Burning Rate for a Solid Propellant Ramjet Developing Constant Tthrust

Author: Arbo, Paul Edward

Year: 1952

Degree: Engineer's thesis

Advisor: Marble, Frank E.

Committee Member: Unknown, Unknown

Option: Aeronautics

DOI: 10.7907/31B3-3W28

Abstract

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.

Files