METHOD FOR DETERMINING COMBUSTION SPEED OF SOLID ROCKET PROPELLANT Russian patent published in 2014 - IPC F02K9/96 

FIELD: power industry.

SUBSTANCE: when determining combustion speed of solid rocket propellant, installation and combustion of a rod-like specimen with a priming wire is performed in a combustion chamber having a pressure recording system. Prior to installation a non-armoured specimen is submerged into an armour shell containing non-hardened armour composition and armour composition is hardened. Then, in the plane of axial section of the armoured specimen there made on its edges are notches with tops perpendicular to the specimen axis. A piece of a fire-resistant cord is installed into the notch on the side of the armoured edge. The notch cavity with the installed piece of the fire-resistant cord is isolated. The priming wire is installed into the notch on the side of the open edge; ends of the wire are connected to a pressure seal, and the specimen together with the pressure seal is mounted in the combustion chamber. Initial pressure is supplied to the combustion chamber from an external source; the specimen is lit up and pressure is maintained in the combustion chamber at the level of the specified pressure by releasing excess pressure till pressure surge appears in the combustion chamber. Pressure is released and combustion speed of solid rocket propellant is determined as per the ratios protected by this invention.

EFFECT: invention allows simplifying preparation of a solid rocket propellant specimen for tests and improving determination accuracy of its combustion speed.

2 cl, 4 dwg