Operational range safety for solid-propellant sounding rockets.
Hazards in sounding rocket assembly and launch operations and safety techniques at NASA Wallops station noting storage, explosive control, ground safety, etc
Parker, L. C.↗
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Results for “Solid propellant”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Solid propellant dynamic mechanical properties and blast effects.
Explosive proclivities of composite propellants related to dynamic mechanical properties
Amster, A. B.↗
A test program to determine the mechanical behavior of solid propellants quarterly progress report, 1 jan. - 31 mar. 1968
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Sharma, M. G.↗
Solid propellant engineering
Surface temperature relations for ignition material deflagration onset, and static tests of Applications Technology Satellite motor
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Review of the combustion instability characteristics of solid propellants
Classes of instability behavior are reviewed and related to theory and to aspects of the combustion process. Experimental methods for small-scale testing of stability characteristics of propellants are described and typical results are presented.
E W Price↗
Rapid linear pyrolysis of composite solid propellant ingredients
Rapid linear pyrolysis of polymethyl methacrylate
Simon, D. R.↗
Solid propellant selection and characterization
The techniques of propellant selection and characterization and the compromises that may be forced on the designer by the change of a propellant parameter are discussed. Rules for the selection of a general propellant type are presented. The characterization of various propellant properties is then approached parameter by parameter. Tailoring pitfalls and compromises are identified whenever possible, and appropriate cross references are used. Related design criteria monographs frequently are cited for a more detailed treatment of the topic under discussion. A list of source references is provided. These references, coupled with established texts in the field, should give the depth of knowledge necessary to the designer to aid in the selection of the most nearly optimum propellant for the design application.
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Task 1, Design Analysis Report: Pulsed plasma solid propellant microthruster for the synchronous meteorological satellite
Thermal vacuum design supporting thruster tests indicate no problems under the worst case conditions of sink temperature and spin rate. The reliability of the system was calculated to be 0.92 for a five-year mission. Minus the main energy storage capacitor it is 0.98.
Guman, W. J.↗
Effects of normal acceleration on transient burning rate augmentation of an aluminized solid propellant
Instantaneous burning rate data for a polybutadiene acrylic acid propellant, containing 16 weight percent aluminum, were calculated from the pressure histories of a test motor with 96.77 sq cm of burning area and a 5.08-cm-thick propellant web. Additional acceleration tests were conducted with reduced propellant web thicknesses of 3.81, 2.54, and 1.27 cm. The metallic residue collected from the various web thickness tests was characterized by weight and shape and correlated with the instantaneous burning rate measurements. Rapid depressurization extinction tests were conducted in order that surface pitting characteristics due to localized increased burning rate could be correlated with the residue analysis and the instantaneous burning rate data. The acceleration-induced burning rate augmentation was strongly dependent on propellant distance burned, or burning time, and thus was transient in nature. The results from the extinction tests and the residue analyses indicate that the transient rate augmentation was highly dependent on local enhancement of the combustion zone heat feedback to the surface by the growth of molten residue particles on or just above the burning surface. The size, shape, and number density of molten residue particles, rather than the total residue weight, determined the acceleration-induced burning rate augmentation.
Northam, G. B.↗
Solid propellant processing factor in rocket motor design
The ways are described by which propellant processing is affected by choices made in designing rocket engines. Tradeoff studies, design proof or scaleup studies, and special design features are presented that are required to obtain high product quality, and optimum processing costs. Processing is considered to include the operational steps involved with the lining and preparation of the motor case for the grain; the procurement of propellant raw materials; and propellant mixing, casting or extrusion, curing, machining, and finishing. The design criteria, recommended practices, and propellant formulations are included.
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Hydrocarbon polymeric binder for advanced solid propellant
The results of curing vinyl alcohol terpolymers of ethylene, propylene and vinyl acetate are reported for an average functionality of 1.24 when reacted with an equivalent amount of diisocynate, and saturated polyisoprene derivative is described having terminal methyl ester functionality. The development is reported of two hydroxy-telechelic polyisoprenes prepared by DEAB initiated free radical polymerization followed by LiAlH4 reduction of the end groups.
Potts, J. E.↗
Hydrocarbon polymeric binder for advanced solid propellant
Various experimental factors were examined to determine the source of difficulty in an isoprene polymerization in the 5-gallon reactor which gave a non-uniform product of low functionality. It was concluded that process improvements relating to initiator and monomer purity were desirable, but that the main difficulty was in the initiator feed system. A new pumping system was installed and an analog simulation of the reactor, feed system and initiator decomposition kinetics was devised which permits the selection of initial initiator concentrations and feed rates to use to give a nearly uniform initiator concentration throughout a polymerization run. An isoprene polymerization was run in which the process improvements were implemented.
Potts, J. E.↗
Effects of the acceleration vector on transient burning rate of an aluminized solid propellant.
Experimental results concerning the transient burning-rate augmentation of a 16% aluminum polybutadiene acrylic acid (PBAA) propellant burned in a 2-in. web motor at pressure levels from 300 to 1200 psia with centrifugal accelerations from 0 to 140 g. The orientation of the acceleration vector was varied to determine its effect on the transient burning rate. The burning-rate augmentation was strongly dependent on (1) acceleration level, (2) propellant distance burned (or burn time), and (3) orientation of the acceleration vector with respect to the burning surface. This transient rate augmentation resulted from the retention of molten metallic residue on the burning surface by the normal acceleration loading. The presence of the residue altered the combustion zone heat transfer and caused increased localized burning rates, as evidenced by the pitted propellant surfaces that were observed from extinction tests conducted at various acceleration levels.
Northam, G. B.↗
Flame spectra of solid propellants during unstable combustion.
The spectral and temporal details of the flames of a series of ammonium perchlorate-polyurethane propellants during both unstable and stable combustion were observed experimentally. A 400-scan per second optical spectrometer operating in the middle infrared region was used. During unstable combustion at low ratios of chamber free volume to nozzle throat area, three different frequencies were observed simultaneously. These were attributable to at least two mechanisms. During stable combustion periodic fluctuations in flame temperature and composition were also observed. Some aspects of theory of bulk mode instability were confirmed, but the assumptions of constant flame temperature and constant composition were found to be inaccurate.
Eisel, J. L.↗
Monitor for physical property changes in solid propellants
Specially designed sensor is attached to or imbedded in propellant. When sensor is driven into vibration, it moves with a phase lag directly proportional to internal friction or loss coefficent. Resonance frequency of the system is related to Young's modulus. Modulus or internal friction can be monitored over long period of time.
Black, R. E., Jr.↗
Pulsed plasma solid propellant microthruster for the synchronous meteorological satellite. Task 3: Model specifications report
The specifications include applicable documents, requirements, and quality assurance provisions. The specifications also include results of earlier tasks of analysis and preliminary design.
Guman, W. J.↗
Advanced solid propellant motor insulation
An advanced lightweight insulation system suitable for use in long duration, low pressure planetary orbiter-type motor applications was developed. Experiments included the screening of various filler and binder materials with optimization studies combining the best of each. Small scale test motor data were used to judge the degree of success.
Smith, P. L.↗
Solid propellant grain design and internal ballistics
The ballistic aspects of grain design were studied to outline the steps necessary to achieve a successful grain design. The relationships of the grain design to steady-state mass balance and erosive burning are considered. Grain design criteria is reviewed, and recommended design criteria are included.
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