Accession Number : ADA575639


Title :   High-Pressure Burning Rate Studies of Solid Rocket Propellants


Descriptive Note : Journal article


Corporate Author : NAVAL AIR WARFARE CENTER WEAPONS DIV CHINA LAKE CA


Personal Author(s) : Atwood, A I ; Ford, K P ; Wheeler, C J


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a575639.pdf


Report Date : Jan 2013


Pagination or Media Count : 13


Abstract : Increased rocket motor performance is a major driver in the development of solid rocket propellant formulations for chemical propulsion systems. The use of increased operating pressure is an option to improve performance potentially without the cost of reformulation. A technique has been developed to obtain burning rate data across a range of pressures from ambient to 345 MPa. The technique combines the use of a low loading density combustion bomb with a high loading density closed bomb technique. A series of nine ammonium perchlorate (AP) based propellants were used to demonstrate the use of the technique, and the results were compared to the neat AP burning rate barrier. The effect of plasticizer, oxidizer particle size, catalyst, and binder type were investigated.


Descriptors :   *SOLID ROCKET PROPELLANTS , AMMONIUM PERCHLORATE , BURNING RATE , HIGH PRESSURE


Subject Categories : Solid Rocket Propellants


Distribution Statement : APPROVED FOR PUBLIC RELEASE