Reduction of depressurization thrust termination jolt

Details Reduction of depressurization thrust termination jolt Reduction of depressurization thrust termination jolt

1975-09-15

1976-12-28

Croyle, Carlton R.

Power plants

Reaction motor

Method of operation

60234, 102 495, 102 498, 220 89A, 220328, 220281, 23926525, F02K 108, F02K 904

Patent

active

039993795

ABSTRACT:
Thrust termination of a solid propellant rocket motor is obtained by connecting the nozzle to the combustion chamber pressure vessel by means of explosive and extrusable bolts. When it is desired to obtain thrust termination, the explosive bolts are blown leaving the nozzle connected to the pressure vessel by the extrusable bolts. The extrusable bolts have sufficient strength to retain the nozzle assembly; however, upon elimination of the strength of the explosive bolts, the nozzle is permitted to separate from the pressure vessel and move to the rear by drawing the extrusable bolts through dies. The bolts deform to absorb the energy of the nozzle and the jolt of forward acceleration which would normally be obtained if the nozzle were ejected, is reduced or eliminated.

REFERENCES:
patent: 1677403 (1928-07-01), Morrison
patent: 3122098 (1964-02-01), Glennan
patent: 3221495 (1965-12-01), Tweet
patent: 3302890 (1967-02-01), Silver
patent: 3613374 (1971-10-01), Ritchey
patent: 3626697 (1971-12-01), Nunn et al.

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