Download or read book Measurement of Rocket Nozzle Surface Recession Using Spectrographic Techniques written by Wendell A. Stephen and published by . This book was released on 1972 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this program was to design, analyze, and evaluate experimentally the surface recession of ablative materials using spectrographic techniques. This program was accomplished in two phases. The first phase was the design, analysis, and development of a containment system for the tracer elements. The second phase was the demonstration of the feasibility of that system during static firings in two rocket nozzles, one fabricated from carbon-phenolic and the other from silica-phenolic with a codeposited silicon carbide/pyrolytic- graphite throat insert. Laboratory tests were conducted with a plasma-arc torch to verify the capsule design. The capsules, with thermocouples, were then tested in a solid rocket motor at a pressure of 800 psi with 16%-aluminized polybutadiene-acrylic acid-acrylonitrile propellant. The test results showed poor correlation between the ablation as indicated by thermocouples and that indicated by detection of the tracer salts. This report describes the various program activities from initial tracer selection and configuration selection to final test firing demonstration and analysis of test results. (Author-PL).
Download or read book Measurement of Rocket Nozzle Surface Recession Using Spectrographic Techniques written by Wendell A. Stephen and published by . This book was released on 1972* with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this program was to design, analyze, and evaluate experimentally the surface recession of ablative materials using spectrographic techniques. This program was accomplished in two phases. The first phase was the design, analysis, and development of a containment system for the tracer elements. The second phase was the demonstration of the feasibility of that system during static firings in two rocket nozzles, one fabricated from carbon-phenolic and the other from silica-phenolic with a codeposited silicon carbide/pyrolytic- graphite throat insert. Laboratory tests were conducted with a plasma-arc torch to verify the capsule design. The capsules, with thermocouples, were then tested in a solid rocket motor at a pressure of 800 psi with 16%-aluminized polybutadiene-acrylic acid-acrylonitrile propellant. The test results showed poor correlation between the ablation as indicated by thermocouples and that indicated by detection of the tracer salts. This report describes the various program activities from initial tracer selection and configuration selection to final test firing demonstration and analysis of test results. (Author-PL).
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1973 with total page 1102 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Development of Local Transient Heat Flux Measurements in an Axisymmetric Hybrid Rocket Nozzle written by D'Elia Christopher and published by . This book was released on 2015 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method of performing local transient heat flux measurements in an uncooled axisymmetric hybrid rocket nozzle is presented. Surface temperatures are collected at various axial locations during short duration tests and post processed using finite difference techniques to determine local transient heat fluxes and film coefficients. Comparisons are made between the collected data and the complete Bartz model. Although strong agreement is observed in certain sections of the nozzle, ideal steady state conditions are not observed to entirely validate the Bartz model for hybrid rocket nozzles. An experimental error analysis indicates the experimental heat fluxes are accurate within ±5.2% and supports the accuracy of the results.
Download or read book Government Reports Index written by and published by . This book was released on 1972 with total page 1120 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Unique 3 in 1 Research Development Directory written by and published by . This book was released on 1973 with total page 426 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Near Net Shape Ultra High Melting Recession Resistant Rocket Nozzles II Low Cost Carbon Carbon Technology for Use in Ultra High Temperature Oxidative Environments written by and published by . This book was released on 2003 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Carbon-carbon composites are ideal materials for high temperature structural uses, such as in rocket propulsion components, hypersonic vehicles, and aircraft brakes. In spite of their excellent properties, the use of carbon-carbon composites has been limited because of their high cost and rapid oxidation at elevated temperatures. Two novel approaches to solving these problems are described and these approaches are employed along with a ZrC/W-based nozzle insert to fabricate and test a recession-resistant carbon-carbon rocket nozzle as a potential replacement for solid tungsten nozzles.
