Accession Number:

AD0377532

Title:

DEVELOPMENT OF CAST-IN-CASE END-BURNING CHARGES. I. RELEASED LINER TECHNIQUE,

Descriptive Note:

Corporate Author:

ROHM AND HAAS CO HUNTSVILLE ALA REDSTONE RESEARCH LABS

Personal Author(s):

• Anderson,S. E.
• Thompson,B. L.

Report Date:

1966-12-09

Pagination or Media Count:

33.0

Abstract:

A new concept for manufacturing rocket motors containing end-burning propellant charges was demonstrated. Cast-in-case solid grains which were free of stresses and strains from cure shrinkage and environmental temperature changes were made using a released-liner technique. The liner, which was not bonded to the insulated wall of the motor, restricted the peripheral surface of the propellant from burning. Retention of the grain was accomplished by allowing the end of the grain to bond to a flexible stress-relieving material which in turn was bonded to the forward end of the motor. This concept eliminated the need for close dimensional tolerances normally required for cartridge-loaded grains, and could give improvements in volumetric loading fraction, manufacturing simplicity, and cost. Motors containing grains with LD ratios of 7 were made with both plastisol nitrocellulose composite propellant and carboxyl-terminated polybutadiene composite propellant. Successful firings with both propellants were made at -35 F, 77 F and 135 F. The grains were shown to withstand thermal cycling tests at -35 F and 135 F and centrifuge tests at 60-70 gs for 9 minutes at -65 F. Author

Descriptors:

• (*ROCKET PROPELLANT GRAINS
• CASTING)
• DESIGN
• COMBUSTION CHAMBER LINERS
• CAPTIVE TESTS
• SOLID PROPELLANT ROCKET ENGINES
• ROCKET ENGINE CASES
• MANUFACTURING
• PROCESSING (U) COMPOSITE PROPELLANTS
• BURNING RATE
• THERMAL INSULATION
• BONDING
• NOZZLE THROATS
• STRESSES
• COSTS
• PERFORMANCE(ENGINEERING)
• NITROCELLULOSE
• BUTADIENES

Subject Categories:

• Rocket Engines
• Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE