Effects of the acceleration vector on transient burning-rate augmentation of an aluminized solid propellant
Aluminized solid propellant transient burning rate augmentation during acceleration loads
Northam, G. B.↗
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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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Role of scanning electron microscopy in the study of solid propellant combustion. III - The surface structure and profile characteristics of burning composite solid propellants
Composite solid propellants surface structure and profile characteristics burning with various oxidizers and polyurethane binder by scanning electron microscopy
Boggs, T. L.↗
A study of the application of microwave techniques to the measurement of solid propellant burning rates Final report
Utilization of Doppler microwave interferometer for measuring solid propellant burning rates
Wood, H. L.↗
Experimental performance of a modular turbojet combustor burning natural gas fuel
Swirl-can modular turbojet combustor burning natural gas fuel
Marchionna, N. R.↗
Silicon burning and the synthesis of cosmic- ray nuclei
Source abundances of cosmic ray nuclei from silicon burning process in supernovae
Reames, D. V.↗
Apollo 7 retrofire and reentry of service propulsion module. Further study of Intelsat 2 F-2 apogee burn
Photography of Apollo 7 retrofire and service propulsion module reentry and apogee burn of Intelsat 2 F-2 satellite
Grandfield, M.↗
The investigation of critical pressure burning of fuel droplets Annual report, 1 Jan. - 31 Dec. 1970
Experimental and theoretical results of critical pressure burning of fuel droplets
Allison, C.↗
Burning rate control of solid propellants Patent
Pressurized gas injection for burning rate control of solid propellants
Heidmann, M. F.↗
Space shuttle: Determination of the static stability characteristics of the 0.00285-scale MDAC parallel burn launch configuration
Aerodynamic force and moment coefficient data for parallel burn vehicle launch configurations tested in trisonic wind tunnel for static stability
Blackwell, K. L.↗
Periodic oscillations observed when 365-micron diameter hafnium droplets burn in O2
Hafnium droplets burning in ultrapure oxygen at various pressures, considering combustion induced natural mode periodic oscillations
Cross, C. W., Jr.↗
Termination of shell burning of helium in solar-mass stars
He shell burning termination in solar mass stars evolution to white dwarf stage
Kutter, G. S.↗
Formulating propellants for fully case-bonded end-burning motors
Low modulus solid propellants family for low thrust-to-mass ratio fully case bonded end-burning motors, using polymer network theory for binder formulation
Marsh, H. E., Jr.↗
Fast burning rates in thin film propellants
Fast burning rates in thin film solid composite propellants composed of McCormick-Selph 510, 164 monopropellant, oxidizer and polyvinyl chloride binder
Rodenberger, C. A.↗
Experimental burning rates of single laser- ignited beryllium droplets
Burning rates of single laser ignited beryllium droplets, considering particle size effect
Prentice, J. L.↗
Response of convectively controlled burning to nonlinear disturbances
Dynamic coupling response between convectively controlled burning process and nonsteady flow field with pressure, density and gas velocity periodic variations
Heidmann, M. F.↗
Fuel droplet burning rates in a combustion gas environment
Fuel droplet burning rate variation with ambient temperature and oxygen concentration in combustion gas environment
Faeth, G. M.↗
Preliminary results of large supersonic burning combustor testing.
A hydrogen fueled supersonic-burning combustor 18 in. in diameter, which is equivalent to that of an engine about 6 ft in diameter, was tested as a direct-connected duct at inlet conditions which simulated Mach 8 flight at 115,000 ft alt. A synthetic air consisting of oxygen with 39% nitrogen and 38% water vapor at a total temperature of 4500 deg R and a total pressure of 300 psia was supplied to the combustor inlet by a hydrazine-nitrogen tetroxide hot gas generator which maintained a uniform inlet flow Mach number of 2.8. The large combustor size required a new approach to fuel injector design. Some hydrogen was injected through flush-wall injectors, but most was injected from two rows of swept and tapered struts immersed in the flow stream. Supersonic combustion was obtained at hydrogen equivalence ratios of 0.94 without encountering thermal cho king. Wall static pressures, and the radial distribution of hydrogen, Pitot pressure, and Mach number were determined at the combustor exit.
Metzler, A. J.↗
Oscillatory burning of solid propellants including gas phase time lag.
An analysis has been performed for oscillatory burning of solid propellants including gas phase time lag. The gaseous flame is assumed to be premixed and laminar with a one-step overall chemical reaction. The propellant is assumed to decompose according to the Arrenhius Law, with no condensed phase reaction. With this model, strong gas phase resonance has been found in certain cases at the characteristic gas-phase frequencies, but the peaking of the acoustic admittance is in the direction favoring the damping of pressure waves. At still higher frequencies, moderate wave-amplifying ability was found. The limit of low frequency response obtained previously by Denison and Baum was recovered, and the limitations of the quasi-steady theory were investigated.
T'Ien, J. S.↗