Dynamic response testing of transient pressure transducers for liquid propellant rocket combustion chambers

Abstract

An investigation of the dynamic response of transient pressure transducers intended for use in liquid propel lant rocket combustion chambers was undertaken. Shock tube testing included optimization of operating techniques especially the tailored interface and the effects of ground shock and other mounting influences. The Kistler 60IA quartz transducer was evaluated as a monitor for the Princeton Sinusoidal Pressure Generator (SPG) and a number of water-cooled transient transducers were evaluated for comparison with results from the SPG. An investigation was conducted which satisfactorily demonstrated the practical value of the SPG as a primary test device for transient pressure transducer evaluations to 10,000 cps. During evaluations special consideration was given to developing operating techniques and improving SPG chamber design. The results from shock tube and the SPG show close agreement up to 10,000 cps, the present limit of usable SPG range. Transducers were then tested in experimental liquid propellant rocket motors to compare laboratory measured characteristics with actual transducer performance.