Abstract: A slurry casting process is described capable of producing crosslinked double base propellant having improved burning rates and high specific impulse. Such propellants can be formulated to be smokeless. Improved burning rates are achieved by incorporating into a slurry of double base composition, casting powder granules containing 20% to 75% by weight of small particle ammonium perchlorate. The casting powder granules substantially retain their indentity in the cured propellant matrix. The casting powder granules have a high burning rate and are uniformly distributed throughout the propellant. The granules are responsible for increasing the burning rate of the entire crosslinked double base propellant composition of the invention.

Abstract: Composite rocket propellants, in which the base component is a functionally terminated rubber, and case-bonded rocket motors containing same, are provided, wherein cross-link density at, and adjacent at least a portion of the initial propellant burning surface is lower than that throughout the remainder of the propellant to provide greater strain capability at the initial burning surface together with greater propellant strength for higher mass ratio and improved case bonding than possible utilizing a single "compromise" propellant cross-link density of the prior art.

Abstract: The invention is based on the discovery that when at least a part of the initial burning surface of an epoxy cured carboxy terminated rubber type composite propellant is coated with a propellant antioxidant material, an increase in resistance to oxidative hardening and an increase in strain capability is imparted to said surface. The invention provides (1) such a composite propellant coated at an initial burning surface with a propellant antioxidant in an amount sufficient to impart those unexpected improvements, (2) method involving coating the burning surface with the requisite amount of the propellant antioxidant material, and (3) a propellant rocket motor containing the above said propellant. When only a portion of the surface is subject to high strain, e.g. in slot areas, it is sufficient that only that portion of the burning surface be coated.

Abstract: A typical rocket motor includes a motor casing containing a cast propellant onded to the casing and provided with a port through which combustion gases are delivered to the motor nozzle. During storage and operation, mechanical stresses in the propellant may produce tears resulting in motor malfunctions. Tear strength can be increased by reactively forming on selected port surface areas a thin-film cross-linked polymeric gel coating formed essentially of a highly functional polyglycol adipate and a polyfunctional isocyanate. Cross-linking with the propellant can be achieved by controlling the hydroxyl to isocyanate ratios of the coating and the propellant. The coating is particularly useful on XLDB (cross-linked, composite-modified double base) and on CMDB (composite-modified double-base) propellants.

Abstract: An energetic binder composition of a carboxy polymer, such as an acrylic ymer, mixed with nitrocellulose and cross-linked with a multifunctional curing agent. A composite type propellant in which the energetic binder is combined with an oxidizer and process for preparation thereof.

Abstract: Composite carboxy terminated polybutadiene (CTPB) rubber base propellants, in which the CTPB inherently contains 2,2'-methylene-bis(4-methyl-6-tert-butyl)phenol (A0-2246) added during CTPB manufacture and antagonistic toward conventional antioxidants added to the CTPB propellant, are provided, which contain a synergistic (see Markush definition) antioxidant mixture highly compatible with the inherently present AO-2246. Invention also provides the antioxidant mixture per se.

Abstract: The invention provides epoxy cured rubber based propellants containing one or more N,N'-dialkyl- and/or diarylphenylenediamines chemically locked in the polymeric network to impart improved resistance to oxidative hardening of the propellant surface and inner structure.

Abstract: Solid propellant compositions wherein the polymeric binder is an all-epoxide cured carboxy-terminated rubber are described. A typical composition contains oxidizer, fuel and a binder formed by curing a carboxy-terminated polybutadiene with a specified mixture of a diepoxide and triepoxide using chromium 2-ethylhexanoate as catalyst.