Recent developments in solid-propellant binders
Solid propellant binders of saturated aliphatic hydrocarbons, describing microstructure, performance contribution, etc
Marsh, H. E., Jr.↗
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Suppressants for lowering propellant binder burning rate
Addition of boron compound to lower burning rate of solid propellant binder is reported. Chemical reactions involved in propellant binder modification are described. Advantages of method for lowering burning rate are analyzed.
Thompson, W. W.↗
Prediction of crosslink density of solid propellant binders
A quantitative theory is outlined which allows calculation of crosslink density of solid propellant binders from a small number of predetermined parameters such as the binder composition, the functionality distributions of the ingredients, and the extent of the curing reaction. The parameter which is partly dependent on process conditions is the extent of reaction. The proposed theoretical model is verified by independent measurement of effective chain concentration and sol and gel fractions in simple compositions prepared from model compounds. The model is shown to correlate tensile data with composition in the case of urethane-cured polyether and certain solid propellants. A formula for the branching coefficient is provided according to which if one knows the functionality distributions of the ingredients and the corresponding equivalent weights and can measure or predict the extent of reaction, he can calculate the branching coefficient of such a system for any desired composition.
Marsh, H. E., Jr.↗
Saturated hydrocarbon polymeric binder for advanced solid propellant Triennial report, 27 Oct. 1965 - 30 Sep. 1968
Developing alkane solid propellant binders
Potts, J. E.↗
Long-term aging of elastomers: Chemical stress relaxation of fluorosilicone rubber and other studies
Aerospace applications of elastomers are considered, including: propellant binders, bladder materials for liquid propellant expulsion systems, and fuel tank sealants for high-speed aircraft. A comprehensive molecular theory for mechanical properties of these materials has been developed but has only been tested experimentally in cases where chemical degradation processes are excluded. Hence, a study is being conducted to ascertain the nature, extent, and rate of chemical changes that take place in some elastomers of interest. Chemical changes that may take place in the fluorosilicone elastomer, LS 420, which is regarded as a fuel and high-temperature-resistant rubber are investigated. The kinetic analysis of the chemical stress relaxation and gel permeation chromatography studies comprise the major portion of the report.
Kalfayan, S. H.↗
Development of a hydrocarbon-type of polymer which possesses the characteristics required for use as a binder for uncoated SPO First quarterly report, May 10 - Aug. 10, 1966
Synthesis of carboxyl terminated butadiene/ isoprene copolymer polymerized by anionic techniques and hydrogenated to minimum residual unsaturization for use as propellant binder
PROPELLANT BINDER↗
Solid propellant engineering
Propellant binders terminated by acid chloride groups, ballistics of propellant-actuated devices, and applications technology satellite motor development
APPLICATIONS TECHNOLOGY SATELLITE /ATS/↗
Review of composite propellant burn rate modeling
Steady-state combustion modeling of composite solid propellants is discussed with emphasis on the Beckstead-Derr-Price (BDP) model. The BDP model and some revisions are considered with respect to the analysis of monomodal ammonium perchlorate/inert binder propellants: topics examined include continuity relations, surface area relations, characteristic surface dimension, flame heights, and energy balance. Application of the BDP model to more complicated propellants containing multiple active ingredients is described. These propellants include multimodal, mixed oxidizer, active binder, aluminized, catalyzed, and nitramine propellants. Example cases of modeling (with comparison to experimental data) are presented, and strengths and weaknesses of current modeling approaches are evaluated.
Cohen, N. S.↗
Homogenization Issues in the Combustion of Heterogeneous Solid Propellants
We examine random packs of discs or spheres, models for ammonium-perchlorate-in-binder propellants, and discuss their average properties. An analytical strategy is described for calculating the mean or effective heat conduction coefficient in terms of the heat conduction coefficients of the individual components, and the results are verified by comparison with those of direct numerical simulations (dns) for both 2-D (disc) and 3-D (sphere) packs across which a temperature difference is applied. Similarly, when the surface regression speed of each component is related to the surface temperature via a simple Arrhenius law, an analytical strategy is developed for calculating an effective Arrhenius law for the combination, and these results are verified using dns in which a uniform heat flux is applied to the pack surface, causing it to regress. These results are needed for homogenization strategies necessary for fully integrated 2-D or 3-D simulations of heterogeneous propellant combustion.
