Download or read book Rocket nozzle Testing and Evaluation written by E. W. Ungar and published by . This book was released on 1960 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Nuclear Thermal Rocket Nozzle Testing and Evaluation Program written by and published by . This book was released on 1993 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Development and Evaluation of PG SiC Codeposited Coatings for Rocket Nozzle Inserts Volume I Insert Test and Evaluation in High Performance Propellant Environments written by Cedric Bielawski and published by . This book was released on 1974 with total page 141 pages. Available in PDF, EPUB and Kindle. Book excerpt: Seven 1.7-inch throat diameter rocket nozzles were test fired in the HIPPO high pressure facilities at Edwards Air Force Base using three different solid propellants. Three 1.0-inch and two 2.0-inch throat diameter rocket nozzles were test fired at Atlantic Research Corporation using three different gel propellants. All of the throat inserts and most of the entrance sections were coated with PG/SiC. The erosion rates of all of the coated inserts tested in this program are plotted in Figures 49 and 50 as functions of pressure with temperature and level of gas oxidizing species indicated. No delaminations occurred. Some cracking of the inserts occurred but this did not interfere with the attainment of erosion data. (Modified author abstract).
Download or read book Rocket Testing and Evaluation in Ground Facilities written by John H. Povolny and published by . This book was released on 1968 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Evaluation of Rocket Nozzle Passive Temperature Indicators Test Nozzle No 2 written by John R. Ellison and published by . This book was released on 1969 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this test was to demonstrate a technique for measuring subsurface nozzle material temperatures beyond the range of conventional thermocouples. The objective was achieved by designing and fabricating a 2.3-inch-throat-diameter solid rocket nozzle and instrumenting it with high-temperature indicators, the evaluation and selection of propellant ballistic properties to obtain 6500 degrees F flame temperature, 810-psig maximum chamber pressure, 21.9-sec effective firing duration, and posttest evaluation of the rocket nozzle including X-ray analysis and sectioning. (Author).
Download or read book NOZZLE EVALUATION written by THIOKOL CHEMICAL CORP HUNTSVILLE ALA. and published by . This book was released on 1964 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: This quarterly report describes progress made during the period 22 June through 21 September 1963 on the program to evaluate experimental rocket motor nozzles produced under the Army Materials Research Agency Program. During this period, the Army Missile Command 29amicom0 delivered to Thiokol Chemical Corporation one Atlantic Research 2-in. pyrolytic graphite coated nozzle insert and two titanium boronitride Calorobic 1-in. nozzle inserts, numbered HTB-3 B 109 and HTD-3 A 7, respectively. AMICOM has approved the use of the TX-24 motor to test the 1-in. nozzles at chamber pressures of 700 psi or lower. The TX-338 test motor will be used for testing 1- or 2-inch nozzle inserts at chamber pressures exceeding 700 psi. Two test plans, A and B, were submitted by Thiokol to AMICOM for AMRA's consideration. Test Plan A was a comprehensive plan which included pretest and posttest evaluations of the nozzle insert. Test Plan B was submitted basically as a go-no-go tye test in which the insert would be shipped to Watertown Arsenal for evaluation after the test. (Author).
Download or read book Evaluation of Coated Columbium Test Panels Having Application to a Secondary Nozzle Extension for the Rl10 Rocket Engine System Parts 1 and 2 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-18 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt: The activity performed on the screening and evaluation of various coatings for application on columbium alloy test panels representative of a radiation-cooled nozzle extension for the RL10 rocket engine is summarized. Vendors and processes of candidate coatings were evaluated. Post engine test evaluations of the two selected coatings are discussed. Murphy, Kenneth S. and Castro, Joaquin H. Unspecified Center COATINGS; NIOBIUM ALLOYS; PERFORMANCE TESTS; ROCKET ENGINES; MICROSTRUCTURE; NOZZLE DESIGN; PANELS...
