Combustion Instability Study of Solid Propellants.
Abstract
The rotating valve method of measuring the combustion response of solid propellants to small amplitude pressure oscillations were evaluated. The method is based on producing pressure oscillations in a small rocket motor by varying the area of a secondary exhaust nozzle in a periodic manner. This is accomplished by using a rotating value as the secondary orifice. The valve apparatus operates concurrently with a primary nozzle which controls the steady-state pressure. The frequency of the oscillations is determined by the rotational speed of the valve. A theoretical analysis was conducted to relate the combustion response function to measurable ballistic properties of the combustion chamber. (Modified author abstract)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1973
- Accession Number
- AD0762841
Entities
People
- James E. Erickson
- Robert S. Brown
- Wayne R. Babcock