초록 ▼

A thermally actuated rocket motor safety system has a fire temperature pyrotechnic sensor which ignites a gas generator (30) which drives piston (38) to the left. Firing pin (40) strikes the primer in transfer booster assembly (42). The transfer booster assembly transmits explosive energy through wi

A thermally actuated rocket motor safety system has a fire temperature pyrotechnic sensor which ignites a gas generator (30) which drives piston (38) to the left. Firing pin (40) strikes the primer in transfer booster assembly (42). The transfer booster assembly transmits explosive energy through window (54) in now open block ring (50) to initiate charge (62) which lies adjacent the rocket motor case. This stresses the rocket motor case by producing a stress raising notch in the case wall. Subsequent grain burning opens the case to vent the rocket motor pressure. Inertia mass (70) slides to the right upon acceleration due to normal rocket motor firing and locks in the rightmost position by means of latch (82). In the locked position, inertia mass (70) prevents leftward motion of the firing pin (40).

대표청구항 ▼

A thermally actuated rocket motor safety system comprising: a thermal sensor for securing adjacent to a rocket motor and for sensing when temperature thereat reaches a temperature over a time indicating the presence of a fire; a control module, said control module being connected to receive a signal

A thermally actuated rocket motor safety system comprising: a thermal sensor for securing adjacent to a rocket motor and for sensing when temperature thereat reaches a temperature over a time indicating the presence of a fire; a control module, said control module being connected to receive a signal from said temperature sensor; means for cutting a rocket motor case for positioning adjacent to the rocket motor case, said means for cutting being connected to said control module to be actuated when said temperature sensor senses the selected temperature and time of heating; and acceleration sensing means within said control module for sensing acceleration resulting from normal operation of the rocket motor, said acceleration sensing means permitting said temperature sensor to actuate said cutting means only before sensing normal rocket motor acceleration and preventing said temperature sensor from actuating said rocket motor cutting means after normal acceleration.