Title:
SAFETY SYSTEM OF ROCKET MOTOR OPERATED BY TEMPERATURE
Document Type and Number:
Japanese Patent JPS60252146
Kind Code:
A
Abstract:
@ 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).
Inventors:
SHIRIRU EFU DORAN
Application Number:
JP9239485A
Publication Date:
December 12, 1985
Filing Date:
May 01, 1985
Export Citation:
Assignee:
HUGHES AIRCRAFT CO
International Classes:
B64D45/00; F02C9/38; F02K9/38; F42B15/00; F42B39/20; (IPC1-7): B64D45/00; F02K9/38; F42B15/00
Attorney, Agent or Firm:
Takehiko Suzue
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