Download or read book Heat Flux and Infrared Spectral Measurements of Burning SRM Propellant Preprint written by and published by . This book was released on 2006 with total page 11 pages. Available in PDF, EPUB and Kindle. Book excerpt: On 23 August 2005 the Air Force Research Laboratory (AFRL) Propulsion Directorate at Edwards AFB conducted an open air burn of over 2000 kg of Titan IV solid rocket motor propellant. Multiple remote sensors were deployed to measure the heat flux and spectral emissions during the burn. The heat flux data was utilized to help determine the hazard classification for the propellant. An average normalized irradiance of 1.62 kW/m2 was obtained during a nominal portion of the burn and supports a classification of 1.4. A Fourier Transform Infrared (FTIR) spectrometer collected data over a spectral range of 1.4 - 14 micrometers. Those data show strong gaseous emissions from carbon dioxide, water, and hydrogen chloride as well as a continuum emission component due to the aluminum oxide particulates.

Download or read book Measurement of Propellant Combustion Response to Sinusoidal Radiant Heat Flux written by J. C. Finlinson and published by . This book was released on 1991 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Improved Techniques for Measuring Thermal Effects of Propellant Burn Tests in Confined Areas written by E. C. Knox and published by . This book was released on 1996 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Measurement of Heat Flux in Solid Propellant Rocketry written by Charles E. Brookley and published by . This book was released on 1963 with total page 49 pages. Available in PDF, EPUB and Kindle. Book excerpt: Internal chamber areas of solid propellant rocket motors are lined with ablative insulation to block the transfer of heat to temperature sensitive case materials. The heat rates to ablative insulators can not be determined by conventional means such as staggering thermocouples through the wall because no workable analytical solution exists for the ablative model. Therefore, it was necessary to measure the heat rates directly by mounting transducers in the ablative wall. A small 5-inch diameter rocket motor was used as the test vehicle for this study, and ablative materials were mounted in the blast tube or in the chamber (peripheral slab) area. Peripheral slabs were subjected to low velocity gas flow calculated to be 50 ft/sec; low velocity flow prevents erosion from affecting the operation of the calorimeters. Because the blast tube has an initial calculated velocity of 870 ft/sec and is therefore subject to extensive erosion, no serious attempt was made to design a heat flux gage for this area. (Author).

Download or read book The Response of a Burning Solid Propellant Surface to Thermal Radiation written by C. Max Mihlfeith and published by . This book was released on 1971 with total page 158 pages. Available in PDF, EPUB and Kindle. Book excerpt: A new technique for the study of processes related to propellant combustion instability has been employed in which burning rate variations produced by a periodic radiant heat flux are measured. The phase angle between the perturbing flux and the burning rate response and the dependence of the magnitude of the response on the driving frequency are obtained. As the frequency of the perturbing flux increases, magnitude of the reaction is observed to first increase and then to pass through a maximum. In general, the experimental results tend to confirm the theoretical models for transient burning rate response, although the observed maximums in the response functions appear to occur at higher frequencies than is predicted by the simpler gas-phase models. (Author).

Download or read book Solid Propellant Combustion Response to Oscillatory Radiant Heat Flux written by L. D. Strand and published by . This book was released on 1989 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Measurement of Heat Flux in Solid Propellant Rocketry written by Charles E. Brookley and published by . This book was released on 1963 with total page 49 pages. Available in PDF, EPUB and Kindle. Book excerpt: Internal chamber areas of solid propellant rocket motors are lined with ablative insulation to block the transfer of heat to temperature sensitive case materials. The heat rates to ablative insulators can not be determined by conventional means such as staggering thermocouples through the wall because no workable analytical solution exists for the ablative model. Therefore, it was necessary to measure the heat rates directly by mounting transducers in the ablative wall. A small 5-inch diameter rocket motor was used as the test vehicle for this study, and ablative materials were mounted in the blast tube or in the chamber (peripheral slab) area. Peripheral slabs were subjected to low velocity gas flow calculated to be 50 ft/sec; low velocity flow prevents erosion from affecting the operation of the calorimeters. Because the blast tube has an initial calculated velocity of 870 ft/sec and is therefore subject to extensive erosion, no serious attempt was made to design a heat flux gage for this area. (Author).