Download or read book High Area Ratio Rocket Nozzle at High Combustion Chamber Pressure written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental data were obtained on an optimally contoured nozzle with an area ratio of 1025:1 and on a truncated version of this nozzle with an area ratio of 440:1. The nozzles were tested with gaseous hydrogen and liquid oxygen propellants at combustion chamber pressures of 1800 to 2400 psia and mixture ratios of 3.89 to 6.15. This report compares the experimental performance, heat transfer, and boundary layer total pressure measurements with theoretical predictions of the current Joint Army, Navy, NASA, Air Force (JANNAF) developed methodology. This methodology makes use of the Two-Dimensional Kinetics (TDK) nozzle performance code. Comparisons of the TDK-predicted performance to experimentally attained thrust performance indicated that both the vacuum thrust coefficient and the vacuum specific impulse values were approximately 2.0-percent higher than the turbulent prediction for the 1025:1 configurations, and approximately 0.25-percent higher than the turbulent prediction for the 440:1 configuration. Nozzle wall temperatures were measured on the outside of a thin-walled heat sink nozzle during the test fittings. Nozzle heat fluxes were calculated front the time histories of these temperatures and compared with predictions made with the TDK code. The heat flux values were overpredicted for all cases. The results range from nearly 100 percent at an area ratio of 50 to only approximately 3 percent at an area ratio of 975. Values of the integral of the heat flux as a function of nozzle surface area were also calculated. Comparisons of the experiment with analyses of the heat flux and the heat rate per axial length also show that the experimental values were lower than the predicted value. Three boundary layer rakes mounted on the nozzle exit were used for boundary layer measurements. This arrangement allowed total pressure measurements to be obtained at 14 different distances from the nozzle wall. A comparison of boundary layer total pressure profiles and analytical
Download or read book Measurement of Solid Rocket Propellant Exhaust Gas Temperatures Using Molecular Spectroscopic Methods written by and published by . This book was released on 2014 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Government Reports Announcements written by and published by . This book was released on 1972-10 with total page 1290 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Spectrographic Analysis of Rocket Nozzle Flow written by H. J. Unger and published by . This book was released on 1967 with total page 101 pages. Available in PDF, EPUB and Kindle. Book excerpt: Spectral analysis of the radiation from combustion products of solid propellants in supersonic flow is used to determine the composition and temperature of the gas. The spectrographic equipment and rocket apparatus are described and the experimental results obtained are compared with theory. The flow system examined is that of combustion gases passing through a rocket nozzle where the stagnation temperature and pressure correspond to 2500K and 75 atmospheres. The rapid expansion of the flow in the supersonic part of the nozzle gives rise to non-equilibrium conditions. The spectrometer is used to determine the concentration of one of the active species, CO2, as a function of distance down the nozzle. It is shown that the experimental results agree very closely with the prediction of flow performance based on chemical kinetics. Both emission and absorption spectra were obtained of CO2, CO and H2O in the range from 4 to 6.5 microns. The spectral measurements also enabled the static free-stream temperature of the gas to be determined. (Author).
Download or read book Feasibility Demonstration of a Rocket Engine Ablation Gauge written by Landall W. Harman and published by . This book was released on 1966 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt: The gauging technique employs trace quantities of two radioactive compounds embedded in the nozzle at selected locations. The compounds are selected so that one ablates and the other erodes in the same manner as the adjacent nozzle material. Recession depths are determined by measuring the decrease in radiation intensity external to the nozzle shell. A carbon phenolic MX4926, is the nozzle material used in this program. Equipment was fabricated, assembled, and tested to demonstrate the gauging technique on a rocket engine. Instrumentation and hardware were provided to gauge concurrent erosion and ablation at up to six locations about the rocket nozzle. Recession sensor needles were molded from mascerated carbon fabric and phenolic resin and embedded in the nozzles. Gauging feasibility was demonstrated during engine tests with needles having radiotracer additives.
Download or read book Research and Technology Program Digest written by United States. National Aeronautics and Space Administration and published by . This book was released on with total page 792 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Abstract Bulletin written by and published by . This book was released on 1981 with total page 212 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Technique for the Prediction of Rocket Nozzle Heat Transfer Using the Method of Ambrok written by James P. Huntsinger and published by . This book was released on 1971 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Notices of Changes in Classification Distribution and Availability written by and published by . This book was released on 1987 with total page 428 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Advances in Solid Rocket Nozzle Design and Analysis Technology in the United States Since 1970 written by Joseph H. Hildreth and published by . This book was released on 1988 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt: The design approaches for solid rocket nozzles and the analytical methods used to develop these designs have changed substantially during the past decade. Although nozzle designs have tended to become somewhat more simplified, the demands that the design requirements place on the new nozzle designs force the use of greater analytical complexity. Nozzle designs have progressed toward minimizing the number of parts and reducing the surface erosion as much as possible. The most significant changes have been the incorporation of 3 directional carbon-carbon throats for space and air launch nozzle types, and use of the 2D carbon-carbon involute exit cone in space nozzle designs. The continuing trend for the design of nozzles is to incorporate higher performance materials by part replacement without substantially altering the configuration. The most significant improvement in the analytical techniques is the capacity to effectively model the behavior of the involute exit cone. The current trend in nozzle analysis is to make wider use of nonlinear and 3 dimensional analytical techniques. The work which most needs to be done to improve the nozzle design capabilities is in the area of material technology. We must understand the influences of changes in the raw materials and manufacturing processes on the ultimate performance of the nozzle part.
