Accession Number:

AD0769283

Title:

Powder Rocket Feasibility Evaluation

Descriptive Note:

Final technical rept. 21 Feb 1972-1 Mar 1973

Corporate Author:

BELL AEROSYSTEMS CO BUFFALO NY

Personal Author(s):

• Loftus, H. J.
• Marshall, D.
• Montanino, L. N.

Report Date:

1973-04-01

Pagination or Media Count:

88.0

Abstract:

The objective of this evaluation was to investigate the feasibility of the powder rocket concept. A series of rocket combustor tests were conducted at 500 and 900 pound thrust levels using ammonium perchloratealuminum propellants. Eight 500 pound thrust fire tests were conducted to determine the effect of propellant variations on combustion. Particle size affected combustion stability with smoother combustion obtained with reduced particle size. Combustion oscillations of plus or minus five percent of mean chamber pressure at a frequency of 140 Hertz occurred using three micron X-65 Al and twenty micron AP which was the smoothest fire test. However, partial plugging of the AP injector occurred which was attributed to the agglomeration tendency of the finer AP. A test with AP containing 0.2 weight percent silica additive, improved the AP flow character but increased combustion oscillation level to plus or minus thirty-eight percent of mean Pc.

Descriptors:

• *SOLID ROCKET PROPELLANTS
• *POWDERS
• FEASIBILITY STUDIES
• AMMONIUM PERCHLORATE
• COMBUSTION STABILITY
• SPECIFIC IMPULSE
• CAPTIVE TESTS
• COMBUSTION
• PARTICLE SIZE
• ALUMINUM

Subject Categories:

• Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE