Photographed on 02/25/2004. -- L2004-47 and L2004-48: R.E. Jeter, E.M. Blount, F.J.L. Bussink, and O. Gomez. L2004-49 through L2004-51: F.J. L. Bussink, J.L. Murdoch, J.L. McNabb, and E.R. Ramiscal. L2004-52: F.J.L. Bussink. L2004-53: E.R. Ramiscal. L2004-54: J.L. McNabb. L2004-55: J.L. Murdoch. L2004-56: K.J. Shelton. L2004-57:C.D. Smith. L2004-58: J.J. Mielnik. L2004-59: K.J. Shelton, J.J. Mielnik, and C.D. Smith. L2004-60: E.M. Blount.
Topic: FLIGHT TESTS. -- SEQUENCING. -- TEST FAC
Photographed on 02/25/2004. -- L2004-47 and L2004-48: R.E. Jeter, E.M. Blount, F.J.L. Bussink, and O. Gomez. L2004-49 through L2004-51: F.J. L. Bussink, J.L. Murdoch, J.L. McNabb, and E.R. Ramiscal. L2004-52: F.J.L. Bussink. L2004-53: E.R. Ramiscal. L2004-54: J.L. McNabb. L2004-55: J.L. Murdoch. L2004-56: K.J. Shelton. L2004-57:C.D. Smith. L2004-58: J.J. Mielnik. L2004-59: K.J. Shelton, J.J. Mielnik, and C.D. Smith. L2004-60: E.M. Blount.
Topic: FLIGHT TESTS. -- SEQUENCING. -- TEST FAC
Photographed on 02/25/2004. -- L2004-47 and L2004-48: R.E. Jeter, E.M. Blount, F.J.L. Bussink, and O. Gomez. L2004-49 through L2004-51: F.J. L. Bussink, J.L. Murdoch, J.L. McNabb, and E.R. Ramiscal. L2004-52: F.J.L. Bussink. L2004-53: E.R. Ramiscal. L2004-54: J.L. McNabb. L2004-55: J.L. Murdoch. L2004-56: K.J. Shelton. L2004-57:C.D. Smith. L2004-58: J.J. Mielnik. L2004-59: K.J. Shelton, J.J. Mielnik, and C.D. Smith. L2004-60: E.M. Blount.
Topic: FLIGHT TESTS. -- SEQUENCING. -- TEST FAC
Photographed on 02/25/2004. -- L2004-47 and L2004-48: R.E. Jeter, E.M. Blount, F.J.L. Bussink, and O. Gomez. L2004-49 through L2004-51: F.J. L. Bussink, J.L. Murdoch, J.L. McNabb, and E.R. Ramiscal. L2004-52: F.J.L. Bussink. L2004-53: E.R. Ramiscal. L2004-54: J.L. McNabb. L2004-55: J.L. Murdoch. L2004-56: K.J. Shelton. L2004-57:C.D. Smith. L2004-58: J.J. Mielnik. L2004-59: K.J. Shelton, J.J. Mielnik, and C.D. Smith. L2004-60: E.M. Blount.
Topic: FLIGHT TESTS. -- SEQUENCING. -- TEST FAC
Photographed on 02/25/2004. -- L2004-47 and L2004-48: R.E. Jeter, E.M. Blount, F.J.L. Bussink, and O. Gomez. L2004-49 through L2004-51: F.J. L. Bussink, J.L. Murdoch, J.L. McNabb, and E.R. Ramiscal. L2004-52: F.J.L. Bussink. L2004-53: E.R. Ramiscal. L2004-54: J.L. McNabb. L2004-55: J.L. Murdoch. L2004-56: K.J. Shelton. L2004-57:C.D. Smith. L2004-58: J.J. Mielnik. L2004-59: K.J. Shelton, J.J. Mielnik, and C.D. Smith. L2004-60: E.M. Blount.
Topic: FLIGHT TESTS. -- SEQUENCING. -- TEST FAC
Photographed on 02/25/2004. -- L2004-47 and L2004-48: R.E. Jeter, E.M. Blount, F.J.L. Bussink, and O. Gomez. L2004-49 through L2004-51: F.J. L. Bussink, J.L. Murdoch, J.L. McNabb, and E.R. Ramiscal. L2004-52: F.J.L. Bussink. L2004-53: E.R. Ramiscal. L2004-54: J.L. McNabb. L2004-55: J.L. Murdoch. L2004-56: K.J. Shelton. L2004-57:C.D. Smith. L2004-58: J.J. Mielnik. L2004-59: K.J. Shelton, J.J. Mielnik, and C.D. Smith. L2004-60: E.M. Blount.
