Accession Number : AD0370635

Title :   BALLISTIC SCALE-UP OF NF PROPELLANTS. I. 80 LBM MOTOR DEMONSTRATION FIRING,

Corporate Author : REDSTONE ARSENAL RESEARCH DIV ROHM AND HAAS CO HUNTSVILLE ALA

Personal Author(s) : Anderson,S. E.

Report Date : 17 MAR 1966

Pagination or Media Count : 26

Abstract : Production of an NFPA/TVOPA propellant having a new prepolymer binder system was scaled up from gram to multipound batches in six months. Ballistic scaling data on RH-SE-103cf were obtained in motors ranging in size from 10 grams to 80-lbm during this time. The burning rate was 0.97 in/sec at 1000 psia and the pressure exponent was 0.6. A specific impulse (Isps) of 261.3 lbf-sec/lbm (97% of theoretical) was obtained from the 80-lbm motor firing. The radar attenuation properties of RH-SE-103 (NF) and RH-P-112 (PNC) exhaust plumes were compared by measurements made about 1-ft and 5-ft from the nozzle exit planes. The X-band attenuation at the 1-ft measurement station was about 1.23 db for the high-energy NF propellant compared with 5.84 db for the PNC propellant. In a preliminary study of techniques for evaluating possible toxicity hazards, samples of exhaust gases from the 80-lbm motor were obtained for HF analysis using evacuated stainless-steel bottles. A polyester-based liner material which had been used with previous NF propellants was also satisfactory for the new system. Propellant would not bond well to fully-cured liner, but excellent bonds were obtained when the propellant was cast on partially-cured liner. (Author)

Descriptors :   (*SOLID PROPELLANT ROCKET ENGINES, CAPTIVE TESTS), (*SOLID ROCKET PROPELLANTS, BURNING RATE), SPECIFIC IMPULSE, SOLID ROCKET PROPELLANT BINDERS, AGING(MATERIALS), BONDING, EFFECTIVENESS, CASTING, COMBUSTION CHAMBER LINERS, ROCKET PROPELLANT GRAINS, BALLISTICS, QUALITY CONTROL, PRESSURE, THRUST (U) FLUOROAMINES, ESTERS, ALKENES, RADAR, ATTENUATION, EXHAUST GASES, X BAND, TOXICITY, ACRYLIC RESINS, CROSSLINKING(CHEMISTRY), ALUMINUM, AMMONIUM COMPOUNDS, PERCHLORATES, PROPANOLS

Subject Categories : Solid Propellant Rocket Engines
      Solid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE