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Cohen, N. S.

Publications and source records attributed to Cohen, N. S..

At least 19 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1993

Hybrid rocket combustion study

The objectives of this study of 'pure' or 'classic' hybrids are to (1) extend our understanding of the boundary layer combustion process and the critical engineering parameters that define this process, (2) develop an up-to-date hybrid fuel combustion model, and (3) apply the model to correlate the regression rate and scaling properties of potential fuel candidates. Tests were carried out with a hybrid slab window motor, using several diagnostic techniques, over a range of motor pressure and oxidizer mass flux conditions. The results basically confirmed turbulent boundary layer heat and mass transfer as the rate limiting process for hybrid fuel decomposition and combustion. The measured fuel regression rates showed good agreement with the analytical model predictions. The results of model scaling calculations to Shuttle SRM size conditions are presented.

Strand, L. D.↗
NASA NTRS1992

Hybrid rocket fuel combustion and regression rate study

The objectives of this study are to develop hybrid fuels (1) with higher regression rates and reduced dependence on fuel grain geometry and (2) that maximize potential specific impulse using low-cost materials. A hybrid slab window motor system was developed to screen candidate fuels - their combustion behavior and regression rate. Combustion behavior diagnostics consisted of video and high speed motion pictures coverage. The mean fuel regression rates were determined by before and after measurements of the fuel slabs. The fuel for this initial investigation consisted of hydroxyl-terminated polybutadiene binder with coal and aluminum fillers. At low oxidizer flux levels (and corresponding fuel regression rates) the filled-binder fuels burn in a layered fashion, forming an aluminum containing binder/coal surface melt that, in turn, forms into filigrees or flakes that are stripped off by the crossflow. This melt process appears to diminish with increasing oxidizer flux level. Heat transfer by radiation is a significant contributor, producing the desired increase in magnitude and reduction in flow dependency (power law exponent) of the fuel regression rate.

Strand, L. D.↗
NASA NTRS1989

Erosive burning threshold conditions in solid rocket motors

Erosive burning has been predicted to be enhanced by factors that increase the level of turbulence close to the propellant surface, such a high cross flow velocity, low surface blowing rate, propellant surface roughness, and adverse pressure gradient. A study is reported which was carried out with the objective of measuring the effects of these parameters on the scaling to larger rocket motor sizes of the transition to, or threshold conditions for, erosive burning rate augmentation. The results are used to develop a scaling criterion for the threshold conditions for erosive burning.

Strand, L. D.↗
NASA NTRS1989

Solid propellant combustion response to oscillatory radiant heat flux

A progress report is given on a research project to use the microwave Doppler velocimeter technique to measure the combustion response to an oscillating thermal radiation source (CO2 laser). The test technique and supporting analyses are described, and the results are presented for an initial test series on the nonmetallized, composite propellant, Naval Weapons Center formulation A-13. It is concluded that in-depth transmission of radiant heat flux is not a factor at the CO2 laser wave length.

Strand, L. D.↗
NASA NTRS1988

The scaling of the threshold conditions for solid propellant erosive burning

Rocket test firings were performed to measure the transition length threshold conditions while systematically varying various rocket motor parameters. These include the crossflow velocity, the chamber pressure, the propellant nonerosive burning rate, the propellant surface roughness, and the motor port diameter. The erosive burning trends with varying propellant burning rate, motor chamber pressure, and mass flow rate are consistent with published results.

Strand, L. D.↗
NASA NTRS1987

The scaling of the threshold conditions for solid propellant erosive burning

The effects of the parameters that are considered to influence most strongly the scaling to larger rocket motor sizes of the transition or threshold conditions for erosive burning rate augmentation are measured and a scaling criterion for the threshold conditions for erosive burning is developed. The results are presented for a series of motor firings that were performed to measure the transition length threshold conditions (axial position at which deviation from nonerosive burning rate begins) while attempting to systematically vary the parameters that are considered to control the phenomena. The results of attempts to correlate the threshold conditions with several flow parameters are presented.

Strand, L. D.↗
NASA NTRS1986

Erosive burning research

A status report is given on the results for the completed tests in a series of motor firings being carried out to measure the effects of the parameters that are considered to most strongly influence the scaling to larger rocket motor sizes of the transition to/or threshold conditions for erosive burning rate augmentation. Propellant burning rates at locations along the axis of the test motors are measured with a newly developed plasma capacitance gauge technique. The measured results are compared with erosive-burning predictions from a supporting ballistics analysis. The completed motor firings have successfully demonstrated response to the designed test variables. The trends with varying propellant burning rate, chamber pressure, and mass flow rate are consistent with existing results, but no pronounced effect of surface roughness has been observed. Rather, the influence of propellant oxidizer particle size on erosive burning is through its effect on the base, no-corssflow burning rate.

Strand, L.↗
NASA NTRS1986

Mapping the Structure of Heterogeneous Materials

Image-processing microdensitometer/Fourier analyzer yields statistics of subcomponent distribution. Nondestructive method for studying structure heterogeneous materials uses energy-dispersive X-ray analysis in scanning electron microscope. Scanning microdensitometer/Fourier analyzer (SMFA) is applied to SEM images to obtain statistics about sample structure. Method originally developed for studying effect on combustion of fine structure of composite solid propellants.

Strand, L. D.↗
NASA NTRS1983

Effects of AP particle size on combustion response to crossflow

An analytical model is developed for the linearized velocity-coupled combustion response function. The model treats elements of response to perturbations in pressure, in composition due to the heterogeneity of composite propellants, and in crossflow velocity. The effects of AP particle size are accounted for in terms of effects on controlling ballistics properties and in terms of fluctuations in propellant composition. There are two facets of the crossflow problem: the effect of crossflow velocity on the various response elements, and the response to velocity perturbations. Both are dealt with in this paper. Important trends derived from series of parametric computations are described.

Cohen, N. S.↗
NASA NTRS1983

Equations for Composite-Propellant Burning

Reported study of composite-propellant burning summarizes recent advances in understanding behavior of propellant formulations based on ammonium perchlorate (AOP), binder, and aluminum in various proportions and particle size distributions. Approach presented incorporates adapted version of earlier model for monopropellant AP. Objective is to predict burning-rate characteristics of composite propellants at high pressure.

Strand, L. D.↗
NASA NTRS1983

Combustion response to compositional fluctuations

A mechanism involving compositional fluctuations at certain frequencies is examined by which the heterogeneity of a composite solid propellant may contribute directly to the combustion response function of combustion instability theory. A combustion model appropriate to ammonium perchlorate (AP) is used to derive the combustion response to compositional fluctuations, and the properties of the combustion response are discussed in terms of the theoretical results obtained. The concentration exponent, i.e., the dependence of the burn rate on AP concentration, is found to be a signficant combustion parameter and to have a tremendous range of variability. It is suggested that the combustion response to compositional fluctuations may be a dominating factor in driving combustion instability.

Cohen, N. S.↗
NASA NTRS1982

Porous plate analog burner study of composite solid propellant flame structure

A porous plate burner system for studying the structure and interaction of diffusion flames from adjacent unlike sources of oxidizer to simulate the behavior of solid propellant flames is presented. The passage of oxidizer gases through ports of determined diameters represents decomposing oxidizer crystals, and are adjustable for various oxidizer/fuel ratio experiments. Tests with air, ethane, oxygen, and oxygen-air mixtures are described, with parameters of flow rate, oxygen/fuel ratio, and pressure. Coarse ports are found to be oxidizer rich, while fine ports are stoichiometric. More heat feedback is found with fine ports, indicating that fine particle propellant systems burn faster unless fuel allocation is such that the reduced temperature overcomes the reduced diffusion length. Further observations on the interactions of flames are reported.

Strand, L. D.↗
NASA NTRS1981

Effects of AP size distribution on the pressure-coupled response function

Progress in theoretical and experimental research to determine effects of AP size distribution on the pressure-coupled response function is presented. The theoretical model was based upon a preferred frequency mechanism in which ordered fluctuations in the propellant formulation, dependent upon the heterogeneity, contributed to the response. Experiments to charaterize and relate the heterogeneity to response function behavior consisted of scanning electron microscope studies and measurements of dynamic burning at constant pressure. The concept, differences between ideal models and real propellants, and results thus far obtained are discussed.

Cohen, N. S.↗