Download or read book Experimental Investigation of High Burn Rate Propellant for Use in Nozzle less Boosters written by R. Farinaccio and published by . This book was released on 2000 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Nozzleless Booster Performance Study written by and published by . This book was released on 2002 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report concerns a project to develop a solid fuel rocket booster for a rocket ramjet. It describes the development of a high burn rate propellant and the experimental evaluation of a nozzleless booster using this propellant. A propellant formulation was developed which exhibited qualities of high burn rate & good combustion stability with high mass flow necessary to cause exhaust gases to choke downstream in a cylindrical grain. Tests on experimental motors, which showed that the pressure & thrust are dependent on the ratio of the motor's length/diameter ratio, are compared to results obtained using prediction model. Improvements to the model are suggested to take into account erosion effects & non-uniform burn rates along the axial length that affect the overall ballistic performance.
Download or read book Experimental Investigation of the Effect of Aluminum Size and Loading on the Burning Rate of Solid Propellants Under Acceleration written by G. Burton Northam and published by . This book was released on 1969 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of High frequency Longitudinal Combustion Instability in Gaseous Propellant Rocket Motors written by Craig Thomas Bowman and published by . This book was released on 1966 with total page 178 pages. Available in PDF, EPUB and Kindle. Book excerpt: The properties of the longitudinal mode of high-frequency combustion instability in a rocket motor burning premixed gaseous propellants were determined experimentally. The experimental observations were compared with the results of a non-linear instability theory based on a chemical kinetic driving mechanism. It was shown that the theory gives the correct waveform for longitudinal instability. In addition the theory gives the correct qualitative dependence of the stability limits on the mean combustion temperature and activation energy. Harmonic mode longitudinal instabilities were observed. The dependence of the stability limits and instability strength on the mean combustion pressure, combustion chamber length, injector and exhaust nozzle was determined experimentally. Based on the general agreement between the experimental observations and theoretical results it is concluded that the appropriate driving mechanism for high-frequency longitudinal gas-phase combustion instability is chemical kinetics. (Author).
Download or read book An Experimental Investigation of the Droplet Combustion of HAN based Propellants written by Charles J. Call and published by . This book was released on 1988 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of Chemical Reaction Between Propellant Tank Material and Rocket Fuels Or Oxidizers when Impacted by Small High velocity Projectiles written by Robert P. Dengler and published by . This book was released on 1963 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Closed Bomb Combustion of Hivelite Based Very High Burn Rate VHBR Propellant written by E. B. Fisher and published by . This book was released on 1985 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the combustion characteristics of a Hivelite-based, very-high-burn-rate (VHBR) propellant was conducted. The experiments were performed in a closed chamber, called the VHBR bomb, that was specially designed and constructed for these experiments. The device was designed with the same diameter as the propellant samples in order to maintain one dimensional combustion processes and transient wave phenomena to simplify subsequent interpretation and analysis. Propellant combustion was characterized by a low burn rate (about 1 m/s) until a pressure in the vicinity of 15-20 MPa is reached. After this pressure, which may represent the propellant crushing or break pressure, the combustion rate accelerated to levels from 10 to 180 m/s, depending on other test parameters. Tests conducted at different loading densities indicated that combustion rate was a strong function of pressure. Variation of sample weight at constant loading density demonstrated that increasing the amount of unburned propellant at the time the break pressure was reached also causes burn rate and thrust to increase. A coating that makes the outside surface of the sample slippery tended to reduce the apparent burn rate but use of a coating which retarded transmission of gas pressure along the periphery of the sample increased the apparent burn rate as well as thrust. Change of mounting interface properties caused significant differences in the dynamic characteristics leading to increased thrust.
Download or read book Computational and Experimental Investigation on Burning Rate Characteristics for Some Aluminized Solid Propellants in Accelerated Field written by Cao Taiyue and published by . This book was released on 1995 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of Unstable Combustion in Solid Propellant Rocket Motors written by Wilmot Grant Brownlee and published by . This book was released on 1959 with total page 302 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of the Burning Rate of Propellant ANB 3066 Under Oscillatory Pressure and Oscillatory Velocity Conditions written by R. D. Gould and published by . This book was released on 1973 with total page 53 pages. Available in PDF, EPUB and Kindle. Book excerpt: A program of work was conducted in order to measure the effects of oscillatory pressure and velocity at a frequency of 800 Hz upon the burning rate of ANB 3066. The burning rate was measured using a microwave interferometer method and also calculated from the pressure/time records of T-burner and KT-motor firings. An empirical relationship was derived which describes the burning rate under oscillatory and non-oscillatory conditions in terms of the average Mach number, the oscillatory pressure and the mean pressure at the propellant surface. (Author).
