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Results for “Hybrid Rockets”

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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At least 73 records · Page 4
All sourcesNASA NTRSDOE OSTI
NASA NTRS1968

Research on the combustion mechanism of hybrid rockets

Investigations of the turbulent boundary layer with heat transfer, mass transfer, and chemical reactions are reviewed, with emphasis on recent studies motivated by the hybrid combustion problem. Relatively high mass injection rates and rapidly changing composition and enthalpy boundary conditions along the boundary layer edge are inherent to the hybrid problem, and earlier treatments are somewhat inconsistent with this situation. To account for these aspects, a more recent analysis reviewed here differs from earlier ones in the way the mass transfer number B, or thermochemical driving force, is related to the thermodynamic parameters of the propellants and flow and in the treatment of the heat transfer blocking effect caused by wall mass injection. It is shown that the present boundary layer analysis is applicable up to B 100, while the maximum thermochemical driving force available from any possible combination of propellants is less than 40. This analysis is used to predict the regression rate performance of several typical propellant combinations with good accuracy.

G A Marxman↗
NASA NTRS1993

Hybrid rocket propulsion

Topics addressed are: (1) comparison of the theoretical impulses; (2) comparison of the density-specific impulses; (3) general propulsion system features comparison; (4) hybrid systems, booster applications; and (5) hybrid systems, upper stage propulsion applications.

Holzman, Allen L.↗
NASA NTRS2014

High Energy Density Additives for Hybrid Fuel Rockets to Improve Performance and Enhance Safety

We propose a conceptual study of prototype strained hydrocarbon molecules as high energy density additives for hybrid rocket fuels to boost the performance of these rockets without compromising safety and reliability. Use of these additives could extend the range of applications for which hybrid rockets become an attractive alternative to conventional solid or liquid fuel rockets. The objectives of the study were to confirm and quantify the high enthalpy of these strained molecules and to assess improvement in rocket performance that would be expected if these additives were blended with conventional fuels. We confirmed the chemical properties (including enthalpy) of these additives. However, the predicted improvement in rocket performance was too small to make this a useful strategy for boosting hybrid rocket performance.

strained hydrocarbons↗
NASA NTRS1990

A feasibility study and mission analysis for the Hybrid Plume Plasma Rocket

The Hybrid Plume Plasma Rocket (HPPR) is a high power electric propulsion concept which is being developed at the MIT Plasma Fusion Center. This paper presents a theoretical overview of the concept as well as the results and conclusions of an independent study which has been conducted to identify and categorize those technologies which require significant development before the HPPR can be considered a viable electric propulsion device. It has been determined that the technologies which require the most development are high power radio-frequency and microwave generation for space applications and the associated power processing units, low mass superconducting magnets, a reliable, long duration, multi-megawatt space nuclear power source, and long term storage of liquid hydrogen propellant. In addition to this, a mission analysis of a one-way transfer from low earth orbit (LEO) to Mars indicates that a constant acceleration thrust profile, which can be obtained using the HPPR, results in faster trip times and greater payload capacities than those afforded by more conventional constant thrust profiles.

Sullivan, Daniel J.↗