Electronic solid propellant burn-up detector

Claim 1

ELECTRONIC APPARATUS FOR DETERMINING THE INSTANT OF BURN-UP OF A SOLID FUEL IN THE COMBUSTION CHAMBER OF A ROCKET MOTOR COMPRISING: A PRESSURE TRANSDUCER LOCATED WITHIN THE COMBUSTION CHAMBER OF A ROCKET MOTOR, FIRST DIFFERENTIATOR MEANS, SECOND DIFFERENTIATOR MEANS, A TRIGGER CIRCUIT, AMPLIFIER MEANS CONNECTING THE OUTPUT OF SAID TRANSDUCER TO THE INPUT OF SAID FIRST DIFFERENTIATOR, MEANS CONNECTING THE OUTPUT OF SAID FIRST DIFFERENTIATOR TO THE INPUT OF SAID SECOND DIFFERENTIATOR, MEANS CONNECTING THE OUTPUT OF SAID SECOND DIFFERENTIATOR TO A FIRST INPUT OF SAID TRIGGER CIRCUIT, A TRIGGER LEVEL SET CONNECTED TO A SECOND INPUT OF SAID TRIGGER CIRCUIT WHEREBY A PRESSURE CHANGE FROM SAID PRESSURE TRANSDUCER WILL PRODUCE A SECOND DERIVATIVE OF SAID VOLTAGE CHANGE IN THE OUTPUT CIRCUIT OF SAID SECOND DIFFERENTIATOR WHEREBY A VOLTAGE PULSE MAY APPEAR AT THE OUTPUT OF SAID TRIGGER CIRCUIT AT THE TIME OF BURN-UP OF A SOLID FUEL PROPELLANT OF THE ROCKET MOTOR.