Abstract: Thermosetting powder coatings are provided which comprise a high epoxide equivalent weight epoxy resin or mixture of epoxy resins, a cure catalyst for the epoxy resin, an acrylic resin and a polyamide resin. These powder coatings are useful for forming corrosion resistant, essentially crack-free coatings on metal cable, especially cable which is subjected to post-tensioning.

Abstract: A solid propellant grain for a gas generator such as a missile canister erection actuator. The grain provides a sustain phase followed by a boost phase which may then be followed by another sustain phase. The aft portion of the grain may have the configuration of an end burner to provide the initial sustain phase. The middle portion contains a longitudinally extending cavity in which is disposed a plug for supporting the grain during the initial sustain phase against collapse or cracking. A gap is provided between the plug and the wall of the cavity to provide effective propellant burnign surface area along the cavity wall for the boost phase. The cavity and plug, which terminate at the aft portion, may extend longitudinally through the forward portion of the grain.

Abstract: Thermosetting powder coatings are provided which comprise a high epoxide equivalent weight epoxy resin or mixture of epoxy resins, a cure catalyst for the epoxy resin, an acrylic resin and a polyamide resin. These powder coatings are useful for forming corrosion resistant, essentially crack-free coating on metal cable, especially cable which is subjected to post-tensioning.

Abstract: Binders for propellants for the like comprise elastomers which are based on block copolymers in which a pair of poly(caprolactone) blocks flank a central hydroxyl-terminated poly(butadiene) block. The block polymers are cured with isocyanates through the OH termini of the poly(caprolactone) blocks. The elastomers have inherent energies and other characteristics intermediate those of PCP and HTPB and have good compatibility with nitrate ester plasticizers.

Abstract: A composite electromagnetic barrel is preloaded to minimize rail separation by jacking the rails radially outwardly away from each other and wedging a pair of insulating members between the rails to retain the preload. The jacking force is then released.

Abstract: Methods for forming or purifying organometallic compounds of elements of Group III-A of the Periodic Table. An intermediate compound is formed which is an adduct of the desired organometallic compound and a Group I-A or Group II-A compound. The adduct is nonvolatile, so volatile impurities are removed from the adduct by distillation. The adduct is decomposed to release the volatile organometallic compound, which is then distilled away from the nonvolatile remainder of the adduct. The method can be used to produce organometallic compounds which are substantially free of volatile metallic compounds and complexed solvents. A method of separating volatile Group II-B impurities from volatile Group III-A compounds is also disclosed.

Abstract: An integrated stage rocket motor arrangement provides boost and repeated throttling post boost operations, on demand, and includes an attitude control system. The rocket motor includes a plurality of casings for enclosing an initial boost motor, a post boost motor, and gas generator means for producing gases that are used for re-ignition of the post boost motor and as a motive source for the attitude control system. The boost motor and post boost motor are contained within the same enclosure but are separated by an internal bulkhead. The rocket motor has a plurality of nozzles one of which is located aft of the boost motor and another located within the internal bulkhead that separates the boost and post boost motors.

Abstract: Compositions for stabilizing rigid (unplasticized) halogen-containing organic polymers against the deteriorative effects of heat, ultra-violet light and weathering comprise organotin or non-tin metal salt primary heat stabilizers in combination with esters of polyhydrocarbyl ether glycols.

Abstract: A gas generant composition especially adapted for inflating automotive airbags in the event of a vehicle collision to protect the occupants of the vehicle from injury. The composition consists essentially of 65-74% alkali metal azide; 10-28% ferric oxide; 6-16% sodium nitrate; 0.1-2% fumed silica; and 0-2% molybdenum disulfide. The composition burns at from about 1.2 to about 1.7 inches per second (about 3.0 to about 4.3 cm/sec).

Abstract: A method of and apparatus for casting uncured solid propellant in solid propellant rocket motors includes a casting bayonet having annular slits formed in the exit end thereof that improve the fluidity and self-leveling behavior of the uncured propellant. Both of these effects eliminate or reduce the trapping of air in the cast propellant, thus providing a better product.

Abstract: A process for preparing curable, aqueous strippable, polymeric materials for application, in succession, as masks, to a specific area of each of a plurality of printed circuit boards that is to be protected from the stripping and plating processes associated with gold finger plating, during the fabrication thereof, includes forming a coating of substantially identical, uniformly spaced, areas of polymeric material on a continuous length of carrier web, applying a cover coating over the carrier web and the uniformly spaced areas of polymeric material with the cover coating having a width substantially the same as that of the carrier film, and winding up in a roll the continuous length of carrier web and the cover coating with the uniformly spaced polymeric material sandwiched therebetween.

