The ignition transient in solid propellant rocket motors
Author:
Affiliation:
1. PRINCETON U., GUGGENHEIM LABS. FOR THE AEROSPACE PROPULSION SCIENCES, PRINCETON, N.J.
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1964-126
Reference5 articles.
1. of Ignition Shock Theory to Rocketdyne Research Department; 18 May 1962.
2. 2 df = 2.02x10-6 ft /sec
3. l l l O - BTU/ft secoR % * (value for superheated steam) ), = Z.1810- BTU/Et secoR
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