Ramjet propulsion using solid propellant for post-boost acceleration of missiles exhibits several favorable properties, brought about by heterogeneous combustion. A simplified theory for calculating the performance of possible propellants is presented, and they are classified with respect to maximum fuel-specific impulse. The optimal choice of fuel, from a system standpoint, must consider volume constraints, and defines the requirements for motor geometry. (ERA citation 02:040567)
Propellant Selection for Ramjets with Solid Fuel
1976
33 pages
Report
Keine Angabe
Englisch
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