Cookies ussage consent
Our site saves small pieces of text information (cookies) on your device in order to deliver better content and for statistical purposes. You can disable the usage of cookies by changing the settings of your browser. By browsing our site without changing the browser settings you grant us permission to store that information on your device.I agree, do not show this message again.
ZHANG QIUYAN1, SONG QIANG1
- Electric Power Research Institute of Guizhou Power Grid Co., Ltd
In this paper, the effects of heat loss on the micro motor performance were investigated, and the propellant formulation was screened to meet the requirements of micro motor. For a designed binder, with the increase of nitrocellulose content, the thermal decomposition performance of LS/NC was the best, the thermal decomposition performance of AP/NC was the worst, and 5:5 LS/NC was suitable as a micro solid rocket propellant formulation. Further calculations demonstrated that the highest temperature appeared at the boundary of the combustion chamber, where the thermal stress and deformation were the maximum. The heat loss had great effects on micro-thruster performance, and the thrust of micro-thruster decreased by 21.7%, and specific impulse decreased by 11.8%. The maximum equivalent thermal stress and thermal deformation of single motor wall were 134.2Mp and 305.9nm respectively. The maximum thermal deformation was small and had little effect on the thermal stability, whereas the thermal stress was the main reason for the stability destruction..
Submitted at: May 25, 2015
Accepted at: June 9, 2016
ZHANG QIUYAN, SONG QIANG, Decomposition and heat distributions of a designed propellant formulation, Journal of Optoelectronics and Advanced Materials Vol. 18, Iss. 5-6, pp. 546-556 (2016)
- Download Fulltext
- Downloads: 74 (from 48 distinct Internet Addresses ).