Chen, M.↗
Saturated hydrocarbon polymeric binder for advanced solid propellant and hybrid solid grains Quarterly report no. 2, 1 Feb. - 30 Apr. 1966
Synthesis and analysis of ethylene-neohexene copolymers with other non ketene-imine group free radicals for solid and hybrid grain propellant saturated hydrocarbon binder program
FREE RADICAL↗
Effects of Ionizing Radiation on Solid Rocket Motor Components
Problems which the solid propellant rocket engineer will encounter in designing for long-term storage in a radiation environment are discussed. A summary of present knowledge of the radiation environment is given. Mechanisms of radiation degradation and its effects on tensile properties of propellant binders are discussed qualitatively. Data from a program of irradiation of several propellants is presented. Properties of two of the propellants were changed significantly by doses of the order of 4 x 10(exp 6) rads.
RADIATION↗
AP reclamation and reuse in RSRM propellant
A solid propellant ingredient reclamation pilot plant has been evaluated at the Strategic Operations of Thiokol Corporation, located in Brigham City, Utah. The plant produces AP wet cake (95 percent AP, 5 percent water) for recycling at AP vendors. AP has been obtained from two standard propellant binder systems (PBAN and HTPB). Analytical work conducted at Thiokol indicates that the vendor-recrystallized AP meets Space Shuttle propellant specification requirements. Thiokol has processed 1-, 5-, and 600-gallon propellant mixes with the recrystallized AP. Processing, cast, cure, ballistic, mechanical, and safety properties have been evaluated. Phillips Laboratory static-test-fired 70-pound and 800-pound BATES motors. The data indicate that propellant processed with reclaimed AP has nominal properties.
Miks, Kathryn F.↗
Polymer research
Stress-strain distribution in elastomers, and chemical and physical properties of prepolymers, rigid urethane foam, and thermoplastic rubbers for composite solid propellant binders
ELASTOMER↗
Study of the synthesis of block copolymers Final report, 18 Oct. 1966 - 18 Aug. 1970
Chemical and mechanical properties and synthesis of 4-vinylbiphenyl-isoprene ABA block copolymers for permeation and propellant binder studies
Heller, J.↗
New type of trifunctional alcohol
New type of trifunctional alcohol was synthesized from commercially available trimer acid. Trifunctional alcohol is hydrocarbon with widely separated terminal hydroxyl groups, and was expressly developed as crosslinking agent for preparation of polyurethane propellants, binders and case liners.
Marsh, H. E., Jr.↗
Chemistry of the system: Al2O3(c)minus HCL aqueous
In order to study exhaust gas chemistry for the space shuttle, the vapor pressure of 2 to 1 weight mixtures of 3-M hydrochloric acid and Al2O3 was studied over a l80 minute reaction period at 31 C. The Al2O3 sample was one of high surface area furnished by NASA Langley Research Center. A brief review is given for aqueous aluminum chemistry, and the chemical reactions of combustion products (exhaust gases) of aluminum propellant binders for the space shuttle are listed.
Tyree, S. Y., Jr.↗
Low-temperature elastomer production and curing
Thermally and chemically stable polymers are needed for materials applications, particularly highly-stable elastomers for solid propellant binders where initial high temperature required for dissolving anhydride in polymer is deerimental. Solvent reactant system allows polymerization without condensation of products under low heat. Solvents utilized were dimethylacetamide, dimethyflormamide, etc.
Ingham, J. D.↗
Storage of solid propellants in a dry environment
Storage of solid propellants in either a dry or a vacuum environment causes a significantly greater increase in the propellants' modulus and maximum tensile strength than does ambient storage. It is postulated that these physical property changes can be attributed to the effect trace amount of moisture has on the bond between the propellants' binder and oxidizer.
Udlock, D. E.↗