ADJUSTABLE DETONATION CHAMBER OF PULSEJET ENGINE Russian patent published in 1997 - IPC

FIELD: pulsejet engines with resonance combustion chambers. SUBSTANCE: detonation chamber has housing, resonator and detonation tubes. Mixture flowing from gas generator through circular slit enters resonator chamber forming flat circular jet which is used as lock for device. At moment of complete filling of resonator chamber, signal for delivery of detonation pulses is fed only to one pair of detonation tubes. To increase modulus of thrust vector, detonation pulse repetition frequency in resonator shall be changed. To this end, command is fed from thrust vector control system to other pairs of detonation tubes at interval between operation of starting pair of detonation tubes and preparation of them for delivery of next detonation pulses. Maximum magnitude of thrust vector modulus is obtained at subsequent operation of all pairs of detonation tubes and minimum magnitude is obtained at operation of one pair only. EFFECT: possibility of change of thrust vector modulus due to introduction of additional pairs of detonation tubes and delivery of signals from control system in definite sequence. 1 dwg