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An Instantaneous Measuring Method of Erosive Burning Rate of Solid Rocket Propellant(PDF)

《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

Issue:
1997年02期
Page:
49-52
Research Field:
Publishing date:

Info

Title:
An Instantaneous Measuring Method of Erosive Burning Rate of Solid Rocket Propellant
Author(s):
XiaJing
School of Mechanics,NUST,Nanjing 210094
Keywords:
solid propellant s erosive bur ning sensors measurment methods
PACS:
V512
DOI:
-
Abstract:
An ex perimental test apparatus and procedure for measur ing ero sive burning rates of so lid rocket pr opellant is described in the present paper. A g as gener ator in the test moto r produces a hig h velocity g as flow ing through a t ransit ion sect ion into a rectang ular channel w hich co ntains the test pr opellant sample. The sample is ig nited by cr oss-flow and burns along the normal dir ectio n of the burning sur face. The bur ning rate is direct ly measured by pho to graphing the ablat ing grain w ith CCD through a quart z w indow mo unted on the test sect ion. The elect rical signal t ranslated f rom image o f the f lame is sampled and pr oceeded by a computer, which makes it possible to determinen instantaneous burning rates o f the test propellant as a funct ion of t ime.

References:

1 董师颜. 固体火箭发动机原理. 北京: 北京理工大学出版社, 1996
2 宁新宝. 物理化学生物传感器. 南京: 南京大学出版社, 1991

Memo

Memo:
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Last Update: 2013-03-29