Accession Number:

AD0387338

Title:

FEASIBILITY DEMONSTRATION OF A SINGLE-CHAMBER CONTROLLABLE SOLID ROCKET MOTOR

Descriptive Note:

Final rept. 1 Jul1965-1 Aug 1967

Corporate Author:

AEROJET-GENERAL CORP SACRAMENTO CA

Personal Author(s):

• Levinsky, Charles T.
• Kobalter, Gerald F.

Report Date:

1968-01-01

Pagination or Media Count:

404.0

Abstract:

A preliminary design phase, a propellant development phase, a lightweight motor development phase, and a lightweight motor demonstration phase were conducted. In the preliminary design phase, a trade-off study was conducted to size the system and a preliminary lightweight motor design was prepared and analyzed. In the propellant development phase, a family of extinguishable propellants was investigated. In the subscale design and development phase, the basic material selections were test fired in a motor which was designed to simulate the full-scale CSRM. In the heavyweight motor development phase, a full-scale CSR motor was designed and fabricated, three units were processed, and four tests conducted. In the lightweight motor development phase, the propellant was changed and the nozzle design was modified, four tests were conducted. In the demonstration phase, four motors were tested at Arnold Engineering Development Center, Tullahoma, Tennessee.

Descriptors:

• *SOLID PROPELLANT ROCKET ENGINES
• FEASIBILITY STUDIES
• ALUMINUM
• COMBUSTION CHAMBERS
• AMMONIUM COMPOUNDS
• IGNITION
• BURNING RATE
• POTASSIUM COMPOUNDS
• SOLID ROCKET PROPELLANTS
• AMMONIUM PERCHLORATE
• NITROGUANIDINE
• FUEL ADDITIVES
• PERCHLORATES
• COLD FLOW
• SOLID ROCKET PROPELLANT BINDERS
• THRUST TERMINATION SYSTEMS

Subject Categories:

• Solid Propellant Rocket Engines
• Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE