Search NASA⌕ Search

SEARCH · Search NASA

Results for “HIGH ENERGY 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.

Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.

At least 19 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1973

Current status of free radicals and electronically excited metastable species as high energy propellants

A survey is presented of free radicals and electronically excited metastable species as high energy propellants for rocket engines. Nascent or atomic forms of diatomic gases are considered free radicals as well as the highly reactive diatomic triatomic molecules that posess unpaired electrons. Manufacturing and storage problems are described, and a review of current experimental work related to the manufacture of atomic hydrogen propellants is presented.

Rosen, G.↗
NASA NTRS1964

High Energy Propellants: A Continuing Bibliography

Through its Continuing Bibliography Program, NASA will prepare and distribute a series of bibliographies devoted to specific subjects in the aerospace field. The subjects have been selected because of their significant relationship to current developments in the space program, and because of a clearly established interest in them on the part of aerospace specialists. In order to assure that future information will become available in an orderly manner, each Continuing Bibliography will be updated periodically in the form of supplements which can be appended to the original edition. High Energy Propellants , NASA-SP-7002, is the first publication to appear under this program. It presents a selection of annotated references to unclassified reports and journal articles announced in Technical Publications Announcements (TPA) , Scientific and Technical Aerospace Reports (STAR) , and International Aerospace Abstracts (IAA) . Prime emphasis is given to those references which are concerned with research and development studies on solid, liquid, and hybrid propellants and oxidizers, but the bibliography also provides extensive coverage of such related topics as propellant handling and storage, combustion characteristics, toxicity, and hazards and safety measures. Each entry in the bibliography consists of a citation and an abstract. The listing of entries is arranged in two major groups: all report literature references are contained in the first group and are subdivided according to their date of announcement in TPA and STAR ; the second group includes all published literature references subdivided according to their date of announcement in IAA . All reports and articles cited were introduced into the NASA Information System during the period January 1962-March, 1964.

Bibliography↗
NASA NTRS1975

Potential seal candidates for high-energy propellants

Five potential seal candidates (linear Tefzel, linear Halar, crosslinked Halar, Viton ECD-006, and phosphazine fluoroelastomer) were evaluated for the orbital maneuvering system of the space shuttle. Since this system employs nitrogen tetroxide (N2O4) and monomethyl hydrazine (MMH) as hypergolic propellants, the seal candidates were selected on the basis of projected chemical resistance as well as rheological behavior. Chemical resistance to these high-energy fuels was determined via conventional isothermal and thermal cycling immersion tests. Rheological measurements, however, were performed on O-rings molded from the subject seal candidates. Properties determined, such as cyclic work and hysteresis, stress relaxation, and indicated modulus, therefore, relate to the O-ring seals themselves.

Merz, P. L.↗
NASA NTRS2016

Propulsion Estimates for High Energy Lunar Missions Using Future Propellants

High energy propellants for human lunar missions are analyzed, focusing on very advanced ozone and atomic hydrogen. One of the most advanced launch vehicle propulsion systems, such as the Space Shuttle Main Engine (SSME), used hydrogen and oxygen and had a delivered specific impulse of 453 seconds. In the early days of the space program, other propellants (or so called metapropellants) were suggested, including atomic hydrogen and liquid ozone. Theoretical and experimental studies of atomic hydrogen and ozone were conducted beginning in the late 1940s. This propellant research may have provided screenwriters with the idea of an atomic hydrogen-ozone rocket engine in the 1950 movie, Rocketship X-M. This paper presents analyses showing that an atomic hydrogen-ozone rocket engine could produce a specific impulse over a wide range of specific impulse values reaching as high as 1,600 s. A series of single stage and multistage rocket vehicle analyses were conducted to find the minimum specific impulse needed to conduct high energy round trip lunar missions.

rocket propulsion↗
NASA NTRS2015

Advanced Booster Composite Case/Polybenzimidazole Nitrile Butadiene Rubber Insulation Development

The NASA Engineering and Safety Center (NESC) was requested to examine processing sensitivities (e.g., cure temperature control/variance, debonds, density variations) of polybenzimidazole nitrile butadiene rubber (PBI-NBR) insulation, case fiber, and resin systems and to evaluate nondestructive evaluation (NDE) and damage tolerance methods/models required to support human-rated composite motor cases. The proposed use of composite motor cases in Blocks IA and II was expected to increase performance capability through optimizing operating pressure and increasing propellant mass fraction. This assessment was to support the evaluation of risk reduction for large booster component development/fabrication, NDE of low mass-to-strength ratio material structures, and solid booster propellant formulation as requested in the Space Launch System NASA Research Announcement for Advanced Booster Engineering Demonstration and/or Risk Reduction. Composite case materials and high-energy propellants represent an enabling capability in the Agency's ability to provide affordable, high-performing advanced booster concepts. The NESC team was requested to provide an assessment of co- and multiple-cure processing of composite case and PBI-NBR insulation materials and evaluation of high-energy propellant formulations.

Gentz, Steve↗
NASA NTRS2007

Metallic Hydrogen - Potentially a High Energy Rocket Propellant

Pure metallic hydrogen is predicted to have a specific impulse (Isp) of 1700 seconds, but the reaction temperature is too high for current engine materials. Diluting metallic hydrogen with liquid hydrogen can reduce the reaction temperature to levels compatible with current material limits and still provide an Isp greater than 900 s. Metallic hydrogen has not yet been produced on earth, but experimental techniques exist that may change this situation. This paper will provide a brief description of metallic hydrogen and the status of experiments that may soon produce detectable quantities of this material in the lab. Also provided are some characteristics for diluted metallic hydrogen engines and launch vehicles.

Cole, John↗
NASA NTRS1991

Advanced chemical propulsion at NASA Lewis: Metallized and high energy density propellants

Two of the programs at the NASA Lewis Research Center investigating advanced systems for future space missions are the Metallized Propellant Program and the Advanced Concepts Program. Each program includes both experimental and theoretical studies of future propellants and the associated vehicle impacts and significant payload benefits for many types of space transportation. These programs are described.

Palaszewski, Bryan A.↗