METHOD FOR DETERMINATION OF RADIAL PRESSURE DIFFERENTIAL IN DUCT CHARGE OF SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2007 - IPC F02K9/96 

FIELD: rocketry, applicable for unbiased measurement of static pressures of gas flow in the duct of charges of the solid-propellant rocket engine.

SUBSTANCE: the method for determination of radial pressure differential in the duct charge of the solid-propellant engine by measurement of static pressures at the surface of the charge duct and in the clearance between the charge and the combustion chamber of the rocket engine is accomplished as follows. Pressure transducers are installed in the adapters located in the measuring sections of the combustion chamber, and a firing rig test of the rocket engine is performed. The pressure near the surface of the charge duct is measured through a steel intake tube having an extension piece of polymeric material. The extension piece has the shape of a truncated cone with a thermodecomposition temperature within 200 to 240C and a height equal to the thickness of the charge arch in the measuring section. The extension piece is pasted-in in the charge arch in the radial direction. One end of the intake tube is mounted in the extension piece to a depth of 0.1 to 0.5 of the extension piece height. The opposite end of the intake tube is jointed to the adapter of the pressure transducer for reciprocating motion in it. The radial pressure differential is estimated by the difference of pressures measured in the clearance and duct.

EFFECT: enhanced precision of pressure measurement in the measuring section, prevented distortion of the gas flow parameters at measurement.

3 cl, 1 dwg