Abstract: An assembly mating first and second tubular bodies is disclosed. The mating assembly includes at least a sleeve structure forming a part of the first tubular body and defining an inner receptacle surface region, a compression loading assembly integrally formed with, constituted by, or otherwise securable to the second tubular body and at least partially received in the sleeve structure, and a cured adhesive bond positioned between an exterior surface region of the compression loading assembly and the inner receptacle surface region to couple the sleeve structure to the compression loading assembly. The compression loading assembly is laterally expandable at at least the exterior surface region thereof and constructed and arranged relative to the cured adhesive bond so that expansion of the exterior surface region compressively loads the cured adhesive bond in a substantially lateral direction.

Abstract: Gas generating compositions and methods for their use are provided. Metal complexes are used as gas generating compositions. These complexes are comprised of a metal cation template, a neutral ligand containing hydrogen and nitrogen, and sufficient oxidizing anion to balance the charge of the complex. The complexes are formulated such that when the complex combusts, nitrogen gas and water vapor is produced. Specific examples of such complexes include metal nitrite ammine, metal nitrate ammine, and metal perchlorate ammine complexes, as well as hydrazine complexes. A binder and co-oxidizer can be combined with the metal complexes to improve crush strength of the gas generating compositions and to permit efficient combustion of the binder. Such gas generating compositions are adaptable for use in gas generating devices such as automobile air bags.

Abstract: A novel process for producing bexaammine cobalt(III) nitrate from a cobalt(II) salt is disclosed. The product is useful in formulating gas generant compositions.

Abstract: Liquid nitromalonate polyesters and methods for their preparation are disclosed. Solid propellants are provided which employ as the binder a nitromalonate polyester. These propellants are resistant to plasticizer syneresis and crystallization and provide an increase in the specific impulse of the propellant.

Abstract: The processing and cure of high solids (>85%) composite propellants at ambient temperature and pressure is accomplished by using a small amount (.ltoreq.0.1 weight percent) of a liquid dialkyl tin catalyst, such as dibutyltindiacetate and dibutyltindilaurate. The propellant binder system is composed of a branched, oxygen-containing polymer, such as polyethers, polypropylene oxide, polybutylene oxide, high homologues or mixtures thereof, and a sterically hindered diisocyanate curing agent. The liquid dialkyl tin catalyst unexpectedly serves as a wetting agent to lower the viscosity of the composite propellant formulation.

Abstract: Compositions are provided which, when burned, produce significant levels of infrared radiation, but only limited levels of visible radiation. The basic components of the compositions include a binder, an oxidizer, and an organic fuel. Preferred oxidizers include those compounds which produce large quantities of infrared radiation when the flare composition is burned. Such oxidizers include potassium nitrate, cesium nitrate, rubidium nitrate, and combinations of these compounds. The composition preferably includes significant quantities of cesium nitrate as an oxidizer. Selection of the binder is important in order to provide the composition with the desirable characteristics identified above. The binder of the present invention does not produce significant soot when burned. At the same time, the binder serves to form a composition which is processible, avoids chunking, and is compatible with the oxidizers used.

Abstract: A process of crystallizing CL-20 is disclosed. In the process, a wet CL-20 solvent/CL-20 solution is dried by azeotropic distillation of a CL-20 solvent/water azeotrope. Removal of water from the CL-20 solution permits crystallization of high density CL-20. A low density, CL-20 non-solvent is added to the resulting dry CL-20 solvent/CL-20 solution to cause precipitation of .epsilon.-polymorph CL-20. The CL-20 crystals are separated from the non-solvent and the solvent by adding sufficient water to displace the non-solvent and the solvent from the surface of the CL-20 crystals. In this fashion, the .epsilon.-polymorph CL-20 is made wet for later handling, packaging, and shipping.

Abstract: There is provided an improved process for preparing a composite propellant comprising (a) a polymeric binder, (b) a bonding agent, (c) a curing agent for the binder, (d) a metallic fuel, and (e) an ammonium salt oxidizer wherein the improvement resides in adding the metallic fuel to the propellant mix after all of the ammonium salt oxidizer has been added to the propellant mix.

Abstract: This invention relates to the production of black body-generating decoy flares for thrusted applications. Compositions are provided which, when combusted, provide black body radiation. The compositions generally include from about 20% to about 60% metal, such as magnesium or aluminum, from about 5% to about 50% ammonium perchlorate, and from about 8% to about 30% binder. Important to operation of the present invention is the production of graphitized carbon upon combustion of the composition. Accordingly, high carbon content materials are added to the compositions. These materials may include from about 5% to about 30% polyaromatic compounds, such as decacyclene, anthracene, and naphthalene. Other suitable high carbon materials include polyolefins. This invention also discloses methods of using these compositions in thrusted decoy flare applications.

Abstract: A family of high performance, large launch vehicle, solid propellants based on polyglycidyl nitrate elastomer binders. A clean, large launch vehicle, solid propellant based on a polyglycidyl nitrate elastomer binder, ammonium nitrate oxidizer and aluminum or magnesium fuel optimizes at low solids levels and produces essentially no HCl or chloride ion in the exhaust.

Abstract: A family of high performance, space motor, solid propellants based on polyglycidyl nitrate elastomer binder, ammonium perchlorate oxidizer and beryllium or beryllium hydride fuel which do not require the presence of plasticizers. A high performance, space motor, solid propellant based on a polyglycidyl nitrate elastomer binder, ammonium perchlorate or hydroxy ammonium perchlorate and beryllium or beryllium hydride optimizes performance at low solids levels.