Re: The 100/10/1 Rule.
- From: Pat Flannery <flanner@xxxxxxxxxx>
- Date: Sat, 10 Mar 2007 14:37:46 -0600
Pat Flannery wrote:
Now that's odd... those were supposed to be these:
There were two NASA studies on it, but neither of them are on the web:
http://tinyurl.com/2243lo
http://tinyurl.com/263dkc
Title: Application of dual-fuel propulsion to a single stage AMLS vehicle
Author(s): Lepsch, Roger A., Jr.; Stanley, Douglas O.; Unal, Resit
Abstract: As part of NASA's Advanced Manned Launch System (AMLS) study to determine a follow-on, or complement, to the Space Shuttle, a reusable single-stage-to-orbit concept utilizing dual-fuel rocket propulsion has been examined. Several dual-fuel propulsion concepts were investigated. These include a separate engine concept combining Russian RD-170 kerosene-fueled engines with SSME-derivative engines the kerosene and hydrogen-fueled Russian RD-701 engine concept and a dual-fuel, dual-expander engine concept. Analysis to determine vehicle weight and size characteristics was performed using conceptual level design techniques. A response surface methodology for multidisciplinary design was utilized to optimize the dual-fuel vehicle concepts with respect to several important propulsion system and vehicle design parameters in order to achieve minimum empty weight. Comparisons were then made with a hydrogen-fueled reference, single-stage vehicle. The tools and methods employed in the analysis process are also summarized.
NASA Center: Langley Research Center
Publication Date: Jun 1, 1993
Document Source: Other Sources
No Digital Version Available: Go to Tips On Ordering
Document ID: 19930066069
Accession ID: 93A50066
Report Number: AIAA PAPER 93-2275
Meeting Information: 29th; AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit; June 28-30, 1993; Monterey, CA; United States
Keywords: HYDROGEN KEROSENE PROPULSION SYSTEM CONFIGURATIONS REUSABLE ROCKET ENGINES SINGLE STAGE ROCKET VEHICLES SINGLE STAGE TO ORBIT VEHICLES OPTIMIZATION PERFORMANCE PREDICTION
Notes: AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit, 29th, Monterey, CA, June 28-30, 1993
Accessibility: Unclassified; Copyright; Unlimited; Publicly available;
Updated/Added to NTRS: 2004-11-03
Title: Thermo-Kinetics Characterization of Kerosene RP-1 Combustion for Tri-Propellant Engine Design Calculations
Author(s): Wang, Ten-See
Abstract: A one-formula surrogate fuel C12H24 and its quasi-global kinetics have been developed to support the conceptual design of the injectors and thrust chambers of the tri-propellant engines. This surrogate fuel represents a fuel blend that properly depicts the physical and chemical properties of kerosene RP-l. The accompanying thermodynamics for the substitute fuel is generated and is anchored with the heat of formation of kerosene RP-1. The surrogate fuel model and its thermodynamics are verified by comparing a series of one dimensional rocket thrust chamber shifting-equilibrium calculations under a kerosene-fueled Russian Engine (RD-170) operating conditions. The models are then tested in conjunction with a computational fluid dynamics formulation to predicting the thermo-flowfield of two single-element shear tri-axial injectors a gaseous oxygen kerosene Hydrogen injector and a liquid oxygen liquid kerosene gaseous hydrogen injector. The mixture ratio of those injectors is that of a proposed tri-propellant engine RD-704. Reasonable flame structure is predicted for those injectors.
NASA Center: NASA (non Center Specific)
Publication Date: Oct. 1995
Document Source: CPIA, 10630 Little Patuxent Pkwy., Suite 202, Columbia, MD 21044-3264
No Digital Version Available: Go to Tips On Ordering
Document ID: 19960026197
Accession ID: 96N27925
Keywords: ENGINE DESIGN THRUST CHAMBERS ROCKET THRUST COMPUTATIONAL FLUID DYNAMICS THERMODYNAMICS PREDICTIONS LIQUID OXYGEN LIQUID HYDROGEN KINETICS KEROSENE HEAT OF FORMATION CHEMICAL PROPERTIES
Accessibility: Unclassified; No Copyright; Unlimited; Publicly available;
Updated/Added to NTRS: 2005-10-10
Pat
.
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