Evaluation of hydraulic fluids for use in advanced supersonic aircraft
Pumpability, lubricability, and durability of five hydraulic fluids at varying inlet temperatures to evaluate applicability for supersonic aircraft
Damasco, F.↗
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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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Non-contacting dynamic seals for space power alternators.
SNAP 8 alternator noncontacting dynamic seal systems design and tests, obtaining durability and leakage rates comparable to mechanical face seals
Mcgrew, J. M.↗
Engines for manned spacecraft.
Apollo propulsion systems design and development emphasizing performance, thrust chamber durability, combustion stability and leakage
Yodzis, C. W.↗
High-pressure seals for rotary shafts
High pressure seals for rotating shafts are machined from a polyimide resin. It is more durable and cheaper than the older seals of plastic coated metal and works at temperatures between - 400 degrees and plus 900 degrees f.
Holden, C. P.↗
Development of an Advanced Annular Combustor
The objective of the effort described in this report was to determine the structural durability of a full-scale advanced annular turbojet combustor using ASTM A-1 type fuel and operating at conditions typical of advanced supersonic aircraft. A full-scale annular combustor of the ram-induction type was fabricated and subjected to a 325-hour cyclic endurance test at conditions representative of operation in a Mach 3.0 aircraft. The combustor exhibited extensive cracking and scoop burning at the end of the test program. But these defects had no appreciable effect on combustor performance, as performance remained at a high level throughout the endurance program. Most performance goals were achieved with pressure loss values near 6% and 8%, and temperature rise variation ratio (deltaTVR) values near 1.25 and l.22 at takeoff and cruise conditions, respectively. Combustion efficiencies approached l004 and the exit radial temperature profiles were approximately as desired.
Rusnak, J. P.↗
High expansion coefficient glasses can be sealed to common metals
New series of high expansion coefficient glasses can be sealed by fusion onto hot surfaces of metals and alloys. Glasses have relatively low working temperatures, good chemical durability, and can be used in electrical insulators and feedthroughs to fluid or vacuum systems.
Camp, F. E.↗
Extravehicular space suit thermal insulations
Space suit thermal insulation properties, wear durability and nonflammability improvements, reflecting techniques in fabricating cryogenic multilayer insulation systems
French, B.↗
New materials for manned spacecraft, aircraft, and other applications
Fireproof nonmetallic materials for spacecraft and aircraft, discussing functional utility, durability and aesthetic requirements relative to environmental conditions
Radnofsky, M. I.↗
Automated endurance testing of a Brayton power conversion system
Computer controlled durability test of 50,000 hour life Brayton power conversion system for space applications
Edkin, R. E.↗
Compact 30 kW circulating helium capsule for fuel element tests in NASA Plum Brook reactor
In pile and out of pile durability tests and characteristics of 30 kW circulating helium fuel capsules in Plum Brook Reactor
Finnegan, P. M.↗
Shuttle-safety - Some representative problems
Space shuttle safety, discussing rocket engine durability, turbine life, flaw detection, radiation hazards, etc
Pinkel, I. I.↗
High-temperature ceramic-to-ceramic seals
Noble-metal braze applied to appropriately prepared zirconia parts produces a gas-tight, durable seal that can withstand temperature of 825 C for over 2000 hours without deterioration.
Smart, W.↗
Water purification by reverse osmosis using heterocyclic polymer membranes
Pyrrone (polyimidazopyrrolone) polymers are a new class of thermally stable, radiation and chemical resistant aromatic-heterocyclic polymers featuring a greater chemical and mechanical durability than cellulose acetate.
Scott, H.↗
A survey of Kaufman thruster cathodes
A survey is presented of the various cathodes which were developed and used in the Kaufman ion thruster. The electron bombardment type ion source is briefly described. The general design, operating characteristics, and power requirements are shown for each type of cathode from the refractory metals used in 1960 to the plasma discharge hollow cathodes of today. A detailed discussion of the hollow cathode is given, including starting and cyclic operating characteristics as well as more fundamental design parameters. Tests to date show that the plasma hollow cathode is an efficient electron source with demonstrated durability over 10,000 hours.
Weigand, A. J.↗
Development and evaluation of vacuum pressure gauge components from carbon and graphite
A prototype all carbon triode ultrahigh vacuum gage was fabricated and tested. The gage exhibited a sensitivity of 3.7 per torr for nitrogen and an X-ray background approximately 0.1 as large as would be expected of a metal gage of the same design. The gage made from these materials, showed good sensitivity and durability. A practical technique was developed for bonding carbon components together without metal fasteners. The bond is made with a cross-linked phenolic resin which is converted to vitreous carbon by a careful pyrolysis procedure. The resulting bonds are strong, electrically conductive, and can withstand repeated excursions to 2500 K in vacuum. Measurements of adsorption and outgassing characteristics of four refractory carbons have confirmed that such materials are suitable for use in ultrahigh vacuum and that some are superior refractory metals in man respects.
Benson, D. K.↗
Space storable propellant performance program coaxial injector characterization
An experimental program was conducted to characterize the circular coaxial injector concept for application with the space-storable gas/liquid propellant combination FLOX(82.6% F2)/CH4(g) at high pressure. The primary goal of the program was to obtain high characteristic velocity efficiency in conjunction with acceptable injector/chamber compatibility. A series of subscale (single element) cold flow and hot fire experiments was employed to establish design criteria for a 3000-lbf (sea level) engine operating at 500 psia. The subscale experiments characterized both high performance core elements and peripheral elements with enhanced injector/chamber compatibility. The full-scale injector which evolved from the study demonstrated a performance level of 99 percent of the theoretical shifting characteristic exhaust velocity with low chamber heat flux levels. A 44-second-duration firing demonstrated the durability of the injector. Parametric data are presented that are applicable for the design of circular, coaxial injectors that operate with injection dynamics (fuel and oxidizer velocity, etc.) similar to those employed in the work reported.
Burick, R. J.↗
A survey of Kaufman thruster cathodes.
A survey is presented of various cathodes which have been developed and used in the Kaufman ion thruster. The electron-bombardment type ion source used in the thruster is briefly described. The general design, operating characteristics, and power requirements are shown for each type of cathode from the refractory metals used in 1960 to the plasma discharge hollow cathodes of today. A detailed discussion of the hollow cathode is given describing starting and cyclic operating characteristics as well as more fundamental design parameters. Tests to date show that the plasma hollow cathode is an efficient electron source with demonstrated durability over 10,000 hours and should offer further performance and life improvements.
Weigand, A. J.↗
The space shuttle and its uses.
The development of reusable space-shuttle vehicles has been made practical by the availability of improved staged-combustion engines and durable thermal protection systems. A two-state launch configuration with fully reusable booster and orbiter elements is considered to be the best design solution, and size specifications for such a vehicle are examined as a function of launch costs. Significant vehicle characteristics are explained in terms of cargo bay dimensions, cross-range maneuvering capability, mission duration requirements, engine characteristics, and acceleration constraints. Shuttle flight activities include satellite deployment and repair, sortie missions for short-duration research purposes, and space station support operations. Phases of the development program are outlined, and structural details of several candidate space shuttle concepts are illustrated.
Mathews, C. W.↗