Download or read book Experimental Investigation of the Effect of Aluminum Size and Loading on the Burning Rate of Solid Propellants Under Acceleration written by G. Burton Northam and published by . This book was released on 1969 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Studies on Propellant Burn rate Characteristics written by Curtis D. Doyle and published by . This book was released on 2005 with total page 216 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Study of Solid Propellant Combustion Instability written by and published by . This book was released on 2005 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: In this study, experimental investigation of solid propellant combustion instability using an end burning T-Burner setup is performed. For this purpose, a T-Burner setup is designed, analyzed, constructed and tested with all its sub components. T-Burner setup constructed is mainly composed of a base part, a control panel and the T-Burner itself. Combustion chamber, pressure stabilization mechanism, pressurization system, measurement instruments and data acquisition systems form the T-Burner. Pressure stabilization mechanism is utilized in two different alternatives, first of which is by the use of nitrogen gas and a small surge tank with a cavitating venturi. This is a brand new approach for this kind of system. The second alternative is the use of a choked nozzle for pressure stabilization. Resonance frequencies of the system with the two different pressure stabilization mechanisms are experimentally evaluated. Helmholtz frequency of the T-burner constructed is calculated and no Helmholtz instability is observed in the system. Constructed T-Burner setup is operated for a specific solid propellant. System worked successfully and pressure data are obtained. Pressure data revealed oscillatory behaviour. Decay and growth rates of pressure oscillations are used for the calculation of pressure response of the propellant tested. By the use of this T-Burner comparison of the behavior of different propellants can be performed. It can be used as a test device for measuring quantitatively the response of a burning propellant to unsteady motions.
Download or read book Experimental Investigation of Ramburner Performance Part I Liquid Propellant Runs written by R. A. Meese and published by . This book was released on 1972 with total page 177 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes the results of a series of connected-pipe runs with an air-augmented rocket system burning liquid rocket propellants. The liquid propellant runs served to evaluate the behavior of the facility and instrumentation with regard to accuracy and to provide performance data for combustion where the chemical rate processes were relatively fast compared with those of metal combustion. The ramburner was designed to provide axisymmetric, coaxial mixing of the primary and secondary streams in a constant area duct. No mixing aids were employed. Nitrogen tetroxide and Aerozine-50 served as the rocket propellants. The secondary air was preheated by combustion to a nominal temperature of 1100 R to simulate flight stagnation conditions. Runs were made with nominal pressures in the ramburner of 90 and 175 psia. The air/propellant ratio was varied from 5 to 13 (approximately 250 to 600 percent theoretical air). Two oxidizer-to-fuel ratios were employed for the primary rocket: 0.8 (fuel rich) and 2.0 (stoichiometric). Combustion efficiencies between 75 and 90 percent were observed for the complete system, decreasing with increasing air/propellant ratio. Estimated uncertainties in the efficiency values were + or - 3 percent. Ramburner efficiencies tended to be 10 to 15 percent lower and were subject to uncertainties in the neighborhood of + or - 6 percent. A slight decrease in efficiency with decreasing pressure was also observed. (Author).
Download or read book Experimental Study of the Response of Solid Propellant Burning Rate to the Changing of Pressure and the Measurement of Transient Burning Rate written by Zhang Wei and published by . This book was released on 1987 with total page 5 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Some Results of an Analytical and Experimental Investigation to Determine Heat Transfer in the Nozzle of Solid Propellant Rocket Motors written by Ewell Roger Heatherly and published by . This book was released on 1965 with total page 208 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental and Numerical Investigations of Nozzle Geometry Effect on the Instabilities in Solid Propellant Boosters written by J. Anthoine and published by . This book was released on 2000 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
