The United States of America as represented by the Secretary of the Army (Washington DC 06)
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초록▼
A tetrabromo compound, e.g., tetrabromophthalic anhydride (TBPA) and tetrabromophthalimide (TBPI), their salts and derivatives, when employed as additives to the inert components when these inert components are being compounded or as crosslinking agents for these inert components, impart fire-retard
A tetrabromo compound, e.g., tetrabromophthalic anhydride (TBPA) and tetrabromophthalimide (TBPI), their salts and derivatives, when employed as additives to the inert components when these inert components are being compounded or as crosslinking agents for these inert components, impart fire-retardancy characteristics to these inert components (liner, insulation, slivers, etc.) which undergo afterburning (combustion of the gases which are produced by the pyrolysis of the inert components with the air ingested into the rocket motor due to the free convective circulation after motor burnout).
대표청구항▼
The combination comprised of a tetrabromo compound selected from tetrabromophthalic anhydride, tetrabromophthalimide, di(2-ethylhexyl) tetrabromophthalate, N-2-hydroxyethyl-tetrabromophthalimide, diammonium tetrabromophthalate, potassium tetrabromophthalimide, an epoxide of tetrabromophthalic anhydr
The combination comprised of a tetrabromo compound selected from tetrabromophthalic anhydride, tetrabromophthalimide, di(2-ethylhexyl) tetrabromophthalate, N-2-hydroxyethyl-tetrabromophthalimide, diammonium tetrabromophthalate, potassium tetrabromophthalimide, an epoxide of tetrabromophthalic anhydride, and an epoxide of tetrabromophthalimide, with a binder and a curing agent for said binder, said combination being the ingredients for use as an inert rocket motor component of a solid-Propelled rocket motor, and being further identified as said inert rocket motor component which serves as either a liner composition for a composite propellant rocket motor or a crosslinked nitrocellulose propellant rocket motor, said liner composition serves to bond the motor wall or wall insulation to the solid propellant grain of said solid-propelled rocket motor, or as an insulation or thermal barrier, said selected compound when in said combination being effective in preventing afterburning of said inert rocket motor component, said liner composition for said composite propellant rocket motor comprised of about 80-85 parts by weight of hydroxy-terminated polybutadiene prepolymer binder with a diisocyanate curing agent, of about 1-4 parts by weight of carbon black additive, of about 4-10 parts by weight of inert fillers, and a curative of about 10 parts by weight of said selected tetrabromo compound; and said liner composition for said crosslinked nitrocellulose propellant rocket motor comprised in parts by weight of a binder of about 49 parts cellulose acetate, of about 31 parts triphenyl phosphate, of about 615 parts acetone, of about 484 parts of an activator 2-methoxy ethanol acetate, of about 2- 4 parts of a diisocyanate curing agent, and of about 19 parts of said selected tetrabromo compound.
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이 특허를 인용한 특허 (3)
Caimi, Luigi, Cable with fire-resistant, moisture-resistant coating.
Nelson Ronald W. ; Lovett Merylin B. ; Poulter Larry W. ; Bonderson Elizabeth K., Erosion resistant-low signature liner for solid propellant rocket motors.
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