Download or read book U Integral Rocket ramjet Component Evaluation Test Program written by C. E. Franklin and published by . This book was released on 1973 with total page 642 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Evaluation of Short duration Rocket Engine Technique for Base Heat Testing with External Airflow written by John G Dawson (Jr) and published by . This book was released on 1966 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt: Base recirculation data were obtained on a 5.47-%-scale model of the Saturn 1-Block 2 booster at trajectory Mach numbers of 1.16 and 1.63. The rocket nozzle flow was produced by use of the short-duration combustor. The turbine exhaust gases were simulated by hydrogen. The test objectives were (1) to compare results obtained by the short-duration technique to those obtained by long-duration test methods and (2) to evaluate the operational advantages of the short-duration method as compared to other techniques. A comparison of model test to flight test data is also presented.
Download or read book Experimental Evaluation of Several Ablative Materials as Nozzle Sections of a Storable Propellant Rocket Engine written by Carl L. Meyer and published by . This book was released on 1966 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report evaluates twenty-two ablative-material samples as nozzle sections of a storable-propellant (nitrogen textroxide and a 50-50 percent blend of unsymmetrical dimethylhydrazine with hydrazine) rocket engine to determine general trends among the material variables and to enable comparison of such trends with those observed from similar tests with a hydrogen-oxygen rocket engine reported in NASA TN D-3258.
Download or read book Experimental Evaluation of Heat Transfer on a 1030 1 Area Ratio Rocket Nozzle written by Kenneth J. Kacynski and published by . This book was released on 1987 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Development and Evaluation of PG SiC Codeposited Coatings for Rocket Nozzle Inserts Volume II Thermostructural Analyses of Selected Nozzle Test Firings written by James W. Murray and published by . This book was released on 1974 with total page 387 pages. Available in PDF, EPUB and Kindle. Book excerpt: Phase 2-Tasks 3 and 4 - Non-linear (elastic-plastic) thermostructural analyses were performed for seven PG/SiC codeposited inserts subjected to actual solid rocket test environments. A failure criteria for multiaxial stress fields and orthotropic material strengths was identified and used to predict failure of success of the inserts. A comparison of analytical predictions and actual test results in good correlation. Hence, a baseline was established from which a rational approach to designing codeposited inserts can be developed in the future. (Author).
Download or read book Integral Rocket ramjet Component Evaluation Test Program U written by C. E. Franklin and published by . This book was released on 1975 with total page 174 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Evaluation of Low cost Materials and Manufacturing Processes for Large Solid Rocket Nozzles Analysis of Performance Nozzle 11 written by J. J. Warga and published by . This book was released on 1967 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report is the first of a series describing the results of static test firings conducted to verify the performance of ablative nozzle components fabricated from low-cost materials and/or low-cost manufacturing processes. The nozzle test configuration and the temperature measurement system is described and a comparison is drawn between predicted and actual performance of the ablative plastics utilized in each nozzle component.
Download or read book Plasma Torch Testing for Thermostructural Evaluation of Rocket Motor Nozzle Materials written by Andrew S. Prince 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 Experimental Evaluation of Heat Transfer on a 1030 1 Area Ratio Rocket Nozzle written by Kenneth J. Kacynski and published by . This book was released on 1987 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Development and Evaluation of PG SiC Codeposited Coatings for Rocket Nozzle Inserts Volume III Subscale Rocket Motor Testing of PG SiC Lined Throat Inserts written by Cedric Bielawski and published by . This book was released on 1973 with total page 45 pages. Available in PDF, EPUB and Kindle. Book excerpt: Six ATJ graphite 1.0-inch throat diameter nozzle throat inserts and four entrance approach sections were coated with PG/SiC and test fired with a low oxidizing 21 percent aluminum 5600F propellant. A preliminary throat erosion rate for PG/SiC of four mils per second at 2000 psia and seven mils per second at 2500 psia average chamber premere was established. Use of a graded coating in which the last third of the deposit was pure pyrographite approximately halved the erosion rate. The inserts appeared to be less prone to cracking when the ATJ substrates had been heat treated at 5400F prior to coating. (Author).