Abstract: A segmented rocket motor case includes wedge members for forcing the case segments into position to remove free play at the joint thereof which may otherwise interfere with or upset the missile's guidance system and throw it off target. A lap joint member for such a joint includes a shoulder having a surface for attachment of a membrane seal assembly for a pulsed rocket motor. A through bulkhead initiator communicates from the forward segment via a fitting which extends through the membrane seal assembly with an igniter for the propellant grain within the aft segment to eliminate the necessity of running explosive transfer lines along the outside of the case from a safe and arm device and other controls at the head end of the rocket motor.

Abstract: A portable, self-contained, light-weight, compact and explosion-proof device, that is readily dismantable and transportable by automobile or aircraft, for inspecting the ignition surfaces of a solid propellant rocket motor can be introduced into the motor from the aft end thereof with or without the nozzle in place and is characterized in that a light source, reflecting means and viewing means are so arranged therein as to allow an operator to observe from outside the motor the condition of the entire ignition surface from either the aft end or the head end of the motor.

Abstract: A lubricating composition for PVC or the like is provided by partially saponifying a triglyceride material, such as an animal tallow, with calcium hydroxide in the presence of at least about 10% water. The minor amount of oxidized polyethylene admixed with the saponified material maintains the resulting soap and esters in a homogeneous lubricating compositions. The lubricating compositions are particularly suitable for preparing rigid resin compositions.

Abstract: The invention is concerned with reducing the effect of a progressive surface area versus web thickness relationship in a rocket motor and is particularly useful with center perforate propellant grains where the chamber pressure versus time history is generally progressive. In a very short action time rocket motor, it is desirable to keep the chamber pressure as close as practical to the peak during the entire burn to increase the propellant burn rate. The multiple-stage throat makes this possible in a motor that uses the cost effective center perforate propellant grain design and operates by allowing a first stage throat to erode at a predictable rate while the area of the propellant burning surface is increasing. The motor initial Kn (propellant surface area divided by nozzle area) is raised by using a relatively small initial size for the first stage throat and as a result the rocket motor reaches peak chamber pressure quickly.

Abstract: A rocket propelled vehicle includes a lower stage solid propellant rocket motor and at least one upper stage solid propellant rocket motor. Each of the rocket motors includes a case, a nozzle and a solid propellant having a central combustion chamber, with the case of the lower stage motor, in a preferred embodiment, being open at the forward end and the case of the upper stage motor being open at the aft end and forming a continuation of the open end of the lower stage case, with a layer of slow burning material cast on the surface defining the central combustion chamber of the upper stage solid propellant, and with ignition of all stages being accomplished approximately simultaneously through operation of a single ignition system.

Abstract: An auxiliary gas generator is used to provide gas for steering and pointing control of a multi-stage rocket motor system to a head or forward end located final interception maneuvering stage. During lower stage operation, this gas is routed through the "Divert" thrusters of the final interception stage through a check valve. When control is not required, the gas can be either dumped through all thrusters or all thrusters can be closed and the gas dumped into the lower stages. As each of the lower stages is burned out, it is discarded. Using one or more gas generating propellant packages provided therein, the final interception stage maneuvers to the target.

Abstract: The device, in a first embodiment, has utility for operation on a dual pulse missile including a booster segment for launching and includes several main components, as follows: an inertial mass, a shaft with a zig zag channel, a gearless electric motor, a switch deck and blocking rotor, another blocking rotor, and a spring which provides a restoring force which acts against the inertia of the inertial mass. In a second embodiment, the device has utility for operation on a triple pulse missile including a booster segment for launching and includes several main components, as follows: two inertial masses, a shaft with a unique zig zag channel, two gearless electric motors, two switch decks with blocking rotors, two springs which provide restorative forces which act against the inertia of the inertia masses.

Abstract: Compositions comprising the combination of an organotin mercaptide and a polyformal of a dithiodiglycol are useful for stabilizing halogen-containing organic polymers against the deteriorative effects of heat, light and weathering.

Abstract: Compositions and methods for developing quinone diazide positive-working photoresists. The compositions consist essentially of an aqueous solution of a tetraalkylammonium hydroxide primary alkali and an alkanolamine having the following structure: ##STR1## wherein n is zero or 1, and each R is independently selected from hydrogen, methyl, or ethyl. The methods involve use of this composition to develop the indicated photoresists. The addition of an alkanolamine of the indicated type prevents the formation of irregular deposits on the edges of unexposed portions of the photoresist lines when the photoresist is developed. Selection of these alkanolamines also increases the uniformity of line widths of photoresist lines developed according to the present invention, and increases the process latitude of the developer.