An experimental investigation of two visual methods of altitude determination
Visual techniques for astronaut determination of spacecraft altitude
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Visual techniques for astronaut determination of spacecraft altitude
Low gravity simulation by high altitude drop test and with short drag shield
Simulated altitude performance of full scale, high temperature turbojet engine using pentaborane and HEF-2 fuel
Integrated circuit control and timing system of high altitude rocket radar
Metabolic reaction of deer mice to temperature and altitude, analyzing various enzyme systems
High altitude balloon top collections of cosmic dust shows evidence of absence of crystal structure in particles
High altitude effect on work capacity, discussing bicycle ergometer test results on physiological response of human subjects
High altitude parachute systems test techniques for analysis of inflation, stability variations porosity, effects at low dynamic pressure, etc
High altitude hypersonic viscous flow degradation of L/D effects on entry vehicle lateral range capability
Cardiac output of young and old men at rest and working at altitude of 3,800 m. during first week
Prophylaxis of oxygen deprivation in rats at simulated high altitude using phenformin HCl
This paper discusses the design, execution, and results of NEAR's low altitude operations at Eros.
Exchange between the upper tropical troposphere and the lower troposphere is considered by examining high altitude aircraft observations of water, ozone, methane, wind and temperature for scale invariance.
This paper describes some design aspects of the reflector antenna system for the High altitude MMIC sounding radiometer (HAMSR) on a remotely piloted aircraft.
A method is described for the empirical determination of altitude-range resolutions of ozone profiles obtained by differential absorption lidar (DIAL) analysis.
Dawn has successfully completed its orbital mission at Vesta and is currently en route to an orbital rendezvous with Ceres in 2015. The longest duration and most complex portion of the Vesta departure trajectory was the transfer from the low to high altitude science orbit. This paper describes the design of this low-thrust trajectory optimized assuming a minimum-propellant mass objective. The transfer utilized solar-electric ion propulsion applied over 139 spacecraft revolutions about Vesta. Science drivers, operational constraints, and robustness to statistical uncertainties are addressed. The 45-day transfer trajectory was successfully implemented in early 2012.
An analytical formula for solving the speed profile that accrues minimum cost during an aircraft descent with a constrained altitude profile is derived. The optimal speed profile first reaches a certain speed, called the minimum-cost speed, as quickly as possible using an appropriate extreme value of thrust. The speed profile then stays on the minimum-cost speed as long as possible, before switching to an extreme value of thrust for the rest of the descent. The formula is applied to an actual arrival route and its sensitivity to winds and airlines' business objectives is analyzed.
The National Aeronautics and Space Administration conducted a full scale ice crystal icing turbofan engine test in the NASA Glenn Research Centers Propulsion Systems Laboratory (PSL) Facility in February 2013. Honeywell Engines supplied the test article, an obsolete, unmodified Lycoming ALF502-R5 turbofan engine serial number LF01 that experienced an un-commanded loss of thrust event while operating at certain high altitude ice crystal icing conditions. These known conditions were duplicated in the PSL for this testing.