Download or read book Arcjet Thruster Research and Technology Phase 2 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-23 with total page 332 pages. Available in PDF, EPUB and Kindle. Book excerpt: The principle objective of Phase 2 was to produce an engineering model N2H4 arcjet system which met typical performance, lifetime, environmental, and interface specifications required to support a 10-year N-S stationkeeping mission for a communications spacecraft. The system includes an N2H4 arcjet thruster, power conditioning unit (PCU), and the interconnecting power cable assembly. This objective was met with the successful conclusion of an extensive system test series. Yano, Steve E. Unspecified Center NASA-CR-182276, E-9332, NAS 1.26:182276, REPT-91-R-1475 NAS3-24631; RTOP 506-42-31...

Download or read book Arcjet Thruster Research and Technology Phase 1 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-25 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: The principal objective of this two phase program is to conduct the development research required to make the low power arcjet a flight ready technology. Many important results were obtained during Phase 1 to move closer to this objective. Fundamental analyses were performed of the arcjet nozzle, the gas kinetic reaction effects, the thermal environment, and the arc stabilizing vortex. These aided the conceptual understanding of the arcjet and guided design work. A hydrazine (N2H4) arcjet was designed that combined a flight qualified catalyst bed with a modular arcjet. Extensive testing was performed which demonstrated the feasibility of using this propellant in an arcjet for the first time. Startup techniques were developed, stability maintained, material compatibility tests conducted, and performance mapping tests performed. Specific impulse values from 400 to 730 seconds were produced with a non-optimized design. These levels are higher than were originally thought possible and proved that extremely high enthalpy values can be obtained with constricted arc technology. Erosion rate data are promising for lifetime extensions to meet flight application requirements. Power control unit (PCU) development was started with the design and fabrication of a laboratory high switching frequency supply. Valuable data were obtained on PCU operation and on the interaction with the dynamic arc. Phase 2 efforts presently underway are resolving key issues for multi-hundred hour lifetimes, are continuing to investigate arcjet/PCU interactions, and will demonstrate duty cycle N2H4 arcjet/PCU operation in a simulated flight mode for lifetimes consistent with initial applications. Unspecified Center NASA-CR-182106, NAS 1.26:182106 NAS3-24631

Download or read book Arcjet Thruster Research and Technology written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-23 with total page 300 pages. Available in PDF, EPUB and Kindle. Book excerpt: The design, analysis, and performance testing of an advanced lower power arcjet is described. A high impedance, vortex stabilized 1-kw class arcjet has been studied. A baseline research thruster has been built and endurance and performance tested. This advanced arcjet has demonstrated long lifetime characteristics, but lower than expected performance. Analysis of the specific design has identified modifications which should improve performance and maintain the long life time shown by the arcjet. Makel, Darby B. and Cann, Gordon L. Unspecified Center NASA-CR-180865, NAS 1.26:180865, RPT/BB0642 NAS3-24842...

Download or read book Reusable Launch Vehicle written by Committee on Reusable Launch Vehicle Technology and Test Program and published by National Academies Press. This book was released on 1996-01-22 with total page 99 pages. Available in PDF, EPUB and Kindle. Book excerpt: The key to opening the use of space to private enterprise and to broader public uses lies in reducing the cost of the transportation to space. More routine, affordable access to space will entail aircraft-like quick turnaround and reliable operations. Currently, the space Shuttle is the only reusable launch vehicle, and even parts of it are expendable while other parts require frequent and extensive refurbishment. NASA's highest priority new activity, the Reusable Launch Vehicle program, is directed toward developing technologies to enable a new generation of space launchers, perhaps but not necessarily with single stage to orbit capability. This book assesses whether the technology development, test and analysis programs in propulsion and materials-related technologies are properly constituted to provide the information required to support a December 1996 decision to build the X-33, a technology demonstrator vehicle; and suggest, as appropriate, necessary changes in these programs to ensure that they will support vehicle feasibility goals.

Download or read book Atmospheric Effects of Chemical Rocket Propulsion written by American Institute of Aeronautics and Astronautics and published by . This book was released on 1991 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Reusable Booster System written by National Research Council and published by National Academies Press. This book was released on 2013-01-10 with total page 115 pages. Available in PDF, EPUB and Kindle. Book excerpt: On June 15, 2011, the Air Force Space Command established a new vision, mission, and set of goals to ensure continued U.S. dominance in space and cyberspace mission areas. Subsequently, and in coordination with the Air Force Research Laboratory, the Space and Missile Systems Center, and the 14th and 24th Air Forces, the Air Force Space Command identified four long-term science and technology (S&T) challenges critical to meeting these goals. One of these challenges is to provide full-spectrum launch capability at dramatically lower cost, and a reusable booster system (RBS) has been proposed as an approach to meet this challenge. The Air Force Space Command asked the Aeronautics and Space Engineering Board of the National Research Council to conduct an independent review and assessment of the RBS concept prior to considering a continuation of RBS-related activities within the Air Force Research Laboratory portfolio and before initiating a more extensive RBS development program. The committee for the Reusable Booster System: Review and Assessment was formed in response to that request and charged with reviewing and assessing the criteria and assumptions used in the current RBS plans, the cost model methodologies used to fame [frame?] the RBS business case, and the technical maturity and development plans of key elements critical to RBS implementation. The committee consisted of experts not connected with current RBS activities who have significant expertise in launch vehicle design and operation, research and technology development and implementation, space system operations, and cost analysis. The committee solicited and received input on the Air Force launch requirements, the baseline RBS concept, cost models and assessment, and technology readiness. The committee also received input from industry associated with RBS concept, industry independent of the RBS concept, and propulsion system providers which is summarized in Reusable Booster System: Review and Assessment.

