Rocket composition

Rakete,/. rocket (leas often) firecracker. Raketen-antrieb, m. rocket propulsion, -bombe, /. rocket bomb, -leuchtgeschoss, n. rocket flare fire, -satz, m. rocket composition rocket attachment, -verfahren, n., -vortrieb, m. rocket propulsion, -wurf-maschine, /. rocket laimcher, rocket projector. -zeichen, n. rocket signal. 

Thiokol Corporation has a patent that covers the use of ADN in rocket compositions together with energetic binders and aluminum as fuel. The patent also covers other salts of dinitramides with nitrogen rich organic bases such as tetrazoles [21]. 

Rocket compositions of both double base and composite type are shaped into the desired form (e.g., star-shaped configurations) on extrusion or screw-type presses through a die or by casting and curing. 

PyrotccUny. — Axteroid Rocket. — Composition for 1 lb. Niter, 8 02. fine charcoal, %... 

Congreve Matches.2146 Marchand s Green Fire.2081 Rockets, Composition tor charging. 2054... 

Miarchand s Green Fire. , 2081 Rockets. Composition for charging. . 2054... 

Results of determining a density of a composite material nozzles of the rocket engine before and after impregnation by metal. 

Carbon—carbon composites for rocket nozzles or exit cones are usually made by weaving a 3D preform composed of radial, axial, and circumferential carbon or graphite fibers to near net shape, followed by densification to high densities. Because of the high relative volume cost of the process, looms have been designed for semiautomatic fabrication of parts, taking advantage of selective reinforcement placement for optimum thermal performance. 

Many compounds explode when triggered by a suitable stimulus however, most are either too sensitive or fail to meet cost and production-scale standards, requirements for safety in transportation, and storage stability. Propellants and explosives in large-scale use are based mosdy on a relatively small number of well-proven iagredients. Propellants and explosives for military systems are manufactured ia the United States primarily ia government owned plants where they are also loaded iato munitions. Composite propellants for large rockets are produced mainly by private iadustry, as are small arms propellants for sporting weapons. 

Polymer-based rocket propellants are generally referred to as composite propellants, and often identified by the elastomer used, eg, urethane propellants or carboxy- (CTPB) or hydroxy- (HTPB) terrninated polybutadiene propellants. The cross-linked polymers act as a viscoelastic matrix to provide mechanical strength, and as a fuel to react with the oxidizers present. Ammonium perchlorate and ammonium nitrate are the most common oxidizers used nitramines such as HMX or RDX may be added to react with the fuels and increase the impulse produced. Many other substances may be added including metallic fuels, plasticizers, stabilizers, catalysts, ballistic modifiers, and bonding agents. Typical components are Hsted in Table 1. 

Table 1. Typical Components of Composite Rocket Propellants...

Oxidizers. The characteristics of the oxidizer affect the baUistic and mechanical properties of a composite propellant as well as the processibihty. Oxidizers are selected to provide the best combination of available oxygen, high density, low heat of formation, and maximum gas volume in reaction with binders. Increases in oxidizer content increase the density, the adiabatic flame temperature, and the specific impulse of a propellant up to a maximum. The most commonly used inorganic oxidizer in both composite and nitroceUulose-based rocket propellant is ammonium perchlorate. The primary combustion products of an ammonium perchlorate propellant and a polymeric binder containing C, H, and O are CO2, H2, O2, and HCl. Ammonium nitrate has been used in slow burning propellants, and where a smokeless exhaust is requited. Nitramines such as RDX and HMX have also been used where maximum energy is essential. 

Solventless Extrusion Process. The solvendess process for making double-base propellants has been used ia the United States primarily for the manufacture of rocket propellant grains having web thickness from ca 1.35 to 15 cm and for thin-sheet mortar (M8) propellant. The process offers such advantages as minimal dimensional changes after extmsion, the elimination of the drying process, and better long-term baUistic uniformity because there is no loss of volatile solvent. The composition and properties of typical double-base solvent extmded rocket and mortar propellant are Hsted ia Table... 

Propellants cast into rockets are commonly case-bonded to the motors to achieve maximum volumetric loading density. The interior of the motor is thoroughly cleaned, coated using an insulating material, and then lined with a composition to which the propellant binder adheres under the environmental stresses of the system. The insulation material is generally a mbber-type composition, filled with siUca, titanium dioxide, or potassium titanate. SiUca-filled nitrate mbber and vulcanizable ethylene—propylene mbber have been used. The liner generally consists of the same base polymer as is used in the propellant. It is usually appHed in a thin layer, and may be partially or fully cured before the propellant is poured into the rocket. 

Pollution Prevention. Procedures haven been developed for recovery of composite ammonium perchlorate propellant from rocket motors, and the treatment of scrap and recovered propellant to reclaim ingredients. These include the use of high pressure water jets or compounds such as ammonia, which form fluids under pressure at elevated temperature, to remove the propellant from the motor, extraction of the ammonium perchlorate with solvents such as water or ammonia as a critical fluid, recrystalli2ation of the perchlorate and reuse in composite propellant or in slurry explosives or conversion to perchloric acid (166,167). 

---