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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 379 records · Page 21
All sourcesNASA NTRSDOE OSTI
NASA NTRS1950

Starting of rocket engine at conditions of simulated altitude using crude monoethylaniline and other fuels with mixed acid

Experiments were conducted at sea level and pressure altitude of about 55,000 feet at various temperatures to determine starting characteristics of a commercial rocket engine using crude monoethylaniline and other fuels with mixed acid. With crude monoethylaniline, ignition difficulties were encountered at temperatures below about 20 degrees F. With mixed butyl mercaptans, water-white turpentine, and x-pinene, no starting difficulties were experienced at temperatures as low as minus 74 degrees F. Turpentine and x-pinene, however, sometimes left deposits on the injector face. With blends containing furfuryl alcohol and with other blends, difficulties were experienced either from appreciable deposits or from starting.

COMBUSTION - ROCKET ENGINES↗
NASA NTRS1988

A reusable rocket engine intelligen control

An intelligent control system for reusable space propulsion systems for future launch vehicles is described. The system description includes a framework for the design. The framework consists of an execution level with high-speed control and diagnostics, and a coordination level which marries expert system concepts with traditional control. A comparison is made between air breathing and rocket engine control concepts to assess the relative levels of development and to determine the applicability of air breathing control concepts to future reusable rocket engine systems.

Merrill, Walter C.↗
NASA NTRS1988

A reusable rocket engine intelligent control

An intelligent control system for reusable space propulsion systems for future launch vehicles is described. The system description includes a framework for the design. The framework consists of an execution level with high-speed control and diagnostics, and a coordination level which marries expert system concepts with traditional control. A comparison is made between air breathing and rocket engine control concepts to assess the relative levels of development and to determine the applicability of air breathing control concepts ot future reusable rocket engine systems.

Merrill, Walter C.↗
NASA NTRS2000

Development of Ceramic Matrix Composite Turbine Blisks for Rocket Engines

Ceramic matrix composite (CMC) integrally bladed turbine disks (blisks) are being considered for use in various advanced propulsion systems for space vehicles. The successful development of this technology can significantly impact National Aeronautics and Space Administration (NASA) space transportation missions, by enabling new efficient systems that can operate at higher temperatures, while reducing costs. Composite blisks comprised of carbon (C) fibers and a silicon carbide (SiC) ceramic matrix were designed, fabricated, characterized, and tested by a multidisciplinary team involving materials, design, structural analysis, turbomachinery, and nondestructive evaluation representatives from government, academia, and industry during a 4.5 year effort led by the NASA Marshall Space Flight Center (MSFC). The testing of several of these blisks, which were developed in the Simplex Turbopump CMC Blisk ]Program for use in rocket engine turbopumps, was recently completed. CMC blisks offer potential advantages in rocket engine turbopumps including increased safety resulting from increased operating temperature margins and greater pump reliability, and decreased costs resulting from improved turbopump performance. The progress that was achieved in that development effort is reviewed, and some of the technology that could be applied to other advanced space transportation propulsion systems is discussed.

Effinger, Mike↗
NASA NTRS1998

Technical Challenges for Next Generation Liquid Rocket Engine Nozzles

Next generation launch and propulsion systems face significant challenges of providing increased performance at lower cost with shorter development cycles. The use of existing materials in new application areas and the development and application of "advanced" material systems are enabling for the achievement of these aggressive goals. An area which offers substantial opportunity to decrease liquid rocket engine systems weight, and thus provide a measure of increased performance, is the nozzle. This presentation will examine the technical issues and showstoppers limiting the application of alternate materials to liquid rocket engine nozzles and identify the key material systems which have the potential for high payoff relative to the forcing functions of cost and performance (weight). Existing nozzle material development projects will be cited and opportunities for future joint partnerships to address these materials and processes challenges will be addressed. The presentation will include overviews of activities in low cost ablative nozzles, ceramic matrix composite cooled and uncooled nozzles, and advanced metallics.

Clinton, R. G., Jr.↗
NASA NTRS1968

Rocket engine analog simulation

Mathematical equations simulate the operation of a rocket engine, simulate destructive and nondestructive tests to verify engine design feasibility, and investigate nonlinear variations in engine performance.

Philyaw, B. K.↗
NASA NTRS1973

The future look in rocket engines

The Space Shuttle Main Engine and an Aerospike engine for the Space Tug illustrate the rocket engines of the future. This paper includes a description of design features leading to high performance, long life, and low cost. Computer control of the engine, turnaround maintenance plans, and engine development plans are also discussed.

Sanchini, D. J.↗
NASA NTRS1974

Liquid rocket engine turbopump gears

Design and fabrication of gear drives for rocket engine turbopumps are described in the sequence encountered during the design process as follows: (1) selection of overall arrangement; (2) selection of gear type; (3) preliminary sizing; (4) lubrication system design; (5) detail tooth design; (6) selection of gear materials; and (7) gear fabrication and testing as it affects the design. The description is oriented towards the use of involute spur gears, although reference material for helical gears is also cited.

Source record↗