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Injector Chamber Scaling Evaluation Rocketdyne Injector Development
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Book Synopsis Injector/Chamber Scaling Evaluation Rocketdyne Injector Development by : Mitchell J Fleiszar (Jr)
Download or read book Injector/Chamber Scaling Evaluation Rocketdyne Injector Development written by Mitchell J Fleiszar (Jr) and published by . This book was released on 1970 with total page 93 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes the results of Rocketdyne modular injector development tests conducted. This project will study low cost injectors with a performance goal of 90 percent theoretical vacuum Isp (shifting equilibrium), 250K lbs thrust using N2O4/UDMH propellants, and will evaluate their potential for scalability up to the multi-million lb thrust class. A total of 39 tests were conducted. Several design configurations were evaluated which provided design data for demonstration injector tests scheduled to occur later in this project. A total of four injector and two chamber configurations were tested. Maximum performance obtained was approximately 91 percent of the test site theoretical shifting isp. (91.5 percent vacuum Isp). Dynamic combustion characteristics of this concept were evaluated by artificially inducing plenum chamber pressure overpressures of 100 percent or greater. Also a thermal bomb was detonated within a module to evaluate the combustion stability of a single module and to determine interaction effects upon the other six modules. In all perturbed tests, chamber pressure recovered to within 10 percent of the original value within 15 milliseconds. Although combustion stability rating data was not obtained on the highest performing injector, the basic design from which it was derived is dynamically stable. The candidate injector will be dynamically rated in future tests.
Book Synopsis Injector/Chamber Scaling Evaluation-TRW Injector Development by :
Download or read book Injector/Chamber Scaling Evaluation-TRW Injector Development written by and published by . This book was released on 1969 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes the results of TRW injector development tests. This project, a task under the overall Minimum Cost Design Space Launch Vehicle (MCD/SLV) Program, has as a goal the development of low-cost injectors capable of performing at 90% theoretical Isp (shifting), 250,000-lb thrust using N2O4/UDMH propellants, and will evaluate their scalability up to the multimillion-lb- thrust class. A total of seven injector and three chamber configurations were tested. Maximum performance obtained was approximately 88% of test site theoretical shifting Isp (90% vacuum Isp). Dynamic combustion characteristics of this concept were evaluated by artificially inducing chamber pressure overpressures of 100% or greater. In all tests, chamber pressure recovered to within 10% of the original value within 30 to 40 milliseconds, and the engine is considered dynamically stable.
Download or read book M-1 Injector Development written by and published by . This book was released on 1968 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Injector/Chamber Scaling Evaluation by : Roy A. Silver
Download or read book Injector/Chamber Scaling Evaluation written by Roy A. Silver and published by . This book was released on 1972 with total page 299 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes the results of the testing performed at the Air Force Rocket Propulsion Laboratory. The purpose of this program was to demonstrate the performance, stability, injector/chamber compatibility and long-duration operation of low-cost scalable pressure-fed engines which use storable propellants. Tests were conducted at the 250,000-pound-thrust level with thrust chamber assemblies using two different design approaches: a pintle injector designed by TRW Systems and a modular injector designed by Rocketdyne. Short-duration tests were performed to measure performance, stability and effects of design variation. Long-duration tests were conducted to demonstrate performance, injector/chamber compatibility, and to measure the performance potential of low-cost ablative chambers. The program goals of achieving 90 percent of theoretical specific impulse, 140-second-duration firing and low-cost thrust chamber assemblies were all achieved.
Book Synopsis Injector/Chamber Scaling Feasibility Program. Volume I. Design and Short Duration Testing by : G. A Voorhees (Jr)
Download or read book Injector/Chamber Scaling Feasibility Program. Volume I. Design and Short Duration Testing written by G. A Voorhees (Jr) and published by . This book was released on 1970 with total page 255 pages. Available in PDF, EPUB and Kindle. Book excerpt: A total of forty-one injector development test firings were made using eight injector configurations. Three chamber lengths were evaluated with a single injector configuration. Satisfactory performance was achieved with the longest chamber tested. Injector dynamic stability was demonstrated in numerous stability rating tests. Three demonstration injectors were designed and fabricated and two of these injectors were subjected to checkout firings.
