Add to ORKGThis work was conducted to define further the effects of propellant composition variables on the acceleration-induced burning rate augmentation of solid propellants. The rate augmentation at a given acceleration was found to be a nonlinear inverse function of the reference burning rate and not controlled by binder or catalyst type at a given reference rate. A nonaluminized propellant and a low rate double-base propellant exhibited strong transient rate augmentation due to surface pitting resulting from the retention of hot particles on the propellant surface
Thermal properties and chemical kinetics of solid phase in combustion process of ammonium perchlorat...
This paper considers the extensive data and correlations on the erosive burning of solid propellants...
Alumina size distributions were obtained for both a coarse and a fine oxidizer composite propellant ...
Instantaneous burning rate data for a polybutadiene acrylic acid propellant, containing 16 weight pe...
The average burning rates of composite solid rocket propellant were measured in acceleration field...
The functional dependence of acceleration-induced burning-rate augmentation on the magnitude and ori...
Aluminum size and loading effects on burning rate of centrifugal accelerated solid propellant
Instantaneous burning rate data for a polybutadiene acrylic acid propellant, containing 16 weight pe...
Acceleration effects on aluminized composite solid propellants combustion by high speed color cinema...
WOS: 000325647000093The burning rate of the solid rocket propellants is one of the most important fa...
Two different independent variable forms, a difference form and a ratio form, were investigated for ...
Pressure and velocity coupling effects on combustion stability in solid propellant burnin
The paper presents a physical-mathematical model for metallized solid propellant combustion under ac...
17 USC 105 interim-entered record; under review.The article of record as published may be found at h...
This item was digitized from a paper original and/or a microfilm copy. If you need higher-resolution...
Thermal properties and chemical kinetics of solid phase in combustion process of ammonium perchlorat...
This paper considers the extensive data and correlations on the erosive burning of solid propellants...
Alumina size distributions were obtained for both a coarse and a fine oxidizer composite propellant ...
Instantaneous burning rate data for a polybutadiene acrylic acid propellant, containing 16 weight pe...
The average burning rates of composite solid rocket propellant were measured in acceleration field...
The functional dependence of acceleration-induced burning-rate augmentation on the magnitude and ori...
Aluminum size and loading effects on burning rate of centrifugal accelerated solid propellant
Instantaneous burning rate data for a polybutadiene acrylic acid propellant, containing 16 weight pe...
Acceleration effects on aluminized composite solid propellants combustion by high speed color cinema...
WOS: 000325647000093The burning rate of the solid rocket propellants is one of the most important fa...
Two different independent variable forms, a difference form and a ratio form, were investigated for ...
Pressure and velocity coupling effects on combustion stability in solid propellant burnin
The paper presents a physical-mathematical model for metallized solid propellant combustion under ac...
17 USC 105 interim-entered record; under review.The article of record as published may be found at h...
This item was digitized from a paper original and/or a microfilm copy. If you need higher-resolution...
Thermal properties and chemical kinetics of solid phase in combustion process of ammonium perchlorat...
This paper considers the extensive data and correlations on the erosive burning of solid propellants...
Alumina size distributions were obtained for both a coarse and a fine oxidizer composite propellant ...