Download or read book Spectroscopic Measurements of the Plume Beneath Counter burning Solid Propellant Flames written by Aren D. Haug and published by . This book was released on 2014 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: A safety analysis of aluminized solid rocket propellant burning at atmospheric pressure is desired. An attempt is made to simulate propellant levitating above a substrate due to the thrust generated by its plume using a motorized support apparatus. This study investigates the temperatures of the plume and burning aluminum droplets with varying substrates, propellant slug diameters, propellant formulations, and gap heights. Two spectrometers were used to collect broadband and narrowband spectral emissions from the plume underneath and immediately adjacent to the propellant-substrate gap. Spectral data were collected as the apparatus passed horizontally through the gap in order to characterize temperatures as a function of flame depth. The broadband spectra were fitted to a linearized Planck's function to estimate gas temperature for several values of emissivity, while the blue-green narrowband spectra were fitted to aluminum monoxide line strength files to calculate the temperature of the burning aluminum. Results indicate the aluminum monoxide flame temperature is generally hotter than the surrounding plume temperature. Calculated temperatures showed a generally flat trend as a function of depth from the center of the plume. Gas temperatures varied wildly and displayed no clear correlation with test variables. Post-test observations indicate that high-temperature chemical reactions within the substrate, phase changes, and the insulating effect of deposited alumina are likely causes for unpredictability.

Download or read book Uncertainties in the Characterization of the Thermal Environment of a Solid Rocket Propellant Fire written by and published by . This book was released on 1993 with total page 6 pages. Available in PDF, EPUB and Kindle. Book excerpt: There has been an interest in developing models capable of predicting the response of systems to Minuteman (MM) III third-stage solid propellant fires. Input parameters for such an effort include the boundary conditions that describe the fire temperature, heat flux, emissivity, and propellant burn rate. In this study scanning spectroscopy and pyrometry were used to infer plume temperatures. Each diagnostic system possessed strengths and weaknesses. The intention was to use various supportive methods to infer plume temperature and emissivity, because no one diagnostic had proven capabilities for determining temperature under these conditions. Furthermore, these diagnostics were being used near the limit of their applicability. All these points created some uncertainty in the data collected.

Download or read book MEASUREMENT OF THE BURNING SURFACE TEMPERATURES OF PROPELLANT COMPOSITIONS BY INFRARED EMISSION written by and published by . This book was released on 1962 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method of determining the burning surface temperatures of solid propellant compositions by measurement of the infrared emission from the surface is described. Specific wavelengths, at which the solid emission is high and the gas emission is low, were selected for the measurements. Very weak fuel/NH4ClO4 powder mixtures, burning at atmospheric pressure, have a constant surface temperature of 495!15 C irrespective of the burning rate. Practical propellant compositions, containing rather more than stoichiometric proportions of fuel with NH4ClO4, give a similar temperature provided that the hot gas emission can be successfully eliminated, but interference from the gas leads to maximum measured temperatures of about 560 C. The average surface temperature of a double-base propellant increases with burning rate; temperatures range from 300 to 400 C at atmospheric pressure. Binder fuels currently used in composite propellants also have surface temperatures close to 500 C when burning in a diffusion flame with oxygen.

Download or read book XX Jornadas de Gen tica Luso Espa olas written by and published by . This book was released on 1984 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Description of Heat Flux Measurement Methods Used in Hydrocarbon and Propellant Fuel Fires at Sandia written by and published by . This book was released on 2010 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: The purpose of this report is to describe the methods commonly used to measure heat flux in fire applications at Sandia National Laboratories in both hydrocarbon (JP-8 jet fuel, diesel fuel, etc.) and propellant fires. Because these environments are very severe, many commercially available heat flux gauges do not survive the test, so alternative methods had to be developed. Specially built sensors include 'calorimeters' that use a temperature measurement to infer heat flux by use of a model (heat balance on the sensing surface) or by using an inverse heat conduction method. These specialty-built sensors are made rugged so they will survive the environment, so are not optimally designed for ease of use or accuracy. Other methods include radiometers, co-axial thermocouples, directional flame thermometers (DFTs), Sandia 'heat flux gauges', transpiration radiometers, and transverse Seebeck coefficient heat flux gauges. Typical applications are described and pros and cons of each method are listed.