Book Synopsis Injector/Chamber Scaling Evaluation, Facility Checkout by : Michael F. Powell
Download or read book Injector/Chamber Scaling Evaluation, Facility Checkout written by Michael F. Powell and published by . This book was released on 1969 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes the results of the checkout test series conducted at the High Thrust Facility. This project, a task under the overall Minimum Cost Design Launch Vehicle Program, will develop low-cost high-performing injectors at 250,000 pounds thrust using N2O4/UDMH propellants and will evaluate their scalability up to the multimillion-pound-thrust class.
Book Synopsis Notices of Changes in Classification, Distribution and Availability by :
Download or read book Notices of Changes in Classification, Distribution and Availability written by and published by . This book was released on 1977 with total page 436 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Memorandum written by and published by . This book was released on 1966 with total page 442 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Liquid Rocket Engine Combustion Instability by : Vigor Young
Download or read book Liquid Rocket Engine Combustion Instability written by Vigor Young and published by AIAA. This book was released on 1995 with total page 606 pages. Available in PDF, EPUB and Kindle. Book excerpt: Annotation Since the invention of the V-2 rocket during World War II, combustion instabilities have been recognized as one of the most difficult problems in the development of liquid propellant rocket engines. This book is the first published in the United States on the subject since NASA's Liquid Rocket Combustion Instability (NASA SP-194) in 1972. In this book, experts cover four major subject areas: engine phenomenology and case studies, fundamental mechanisms of combustion instability, combustion instability analysis, and engine and component testing. Especially noteworthy is the inclusion of technical information from Russia and China--a first.
Book Synopsis Injector/Chamber Scaling Feasibility Program. Volume II. Ablative Chamber Design and Long Duration Testing by : G. A Voorhees (Jr)
Download or read book Injector/Chamber Scaling Feasibility Program. Volume II. Ablative Chamber Design and Long Duration Testing written by G. A Voorhees (Jr) and published by . This book was released on 1970 with total page 176 pages. Available in PDF, EPUB and Kindle. Book excerpt: Three ablative thrust chambers were designed, fabricated and test fired. Low-cost liner materials were used in three chamber designs; the material selection was based upon subscale test data. Low-cost fabrication techniques were employed throughout. Several fabrication problems with low-cost materials were delineated. Four ablative materials were evaluated in the test program.
Book Synopsis Design of Injectors and Ablative Thrust Chambers for a Flox-propane Rocket Engine with a 1.2-inch Throat Diameter by : Jerry M. Winter
Download or read book Design of Injectors and Ablative Thrust Chambers for a Flox-propane Rocket Engine with a 1.2-inch Throat Diameter written by Jerry M. Winter and published by . This book was released on 1969 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Design and Evaluation of an Oxidant-fuel-ratio-zoned Rocket Injector for High Performance and Ablative Engine Compatibility by : Jerry M. Winter
Download or read book Design and Evaluation of an Oxidant-fuel-ratio-zoned Rocket Injector for High Performance and Ablative Engine Compatibility written by Jerry M. Winter and published by . This book was released on 1972 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Collection of Technical Papers written by and published by . This book was released on 1967 with total page 214 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Note written by and published by . This book was released on 1968 with total page 374 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Progress In Astronautics and Aeronautics by : Mohammed Habiballah
Download or read book Progress In Astronautics and Aeronautics written by Mohammed Habiballah and published by AIAA. This book was released on 2004 with total page 784 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book M-1 Injector Development written by and published by . This book was released on 1968 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis M-1 Injector Development by : Walter F. Dankhoff
Download or read book M-1 Injector Development written by Walter F. Dankhoff and published by . This book was released on 1968 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
