RT Journal Article ID 3a0d77502adc0981 A1 Hewson , Jacquie A1 Le Neal, Robert T1 ENHANCEMENT OF COMPOSITE PROPELLANT IGNITION CHARACTERISTICS BY SURFACE ABRASION JF International Journal of Energetic Materials and Chemical Propulsion JO IJEMCP YR 2013 FD 2013-09-26 VO 12 IS 4 SP 335 OP 346 K1 propellant K1 ignition K1 rocket AB During curing of composite solid rocket motor propellants, the propellant polymer tends to accumulate as a thin film adjacent to the mandrel used to form the internal bore of the propellant grain. This binder-rich layer coats the ammonium perchlorate crystals on the propellant surface and may inhibit flame propagation during rocket motor ignition. Poor flame propagation during ignition can affect both ignition performance and the reliability characteristics. Abrasion of the solid propellant bore surfaces to remove the binder-rich layer and expose the ammonium perchlorate oxidizer is a common procedure used to enhance rocket motor ignition. Abrasion of the propellant bore was evaluated as a means to enhance the ignition performance and reliability characteristics of Bristol 2.75-in. CRV7 rocket motors. Techniques were developed using wire brushes to scrub the surface of the propellant bore. Automated production processes were developed to provide uniform abrasion of the propellant surface, resulting in consistent enhancement of the rocket motor ignition characteristics. This paper describes the development of the CRV7 propellant bore abrasion process, and describes the results of the testing performed to quantify the effect of propellant abrasion on the rocket motor ignition characteristics. PB Begell House LK https://www.dl.begellhouse.com/journals/17bbb47e377ce023,666ac2715cb41467,3a0d77502adc0981.html