3 edition of Design issues for lunar in situ aluminum/oxygen propellant rocket engines found in the catalog.
Design issues for lunar in situ aluminum/oxygen propellant rocket engines
by National Aeronautics and Space Administration, For sale by the National Technical Information Service in [Washington, DC], [Springfield, Va
Written in English
|Statement||Michael L. Meyer.|
|Series||NASA technical memorandum -- 105433.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
Group IV: Electromagnetic mass drivers for use as interorbital engines, as devices to launch lunar material into space, and as tugs for the retrieval of asteroidal material. Goddard develops centrifugal pumps for rocket engines. Germans test rocket-powered interceptor aircraft Me V-2 rocket fired from Pennemünde enters space during ballistic flight. First operational V-2 launch. V-2 rocket launched to strike London. Arthur C. Clarke proposes geostationary satellites.
A lunar colony could build aluminum-oxygen rockets. The propellant is not as good as the usual stuff but it can be made out of moon rocks. Combined with your idea of using a lunar space elevator, which skips the worst part of using discount rockets, maybe the moon is actually a good place to build probes and satellites. ence issues. The incorporation of once-diverse fields adds strength and additional relevance to geoscience studies. World of Earth Science is a collection of entries on topics covering a diversity of geoscience related interests— from biographies of the pioneers of Earth science to explanations of the latest developments and advances in.
It was thought that the RAIR design could perform two or three times better than the Bussard system, and achieve perhaps 10 or 20 percent of the speed of light. “And, as far as we can tell from the Bruno data,” Sally said, “that Gaijin flower-ship was pretty much a RAIR design: exotic-looking, but nothing we can’t comprehend. Research and Technology /ForewordAs the NASA Center of Excellence for Launchand Payload Processing Systems and launching spacemissions, the John F. Kennedy Space CenterTechnology /ForewordAs the NASA Center of Excellence for Launchand Payload Processing Systems and launching spacemissions, the John F. Kennedy Space Center.
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Meyer. Get this from a library. Design issues for lunar in situ aluminum/oxygen propellant rocket engines. [Michael L Meyer; United States. National Aeronautics and Space Administration.]. Conceptual design of a hybrid rocket engine utilizing lunar-derived propellants Design issues for lunar in situ aluminum/oxygen propellant rocket engines The first scholarly paper above is discussed by Friesen, and suggests two possibilities, a powdered aluminum LOX version, and another that uses aluminum bars bathed in LOX.
Buy Design issues for lunar in situ aluminum/oxygen propellant rocket engines (SuDoc NAS ) by Meyer, Michael L. (ISBN:) from Amazon's Book Store. Everyday low prices and free delivery on eligible : Michael L.
Meyer. This will come as no surprise to long-term students of lunar base proposals. The major reason is that traffic models for lunar base show that by far the largest budget item in mass being moved around between the Earth and Moon is rocket propellant.
Lunar propellant could also be used to launch inter-planetary space flights. Based on the above, I conclude that given an established mining and manufacturing presence on the moon, and giving enough power, an aluminum-oxygen rocket engine might use locally-sourced fuel for jaunting around the moon.
However, I do not expect that this technology could be used to power ships from the moon to other destinations. In this paper it is proposed that not only oxygen but also metals obtained by the reduction of lunar silicates (as well as asteroidal and planetary soils) be used as a rocket propellant.
Metallic aluminum has long been a component of solid rocket propellants, anywhere from 14 to 25% powdered aluminum is commonly used. Production, power, and propulsion technologies for using oxygen and metals derived from lunar resources are discussed. The production process is described, and several of the more developed.
An Aerodynamic Design Study of a Series of Lifting Bodies at Angles of Attack From to 53 Degrees at Mach Numbers from to M. Spearman and Abel Torres. Rocket propellant is the reaction mass of a reaction mass is ejected at the highest achievable velocity from a rocket engine to produce energy required can either come from the propellants themselves, as with a chemical rocket, or from an external source, as with ion engines.
The pasty propellant rocket engine development. NASA Astrophysics Data System (ADS) Kukushkin, V. I.; Ivanchenko, A.
The paper describes a newly developed pasty pro. RP- 1 Rocket Propellant- 1 SRB Solid Rocket Booster T Temperature (K or F) wt% Weight Percent of Fuel Mass 0-wt% RP-1/AI Gelled RP-1 (no metal) Introduction The heat transfer in rocket engines has always been a major design factor due to the extremely high temperature of rocket environments and the limits of existing materials.
Engines using. In Situ Resource-Based Lunar and Martian Habitat Structures Development at NASA/MSFC. NASA Technical Reports Server (NTRS) Bodiford, Melanie P. The most common type of aluminum used in solid propellant formulations is powdered spherical aluminum 5 to 60 mm in diameter and usually constitutes 14% to 20% of the propellant by weight.
The Space Shuttle's Solid Rocket Boosters, for example, contain over million pounds (, kg) of propellant and produce over million pounds ( Both aluminum and oxygen are readily available in the lunar regolith, and such a rocket could easily perform lunar liftoff, lunar landing, or departure from a hypothetical L5 colony for Terra (using a lunar swingby trajectory).
The low specific impulse is more than made up for by the fact that the fuel does not have to be imported from Terra. Meyer M.L. Design Issues for Lunar In Situ Aluminum/Oxygen Propellant Rocket Engines. Aerospace Design Conference, Irvine, California, February21 p.
Meyer M.L., Arrington L.A., Kleinhenz J.E. Testing of a Liquid Oxygen/Liquid Methane Reaction Control Thruster in a New Altitude Rocket Engine Test Facility.
Search the history of over billion web pages on the Internet. Download Citation | Ablation, Flux, and Atmospheric Implications of Meteors Inferred from Stratospheric Aerosol | Single-particle analyses of stratospheric aerosol show that. A Full Burning FSI Simulation of Solid Propellant Rocket Interior.
Han, S. / Kim, C. / Lee, C. / American Institute of Aeronautics Analysis and Design of a Mobile, Actively-Balanced Ballbot for Integration into Human Environments Direct Ignition and S-curve Transition by in situ Nano-Second Pulsed Discharge in Methane/Oxygen/Helium. main TA02 InSpaceProp DRAFT Nov A - Free download as PDF File .pdf), Text File .txt) or read online for free.
Nasa. Lunar Ice Orbitec - Free download as PDF File .pdf), Text File .txt) or read online for free. Plentiful supplies of the raw material for Aluminum-Oxygen and other ISRU-Oxygen rocket fuel. Just add electricity or solar heat to separate the oxygen from the metal. Titanium from Lunar Ilmenite ore.
On Luna a "High titanium basalt" is one with more than 6% titanium by weight, it can go up to 8%.The appealing design the paraffin-based mixture at grain manufacturing process, chemical rockets for in-space propulsion systems, i.e.
liquid the fuel regression rate has is consequently identified with C, by tests performed at an experimental facility was set applications having the rocket engines and solid the highest influence on the a.