Download or read book High Pressure Earth Storable Rocket Technology Program Hipes Options 1 2 Report written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-09-19 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: Under the High Pressure Earth Storable Rocket Technology (HIPES) Program, TRW successfully completed testing of two 100 lbf thrust class rhenium chambers using N204-MMH. The first chamber was successfully fired for 4789 seconds of operating time with a maximum duration of 700 seconds. This chamber had been previously fired for 5230 seconds with N2O4-N2H4. The second chamber was successfully fired for 8085 seconds with a maximum firing duration of 1200 seconds. The Isp (specific impulse) for both chambers ranged from 323 lbf-sec/lbm to 330 lbf-sec/lbm.Chazen, M. L. and Sicher, D. and Calvignac, J. and Ono, D.Glenn Research CenterHIGH PRESSURE; THRUST CHAMBERS; ROCKET ENGINE DESIGN; ENGINE TESTS; SPACE STORAGE; METHYLHYDRAZINE; RHENIUM; PINTLES; INJECTORS; SPECIFIC IMPULSE; TEST FIRING

Download or read book Mathematical Theory of Rocket Flight written by Barkley Rosser and published by Budge Press. This book was released on 2008-11 with total page 288 pages. Available in PDF, EPUB and Kindle. Book excerpt: MATHEMATICAL THEORY OF ROCKET FLIGHT BY J. BARKLEY ROSSER, PH. D. Professor of Mathematics at Cornell University Formerly, Chief, Theoretical Ballistics Section Alleyany Ballistics Laboratory ROBERT R. NEWTON, PH. D. Member of Technical Staff, Bell Telephone Laboratories, Inc., Murray Hill, N. J. Formerly, Research Associate Allegany Ballistics Laboratory GEORGE L. GROSS, PH. D. Research Engineer in Applied Mathematics, Grumman Aircraft Engineering Corporation Beth page, N. Y. Formerly, Research Associate A lleyany Ballistics Laboratory Office of Scientific Research and Development National Defense Research Committee NKW YORK AND LONDON MCGRAW-HILL BOOK COMPANY, INC. 1947 MATHEMATICAL THEORY OF ROCKET FLIGHT PRINTED IN THE UNITED STATES OF AMERICA PREFACE This is the official final report to the Office of Scientific Research and Development concerning the work done on the exterior ballistics of fin-stabilized rocket projectiles under the supervision of Section H of Division 3 of the National Defense Research Committee at the Allegany Ballistics Laboratory during 1944 and 1945, when the laboratory was operated by The George Washington University under contract OEMsr-273 with the Office of Scientific Research and Devel opment. As such, its official title is Final Report No. B2.2 of the Allegany Ballistics Laboratory, OSRD 5878. After the removal of secrecy restrictions on this report, a consider able amount of expository material was added. It is our hope that thereby the report has been made readable for anyone interested in the flight of rockets. Two slightly different types of readers are antici pated. One is the trained scientist who has had no previous experience with rockets. Theother is the person with little scientific training who is interested in what makes a rocket go. The first type of reader should be able to comprehend the report in its entirety. For the benefit of the second type of reader, who will wish to skip the more mathematical portions, wo have attempted to supply simple explana tions at the beginnings of most sections telling what is to be accom plished in those sections. It is our hope that a reader can, if so minded, skip most of the mathematics and still be able to form a general idea of rocket flight. Although this is a report of the work done at Allegany Ballistics Laboratory, it must not be supposed that all the material in the report originated there. We have been most fortunate in receiving the whole hearted cooperation and assistance of scientists in other laboratories. Many of them, notably the English scientists, were well advanced in the theory before we even began. Without the fine start given us by these other workers, this report could certainly not have been written. However, we were fortunate enough to discover two means of avoiding certain difficulties of the theory. The first is that of using some dynamical laws especially suited to rockets in deriving the equations of motion, and the second is that of using some mathematical functions especially suited to rockets in solving the equations of motion. The explanation and illustration of these simplifying devices take up a considerable portion of the report, although for completeness we have included material not involving them. vi PREFACE In attempting to acknowledge the contributions of other workers, we are in a difficult position. Approximately a hundred reports by otherworkers were useful in one way or another in the preparatf on of this report. However, most of them are still bound by military secrecy, so that only the few cited in our meager list of bibliographical references can be mentioned here. Many figures are copied from these unmentioiied reports. Sizable portions of our report, such as Chap. II and Appendix 1, lean very heavily on certain of these unmentioned reports, but no specific credit is given...

Download or read book Preludes to U S Space launch Vehicle Technology written by J. D. Hunley and published by . This book was released on 2008 with total page 494 pages. Available in PDF, EPUB and Kindle. Book excerpt: "Preludes to U.S. Space-Launch Vehicle Technology is devoted primarily to military hardware and traces the evolution of missile technology from the 1920s through the 1970s, when the Minuteman III became operational. Hunley discusses individual innovations, technology transfer, management systems, and the organizations that were involved in the research and development of a wide range of rockets and missiles, including the German V-2, Redstone, Atlas, Thor, Jupiter, Titan I and II, and Polaris. He also humanizes the subject through numerous anecdotes and sketches of such fascinating individuals as Robert H. Goddard, Werner von Braun, Bernard Schriever, and "Red" Raborn, among others."--BOOK JACKET.