation during flight, it allows us to accurately detect any issues or changes affecting the performance of certain parts of the vehicle. It also includes features like monitoring the flow fields around the bouncing zone behind the hard cover layer, allowing researchers to analyze how well these components are performing properly before they hit them again. Additionally, there may exist other technical means such as controllably varying the size of particles used by each part of the machine, making sure their impacts negligible when hitting another component next. Overall, this technology improves safety measures while reducing costs associated with maintenance operations.

Problems solved by technology

This patented technical problem addressed by this patents relates to improving the control over conventional solid rocker engines without sacrificing reliance or flexibility during flight operations due to its unique features such as repeated starting up after each firing cycle, high efficiency at low altitudes (up to 2000 meters) while also having excellent maneuverability under extreme conditions like impact from space debris.

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