Burn rate modification of solid propellants with bismuth trioxid

Details Burn rate modification of solid propellants with bismuth trioxid Burn rate modification of solid propellants with bismuth trioxid

1992-02-10

1994-12-13

Nelson, Peter A.

Ammunition and explosives

Powder form

Having burning inhibiting means

102272, 149 2, 149 57, 149 85, C06B 4500, C06B 2904

Patent

active

053720709

ABSTRACT:
Propellant formulations are provided which include non-toxic burn rate modifiers. In order to produce a usable propellant formulation, it is necessary to control the burn rate of the propellant. Failure to adequately control the propellant burn rate often results in unacceptable performance of the propellant. For example, during the operation of a rocket motor, or similar device which contains a propellant, the propellant may produce operating pressures which are too high or too low for the intended purpose of the device.
It has often been the practice to add lead to rocket motor propellants in order to modify the burn rate and to maintain the burn rate within acceptable parameters. Lead, however, is known to be toxic and a pollutant. Accordingly, it is desirable to replace the lead in the formulation. It has been found herein that bismuth trioxide is capable of modifying the burn rate of propellants without resorting to lead as a burn rate additive. Accordingly, the use of bismuth trioxide is taught as effective burn rate modifiers in propellants, in order provide non-toxic means for modifying the propellant burn rate.

REFERENCES:
patent: 1631070 (1927-05-01), Snelling
patent: 2938778 (1960-05-01), Linsk
patent: 3755021 (1973-08-01), Sujanski
patent: 3862866 (1975-01-01), Timmerman et al.
patent: 4419153 (1983-12-01), Boberg
patent: 4853052 (1989-08-01), Calsson et al.
patent: 5074938 (1991-12-01), Chi

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