USA As Represented by Secretary of the Navy

United States of America As Represented by the Secretary of the Air Force

Atlantic Research Corporation

Thomas F Davidson

Guy Bruce Spear

Edward G Skolnik

Evester Sullivan

Gregory S Rogowski

Timothy Ludlow

William L Pennington

Timothy L Ludlow

An insulation material for a rocket motor is described, which is composed of a glass fabric, a resin binder, and a fire retardant. The resin binder preferably is composed of a phenolic resin and a Buna-N rubber, and the fire retardant is preferably alumina trihydrate. A method of manufacturing the insulation material is also described.

Non-Asbestos insulation for rocket motor casing

A solid propellant to inhibitor bonding system for use in replaceable prolant grain assemblies is used with an inhibitor sleeve that has one end attached to an end closure having interior insulation, made of the same rubber insulation material as the inhibitor, and forming a cylindrical cavity for receiving a poured propellant mix. The bonding system is employed prior to pouring the propellant mix. This bonding system involves cleaning the interior surface of the cavity with freon solvent and brush applying a barrier coat, comprising an epoxy resin with amine curing agents, to the interior surface of the cleaned inhibitor. The barrier coat is then cured and a liner is then brush coated onto the cured interior surface of the barrier coat. The liner is then cured and the propellant is then cast into the cavity formed by the lined inhibitor sleeve and insulated closure. It is important the the polymer and curing agent of the propellant and liner be the same to assure optimum compatibility and effective adhesive bonding. This is accomplished by providing common chemical constituents even though they are formed by different processes and have other different chemical constituents.

Propellant-to-inhibitor bonding system

A cost effective, efficient thermal insulation composition that will have ng shelf life and withstand severe high temperature and pressure conditions in high temperature solid propellant gas generators can be formed of an ethylene propylene, diene monomer (EPDM)/neoprene rubber binders containing silica powder filler and aramid fibers. The specific chemical constituents include EPDM elastomer, 2 Chlorobutadiene 1,3 elastomer, Silica hydrate, Polymerized Trimethyl Dihydroquinoline, Alkylated Diphenylamines and Diphenyl-p-Phenylendiamene, 40% a,a' Bis (Tert-Butylperoxy), Diisopropylbenzene, Napthenic Process Oil, Synthetic Polyterpene Resin, Aramid Fiber (0.25 inch), and Zinc Oxide, Technical.

Thermal insulation chemical composition and method of manufacture

An improved composition for an insulating liner, or insuliner, for a solid propellant rocket motor, which composition comprises a vulcanizable elastomeric composition comprising a vulcanizable elastomer and about 5 to 25 pph (parts by weight per 100 parts by weight of elastomer) of vulcanizing agents for the elastomer, about 10 to 20 pph of aramid polymer fibers, about 5 to 20 pph of a powder filler selected from the group consisting of silica, iron oxide, titanium dioxide, carbon, milled glass and ceramic clays, and about 10 to 25 pph of a bond promoter selected from the group consisting of treated cellulosic fiber and a multifunctional aromatic epoxy resin.

Growing community of inventors

Manassas, VA, United States of America

Thomas F Davidson