|Table of Contents|

Control system for liquid rocket engine heat-vacuum test based on PLC and WinCC(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2015年03期
Page:
93-97
Research Field:
测控与试验
Publishing date:

Info

Title:
Control system for liquid rocket engine heat-vacuum test based on PLC and WinCC
Author(s):
SHEN Chuan-bing;  SU Hang;  ZHU Zi-yong
Beijing Aerospace Testing Technique Institute, Beijing 100074, China
Keywords:
heat-vacuum test;  PLC;  rocket engine
PACS:
V434-34
DOI:
-
Abstract:
To validate rationality and reliability of heat protection and heat management measure for liquid rocket engine, a platform of thermal vacuum test is needed to be constructed to simulate the entire process of the flight program, and examine adaptability of rocket engine and each subassembly under the condition of thermal vacuum. The requirements, technological approaches and debugging process that the control system of heat-vacuum test platform simulates vacuum and heat environments are introduced. The PLC and WinCC configuration software are adopted in the control system to adjust the output power of the simulation device to meet the needed heat flow condition. The vacuum pump is used to make the environment pressure of the engine close to vacuum, and each index accord with the test request.

References:

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