Arbo, Paul Edward (1952) Burning rate for a solid propellant ramjet developing constant thrust. Engineer's thesis, California Institute of Technology. http://resolver.caltech.edu/CaltechETD:etd-03232009-150232
An analysis of a solid propellant ramjet which carries the propellant in the combustion chamber was made, and a procedure outlined for calculating the required burning rate of such a ramjet which develops constant thrust. The two factors which influenced this development were:
1) The solid propellant ramjet’s combustion chamber varies in size with time due to burning of the fuel. 2) The solid propellant ramjet develops constant thrust.
These factors were coordinated with the analysis of the internal flow system of the ramjet, and an expression for the required burning rate was derived.
|Item Type:||Thesis (Engineer's thesis)|
|Degree Grantor:||California Institute of Technology|
|Division:||Engineering and Applied Science|
|Thesis Availability:||Public (worldwide access)|
|Defense Date:||1 January 1952|
|Default Usage Policy:||No commercial reproduction, distribution, display or performance rights in this work are provided.|
|Deposited By:||Imported from ETD-db|
|Deposited On:||24 Mar 2009|
|Last Modified:||26 Dec 2012 02:35|
- Final Version
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