Performance assessment of a Space Station rescue and personnel/logistics vehicle
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Naftel, J. Chris↗
Engineering topics
Talay, Theodore A.
Publications and source records attributed to Talay, Theodore A..
Advanced manned launch system comparisons
Studies of Advanced Manned Launch Systems (AMLS) at the NASA Langley Research Center are examining all-rocket and air-breathing/rocket options for the next-generation U.S. manned space transportation system. Under review are vehicle concepts that have a goal of reliable, safe, cost-effective manned access to space beyond the year 2000. Technology levels, system complexities, and operations approaches are shown to be factors which significantly affect comparisons of the various concepts. Low life-cycle cost and low cost per flight are considered to be major discriminators in selecting a launch system to satisfy future needs.
Piland, William M.↗
Advanced manned launch systems
Advanced Manned Launch Systems (AMLS) studies underway at the NASA Langley Research Center are described. The AMLS studies have focused on investigating mission needs and identifying technologies, operational requirements, and life-cycle costs. Two-stage vertical take off rocket vehicles with significant levels of reusability are shown to be cost effective for moderate to high flight rates. All-hydrogen fuel vehicles are preferred over methane boosted systems for both operational and cost considerations. Drawings of possible AMLS design solutions are presented. Fully reusable, partially resusable, expendable stage and horizontal take off airbreather/rocket solutions are compared.
Talay, Theodore A.↗
Advanced Manned Launch Systems
Advanced Manned Launch Systems (AMLS) studies underway at the NASA Langley Research Center are part of a broader effort examining options for the next U.S. manned space transportation system. AMLS study phases have focused on investigating mission needs and identifying technologies and technology levels, concepts, systems, operational requirements, and life-cycle costs. For near-term technologies and an operations-oriented approach, two-stage vertical-takeoff rocket vehicles with significant levels of reusability are shown to be cost-effective for moderate to high flight rates. All-hydrogen fuel vehicles are also preferred over methane boosted systems from both operational and cost considerations.
Talay, Theodore A.↗
Advanced manned launch system (AMLS) review
The current status of NASA's AMLS conceptual studies, part of a broader effort aimed at determining options for the next manned space transportation system, is reported. The primary goal of the studies is to identify means for lowering the cost of manned access to space while fulfilling mission needs. Vehicle systems, technologies, and operations factors affecting launch costs, mission success, and safety are identified. Emphasis is placed on partially and fully reusable launch concepts that employ an operations-oriented design approach.
Talay, Theodore A.↗
Design of Long-Endurance Unmanned Airplanes Incorporating Solar and Fuel Cell Propulsion
Preliminary performance analysis and conceptual design are described for a class of unmanned airplanes possessing multi-day endurance capability. A mixed-mode electric power system incorporates solar cells for daytime energy production and a non-regenerative H2-02 fuel cell to supply energy for night flight. The power system provides energy for all onboard systems, including propulsion., payload, and avionics. Excess solar energy is available during significant portions of the day, and may be used for climbing, maneuvering, or payload functions. By jettisoning fuel cell reactant product (water) during flight, vehicle endurance may be increased under certain conditions. Empirical structure sizing algorithms are combined with low-Reynolds number aerodynamics algorithms to estimate airplane size and geometry to meet prescribed mission requirements. Initial calculations for summertime, high-altitude flight (above 40,000 ft (12 km)) at moderate latitude (31 deg N) indicate that mission endurance of several days may be possible for configurations having wing loadings on the order of 0.9 to 1.3 lb/ft(exp 2). These aircraft tend to be somewhat smaller than solar-powered aircraft previously conceived for multi-month endurance utilizing regenerative fuel cell systems for night flight.
Youngblood, James W.↗
The Effects of Parachute System Mass and Suspension-Line Elastic Properties on the LADT #3 Viking Parachute Inflation Load
Analytical calculations have considered the effects of 1) varying parachute system mass, 2) suspension-line damping, and 3) alternate suspension-line force-elongation data on the canopy force history. Results indicate the canopy force on the LADT #3 parachute did not substantially exceed the recorded vehicle force reading and that the above factors can have significant effects on the canopy force history. Analytical calculations have considered the effects of i) varying parachute system mass, 2) suspension line damping, and 3) different suspension-line force-elongation data on the canopy force history. Based on the results of this study the following conclusions are drawn: Specifically, 1. At the LADT #3 failure time of 1.70 seconds, the canopy force ranged anywhere from 15.7% below to 2.4% above the vehicle force depending upon the model and data used. Therefore, the canopy force did not substantially exceed the recorded vehicle force reading. 2. At a predicted full inflation time of 1.80 seconds the canopy force would be greater than the vehicle force by from 1.1% to 10.6%, again depending upon the model and data used. Generally, 3. At low altitudes, enclosed and apparent air mass can significantly effect the canopy force calculated and should, therefore, not be neglected. 4. The canopy force calculations are sensitive to decelerator physical properties. In this case changes in the damping and/or force-elongation characteristics produced significant changes in the canopy force histories. Accurate prediction of canopy force histories requires accurate inputs in these areas.
Talay, Theodore A.↗
The Effect of Suspension-Line Length on Viking Parachute Inflation Loads
Analytical calculations have considered the effect on maximum load of increasing the suspension-line length on the Viking parachute. Results indicate that unfurling time is increased to 1.85 seconds from 1.45 seconds, and that maximum loads are increased approximately 5 percent with an uncertainty of -4 percent to +3 percent.
Talay, Theodore A.↗