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1992 with total page 320 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Combustion of Energetic Materials written by Kenneth K. Kuo and published by Begell House Publishers. This book was released on 2002 with total page 1114 pages. Available in PDF, EPUB and Kindle. Book excerpt: This edited book contains state-of-the-art information associated with energetic material combustion. There are twelve topical areas, including: Reaction Kinetics of Energetic Materials (Solid, Liquid, and Gel Propellants); Recycling of Energetic Materials; Combustion Performance of Hybrid and Solid Rocket Motors; Ignition and Combustion of Energetic Materials; Energetic Material Defects and Rocket Engine Flowfields; Metal Combustion; Pyrolysis and Combustion Processes of New Ingredients and Applications; Theoretical Modeling and Numerical Simulation of Combustion Processes of Energetic Materials; Combustion Diagnostic Techniques; Propellant and Rocket Motor Stability; Commercial Applications of Energetic Materials (Airbags, Gas Generators, etc.); and Thermal Insulation and Ablation Processes.

Download or read book Rocket and Spacecraft Propulsion written by Martin J. L. Turner and published by Springer Science & Business Media. This book was released on 2006-08-29 with total page 344 pages. Available in PDF, EPUB and Kindle. Book excerpt: The revised edition of this practical, hands-on book discusses the launch vehicles in use today throughout the world, and includes the latest details on advanced systems being developed, such as electric and nuclear propulsion. The author covers the fundamentals, from the basic principles of rocket propulsion and vehicle dynamics through the theory and practice of liquid and solid propellant motors, to new and future developments. He provides a serious exposition of the principles and practice of rocket propulsion, from the point of view of the user who is not an engineering specialist.

Download or read book Chemical Rocket Propulsion written by Luigi T. De Luca and published by Springer. This book was released on 2016-08-19 with total page 1069 pages. Available in PDF, EPUB and Kindle. Book excerpt: Developed and expanded from the work presented at the New Energetic Materials and Propulsion Techniques for Space Exploration workshop in June 2014, this book contains new scientific results, up-to-date reviews, and inspiring perspectives in a number of areas related to the energetic aspects of chemical rocket propulsion. This collection covers the entire life of energetic materials from their conceptual formulation to practical manufacturing; it includes coverage of theoretical and experimental ballistics, performance properties, as well as laboratory-scale and full system-scale, handling, hazards, environment, ageing, and disposal. Chemical Rocket Propulsion is a unique work, where a selection of accomplished experts from the pioneering era of space propulsion and current technologists from the most advanced international laboratories discuss the future of chemical rocket propulsion for access to, and exploration of, space. It will be of interest to both postgraduate and final-year undergraduate students in aerospace engineering, and practicing aeronautical engineers and designers, especially those with an interest in propulsion, as well as researchers in energetic materials.

Download or read book Effects on Adjacent Surfaces from the Firing of Rocket Jets written by Walter E. Bressette and published by . This book was released on 1957 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper is a preliminary and brief account of some research currently being conducted to determine the jet effects on adjacent surfaces from the firing of rocket jets. Measurements of jet-effect pressures on a flat plate as well as shadowgraphs are presented that were obtained when a rocket jet at a Mach number of 3 was exhausted downstream and upstream into free-stream flow at a Mach number of 2 located from 2 to 4.7 rocket-jet-exit diameters from the plate. The jet effects on the flat plate with the rocket jet exhausting downstream are of the same order of magnitude as those previously obtained from sonic exits with a total pressure 10 times lower. A maximum pressure coefficient on the plate of 1.35 was obtained when the rocket jet was exhausted upstream at 2 rocket-jet-exit diameters below the plate, and an integration of the measured jet-effect pressures at this position resulted in a normal force on the plate equal to 2.3 times the thrust output of the rocket jet.