METHOD OF EXPERIMENTAL CONFIRMATION OF LIQUID-PROPELLANT ROCKET ENGINE AMPLITUDE-PHASE CHARACTERISTICS AND LIQUID-PROPELLANT ROCKET ENGINE (VERSIONS) Russian patent published in 2010 - IPC F02K9/46 G05B23/00 

FIELD: engines and pumps.

SUBSTANCE: proposed method is based on measuring engine parametres responses to perturbation and comparing measured responses. In compliance with this invention, perturbation is produced by generating surges of pressure or fuel component flow rate in at least one lines of engine. Note here that said surge causes damped natural oscillations of the system, components and engine on the whole. Transient processes in engine parametres are noted by measurement system, while responses are compared with those of transient processes in perturbation. Pressure surge is generated at oxidiser or fuel pump inlet or outlet. Surge of flow rate is created in the line feeding oxidiser or fuel into gas generator. Surge of flow rate is created in the line feeding gas to turbo pump unit turbine. In compliance with first version, throttling valve can be arranged at oxidiser or fuel pump inlet or outlet with its time of operation smaller that period of oscillation in hydraulic system. In compliance with second version, engine incorporates at least one line to bypass fuel components at gas generator inlet. Said line incorporates throttling valve with its time of operation smaller that period of oscillation in hydraulic system. In compliance with third version, engine incorporates line to bypass gas around turbine of turbo pump unit with throttling valve with its time of operation smaller that period of oscillation in hydraulic system.

EFFECT: higher accuracy and reliability of determination.

7 cl, 3 dwg