IGNITION DEVICE OF SAMPLE OF SOLID ROCKET PROPELLANT, AND IGNITION METHOD BY USING SUCH DEVICE Russian patent published in 2011 - IPC F02K9/95 F02K9/96 

FIELD: engines and pumps.

SUBSTANCE: ignition device of sample of solid rocket propellant includes housing in which there arranged is charge of priming composition, as well as flow holes. The latter are located in waveguide bushing. Housing and charge of priming composition is attached on the outside to the bushing by pressure nut and located on the outside around flow holes beyond high-temperature zone of measuring path of burning velocity of primary charge in bushing. Inside priming composition there located is heated metal wire of electric igniter. Ignition method of sample of solid rocket propellant by using the above device involves response of charge of priming composition. By means of heated metal wire of electric igniter, which is located inside charge of priming composition there performed is simultaneous ignition of the whole charge of priming composition in the area of flow holes. Then, combustion products of priming composition are supplied through flow holes to ignited surface of sample and ignition of the sample surface is performed. During the sample ignition there formed is stable zone in the area of ignited surface.

EFFECT: improving measurement accuracy of burning speed of solid rocket propellant sample.

3 cl, 4 dwg