A Caltech Library Service

Burning Rate for a Solid Propellant Ramjet Developing Constant Tthrust


Arbo, Paul Edward (1952) Burning Rate for a Solid Propellant Ramjet Developing Constant Tthrust. Engineer's thesis, California Institute of Technology. doi:10.7907/31B3-3W28.


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)
Subject Keywords:Aeronautical Engineering
Degree Grantor:California Institute of Technology
Division:Engineering and Applied Science
Major Option:Aeronautics
Thesis Availability:Public (worldwide access)
Research Advisor(s):
  • Marble, Frank E.
Thesis Committee:
  • Unknown, Unknown
Defense Date:1 January 1952
Record Number:CaltechETD:etd-03232009-150232
Persistent URL:
Default Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:1080
Deposited By: Imported from ETD-db
Deposited On:24 Mar 2009
Last Modified:10 May 2023 22:22

Thesis Files

PDF (Arbo_pe_1952.pdf) - Final Version
See Usage Policy.


Repository Staff Only: item control page