Topic: FLIGHT TESTS. -- SEQUENCING. -- TEST FAC
Photographed on 02/25/2004. -- L2004-47 and L2004-48: R.E. Jeter, E.M. Blount, F.J.L. Bussink, and O. Gomez. L2004-49 through L2004-51: F.J. L. Bussink, J.L. Murdoch, J.L. McNabb, and E.R. Ramiscal. L2004-52: F.J.L. Bussink. L2004-53: E.R. Ramiscal. L2004-54: J.L. McNabb. L2004-55: J.L. Murdoch. L2004-56: K.J. Shelton. L2004-57:C.D. Smith. L2004-58: J.J. Mielnik. L2004-59: K.J. Shelton, J.J. Mielnik, and C.D. Smith. L2004-60: E.M. Blount.
Topic: FLIGHT TESTS. -- SEQUENCING. -- TEST FAC
Photographed on 02/25/2004. -- L2004-47 and L2004-48: R.E. Jeter, E.M. Blount, F.J.L. Bussink, and O. Gomez. L2004-49 through L2004-51: F.J. L. Bussink, J.L. Murdoch, J.L. McNabb, and E.R. Ramiscal. L2004-52: F.J.L. Bussink. L2004-53: E.R. Ramiscal. L2004-54: J.L. McNabb. L2004-55: J.L. Murdoch. L2004-56: K.J. Shelton. L2004-57:C.D. Smith. L2004-58: J.J. Mielnik. L2004-59: K.J. Shelton, J.J. Mielnik, and C.D. Smith. L2004-60: E.M. Blount.
Topic: FLIGHT TESTS. -- SEQUENCING. -- TEST FAC
Photographed on 02/25/2004. -- L2004-47 and L2004-48: R.E. Jeter, E.M. Blount, F.J.L. Bussink, and O. Gomez. L2004-49 through L2004-51: F.J. L. Bussink, J.L. Murdoch, J.L. McNabb, and E.R. Ramiscal. L2004-52: F.J.L. Bussink. L2004-53: E.R. Ramiscal. L2004-54: J.L. McNabb. L2004-55: J.L. Murdoch. L2004-56: K.J. Shelton. L2004-57:C.D. Smith. L2004-58: J.J. Mielnik. L2004-59: K.J. Shelton, J.J. Mielnik, and C.D. Smith. L2004-60: E.M. Blount.
Topic: FLIGHT TESTS. -- SEQUENCING. -- TEST FAC
Photographed on 02/25/2004. -- L2004-47 and L2004-48: R.E. Jeter, E.M. Blount, F.J.L. Bussink, and O. Gomez. L2004-49 through L2004-51: F.J. L. Bussink, J.L. Murdoch, J.L. McNabb, and E.R. Ramiscal. L2004-52: F.J.L. Bussink. L2004-53: E.R. Ramiscal. L2004-54: J.L. McNabb. L2004-55: J.L. Murdoch. L2004-56: K.J. Shelton. L2004-57:C.D. Smith. L2004-58: J.J. Mielnik. L2004-59: K.J. Shelton, J.J. Mielnik, and C.D. Smith. L2004-60: E.M. Blount.
Topic: FLIGHT TESTS. -- SEQUENCING. -- TEST FAC
Photographed on 02/25/2004. -- L2004-47 and L2004-48: R.E. Jeter, E.M. Blount, F.J.L. Bussink, and O. Gomez. L2004-49 through L2004-51: F.J. L. Bussink, J.L. Murdoch, J.L. McNabb, and E.R. Ramiscal. L2004-52: F.J.L. Bussink. L2004-53: E.R. Ramiscal. L2004-54: J.L. McNabb. L2004-55: J.L. Murdoch. L2004-56: K.J. Shelton. L2004-57:C.D. Smith. L2004-58: J.J. Mielnik. L2004-59: K.J. Shelton, J.J. Mielnik, and C.D. Smith. L2004-60: E.M. Blount.
Topic: FLIGHT TESTS. -- SEQUENCING. -- TEST FAC
Photographed on 02/25/2004. -- L2004-47 and L2004-48: R.E. Jeter, E.M. Blount, F.J.L. Bussink, and O. Gomez. L2004-49 through L2004-51: F.J. L. Bussink, J.L. Murdoch, J.L. McNabb, and E.R. Ramiscal. L2004-52: F.J.L. Bussink. L2004-53: E.R. Ramiscal. L2004-54: J.L. McNabb. L2004-55: J.L. Murdoch. L2004-56: K.J. Shelton. L2004-57:C.D. Smith. L2004-58: J.J. Mielnik. L2004-59: K.J. Shelton, J.J. Mielnik, and C.D. Smith. L2004-60: E.M. Blount.
Topic: FLIGHT TESTS. -- SEQUENCING. -- TEST FAC
Photographed on 02/25/2004. -- L2004-47 and L2004-48: R.E. Jeter, E.M. Blount, F.J.L. Bussink, and O. Gomez. L2004-49 through L2004-51: F.J. L. Bussink, J.L. Murdoch, J.L. McNabb, and E.R. Ramiscal. L2004-52: F.J.L. Bussink. L2004-53: E.R. Ramiscal. L2004-54: J.L. McNabb. L2004-55: J.L. Murdoch. L2004-56: K.J. Shelton. L2004-57:C.D. Smith. L2004-58: J.J. Mielnik. L2004-59: K.J. Shelton, J.J. Mielnik, and C.D. Smith. L2004-60: E.M. Blount.
Topic: FLIGHT TESTS. -- SEQUENCING. -- TEST FAC
Photographed on 02/25/2004. -- L2004-47 and L2004-48: R.E. Jeter, E.M. Blount, F.J.L. Bussink, and O. Gomez. L2004-49 through L2004-51: F.J. L. Bussink, J.L. Murdoch, J.L. McNabb, and E.R. Ramiscal. L2004-52: F.J.L. Bussink. L2004-53: E.R. Ramiscal. L2004-54: J.L. McNabb. L2004-55: J.L. Murdoch. L2004-56: K.J. Shelton. L2004-57:C.D. Smith. L2004-58: J.J. Mielnik. L2004-59: K.J. Shelton, J.J. Mielnik, and C.D. Smith. L2004-60: E.M. Blount.
Topic: FLIGHT TESTS. -- SEQUENCING. -- TEST FAC
321
321
May 21, 2011
05/11
by
Thompson, F
texts
eye 321
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comment 0
Various methods of measuring the air speed of airplanes are described. Particular emphasis is placed on the procedure required to obtain precise measurements of speed by the use of the suspended Pitot-static head or the suspended static head. Typical calibration curves for service installations of Pitot-static heads are shown and the relation between errors in air speed and corresponding errors in observed altitude for such installations is discussed. There is included a brief discussion of...
Topic: AIRPLANES - HANDLEY PAGE TORPEDO FLIGHT TESTS (BRIT )
The Department of Aeronautics and Astronautics at the Naval Postgraduate School (NPS) is conducting a research program in methods of higher harmonic control (HHC) for reduction of helicopter vibrations. The program at NPS uses remotely piloted helicopters (RPH) to study HHC effects on vibration and blade load reduction. The scope of this master's thesis was to measure the baseline vibration profile of the RPH test vehicles prior to the installation of a HHC system. This goal was met by the...
Topics: HHC, RPH, Vibrations, Flight Tests, Ground Tests
20,816
21K
Mar 8, 2010
03/10
by
NASA eClips
movies
eye 20,816
favorite 1
comment 0
Learn how NASA engineers are paving the way to new aeronautical breakthroughs and helping to make the future of flying safer and greener.
Topics: NASA, eClips, NIA, BWB, x-48, flight tests
725
725
May 31, 2011
05/11
by
Mitcheltree, R. A.; Braun, R. D.; Hughes. S. J.; Simonsen, L. C
texts
eye 725
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comment 0
The driving requirement for design of a Mars Sample return mission is assuring containment of the returned samples. The impact of this requirement on developmental costs, mass allocation, and design approach of the Earth Entry Vehicle is significant. A simple Earth entry vehicle is described which can meet these requirements and safely transport the Mars Sample Return mission's sample through the Earth's atmosphere to a recoverable location on the surface. Detailed analysis and test are...
Topics: HISTORIES, RESEARCH, PROBLEM SOLVING, FLIGHT TESTS, SUPERSONIC FLIGHT
214
214
May 27, 2011
05/11
by
MONAKHOV, N. M
texts
eye 214
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A METHOD IS PRESENTED FOR THE THEORETICAL DETERMINATION OF THE CIRCULATION OF A LARGE SPAN SWEPT WING USING LIFTING SURFACE THEORY. BY SOLUTION OF AN INTEGRAL EQUATION, EXPRESSIONS ARE DERIVED FOR THE INTENSITY OF THE WING VORTEX LAYER ALONG AND AT RIGHT ANGLES TO THE FLOW. THE RESULTS ARE COMPARED WITH THOSE OF THE SIMPLER BUT NONRIGOROUS ''THREE-QUARTER CHORD'' METHOD OF DETERMINING THE CIRCULATION. USE OF THE LATTER METHOD IS SHOWN TO BE JUSTIFIED FOR SWEPT WINGS OF LARGE SPAN.
Topics: SOUNDING ROCKETS, FUEL SYSTEMS, FLIGHT TESTS, PAYLOADS, ROCKETS
167
167
May 21, 2011
05/11
by
NON
texts
eye 167
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comment 0
The experiments herein described were made for the purpose of finding whether removing a larger portion of the wing to improve the pilot's view would be possible, without too great detriment to the aerodynamic properties of the airplane. The experiments were conducted on a wing similar to the Fokker F III.
Topics: AIRPLANES - FREE TEST FLIGHTS, FLIGHT TESTS, STABILITY, LONGITUDINAL
260
260
Jun 11, 2011
06/11
by
Chu, Paul C. W
texts
eye 260
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comment 0
The research at Houston was focused on optimizing the design of superconducting magnets for advanced adiabatic demagnetization refrigerators (ADRs), assessing the feasibility of using high temperature superconducting (HTS) magnets in ADRs in the future, and developing techniques to deposit HTS thin and thick films on high strength, low thermal conductivity substrates for HTS magnet leads. Several approaches have been tested for the suggested superconducting magnets.
Topics: AIR BREATHING ENGINES, HYPERSONIC VEHICLES, FLIGHT TESTS, HYPERSONICS, INDUSTRIES
219
219
Jun 2, 2011
06/11
by
Pueschel, Rudolf F.; Ferry, Guy V.; Strawa, Anthony W
texts
eye 219
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comment 0
The observed existence of soot aerosol at 20-kilometer (km) altitude (which arguably is generated by aircraft flying in corridors at 10 - 12 km) requires a transport mechanism in a thermally stable stratosphere that is different from isentropic or dynamic mixing. Such a mechanism could be provided by gravito-photophoresis, induced by the incidence of sunlight on strongly absorbing fractal soot particles. This particle absorptivity, in conjunction with uneven surface-coating of sulfuric acid and...
Topics: FLIGHT TESTS, AERODYNAMIC STALLING, HELICOPTERS, STIFFNESS, ROTARY WING AIRCRAFT
301
301
Jul 5, 2010
07/10
by
Fournier, R. H.; Morgan, J. R
texts
eye 301
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comment 0
No Abstract Available
Topics: FUEL SYSTEMS, LIQUID HYDROGEN, RELIABILITY, TURBOJET ENGINES, FLIGHT TESTS
227
227
May 31, 2011
05/11
by
Xu, J.; Stanescu, D.; Hussaini, M. Y.; Farassat, F
texts
eye 227
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comment 0
The paper presents a comparison of experimental noise data measured in flight on a two-engine business jet aircraft with Kulite microphones placed on the suction surface of the wing with computational results. Both a time-domain discontinuous Galerkin spectral method and a frequency-domain spectral element method are used to simulate the radiation of the dominant spinning mode from the engine and its reflection and scattering by the fuselage and the wing. Both methods are implemented in...
Topics: AIRCRAFT MANEUVERS, AIRCRAFT MAINTENANCE, FAULT DETECTION, VIBRATION, FLIGHT TESTS
378
378
May 21, 2011
05/11
by
Reynolds, Thaine W; Ebersole, Earl
texts
eye 378
favorite 0
comment 0
No Abstract Available
Topics: ICE FORMATION, METEOROLOGY - CLOUDS, METEOROLOGY - RAIN, ICE PREVENTION - HEATING, ICE PREVENTION -...
459
459
Jun 20, 2010
06/10
by
Anoshchenko, N. D
texts
eye 459
favorite 0
comment 0
Rocket engine technology, rocket planes, rocket propelled gliders, and seaplanes - history
Topics: GLIDERS, HISTORIES, ROCKET ENGINES, ROCKET PLANES, SEAPLANES, FLIGHT TESTS, GRAVITATION
The equipment and techniques are described which are to be used in a project aimed at measuring oscillating air forces and dynamic aeroelastic response of a swept wing airplane at high subsonic speeds. Electro-hydraulic inertia type shakers installed in the wing tips will excite various elastic airplane modes while the related oscillating chordwise pressures at two spanwise wing stations and the wing mode shapes are recorded on magnetic tape. The data reduction technique, following the...
Topics: NASA Technical Reports Server (NTRS), FLIGHT TESTS, FLUTTER, MILITARY AIRCRAFT, AEROELASTICITY,...
231
231
May 30, 2011
05/11
by
Elbuluk, Malik E.; Hammond, Ahmad; Gerber, Scott; Patterson, Richard L.; Overton, Eri
texts
eye 231
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comment 0
In this paper, two second-generation high power density DC/DC converter modules have been evaluated at low operating temperatures. The power rating of one converter (Module 1) was specified at 150 W with an input voltage range of 36 to 75 V and output voltage of 12 V. The other converter (Module 2) was specified at 100 W with the same input voltage range and an output voltage of 3.3 V. The converter modules were evaluated in terms of their performance as a function of operating temperature in...
Topics: VIBRATION ISOLATORS, ISOLATION, MICROGRAVITY, LEVITATION, FLIGHT TESTS, ACCELERATION, EARTH ORBITAL...
134
134
Jun 2, 2011
06/11
by
Ackerman, Andre
texts
eye 134
favorite 0
comment 0
The effects of aerosols on cloud albedos contributes the single greatest uncertainty in estimates of global radiative forcing since preindustrial times. A dramatic example of these effects is provided by ship tracks, which are long, linear regions of enhanced cloud reflectivity that sometimes form downwind of ships. Previously, ship tracks and a number of other topics in the area of aerosol-cloud interactions have been investigated with a one-dimensional numerical model, which is composed of...
Topics: SHARP LEADING EDGES, REENTRY VEHICLES, DRAG, FLIGHT TESTS, NOSE TIPS, THERMOCOUPLES
208
208
Jun 12, 2011
06/11
by
Bowman, Cheryl L.; Ritzert, Frank J.; Smialek, James L.; Jaster, Mark L.; rker, Samuel P
texts
eye 208
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Proposed concepts for an ambitious mission to explore Jupiter's three icy moons place significant demands on the various spacecraft systems. There are many challenges related to the high output power conversion systems being considered, and one example is the need to ensure system compatibility at all levels. The utilization of appropriate materials for component structures is important to ensuring long mission life. Refractory metal alloys have attractive high-temperature properties in inert...
Topics: FLIGHT TESTS, SYSTEMS INTEGRATION, ENHANCED VISION, PREVENTION, COMMERCIAL AIRCRAFT, AIRPORTS,...
309
309
Jun 3, 2011
06/11
by
Shin, Jong-Yeo
texts
eye 309
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comment 0
In a fault tolerant control (FTC) system, a parameter varying FTC law is reconfigured based on fault parameters estimated by fault detection and isolation (FDI) modules. FDI modules require some time to detect fault occurrences in aero-vehicle dynamics. This paper illustrates analysis of a FTC system based on estimated fault parameter transient behavior which may include false fault detections during a short time interval. Using Lyapunov function analysis, the upper bound of an induced-L2 norm...
Topics: X-38 CREW RETURN VEHICLE, RESCUE OPERATIONS, REENTRY, FLIGHT TESTS, ELECTROMECHANICS
220
220
Jul 9, 2010
07/10
by
Lezberg, E. A
texts
eye 220
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comment 0
Calculations of exhaust emissions from a scramjet powered hypersonic transport burning hydrogen fuel were performed over a range of Mach numbers of 5 to 12 to provide input data for wake mixing calculations and forecasts of future levels of pollutants in the stratosphere. The calculations were performed utilizing a one-dimensional chemical kinetics computer program for the combustor and exhaust nozzle of a fixed geometry dual-mode scramjet engine. Inlet conditions to the combustor and engine...
Topics: FLIGHT SIMULATORS, FLIGHT TESTS, SHORT TAKEOFF AIRCRAFT, AIRCRAFT LANDING, ATTITUDE CONTROL
286
286
Jul 5, 2010
07/10
by
Rakich, J. V
texts
eye 286
favorite 0
comment 0
No Abstract Available
Topics: AIRCRAFT MODELS, FLIGHT TESTS, VERTICAL TAKEOFF AIRCRAFT, MILITARY AIRCRAFT, SUPERSONIC SPEED
846
846
Jul 11, 2010
07/10
by
NON
texts
eye 846
favorite 0
comment 0
No Abstract Available
Topics: MERCURY SPACECRAFT, SPACECRAFT CONFIGURATIONS, FLIGHT TESTS, LAUNCH VEHICLES, SPECIFICATIONS,...
337
337
May 29, 2011
05/11
by
Irwin, Keit
texts
eye 337
favorite 0
comment 0
The current preliminary design tools lack the product performance, quality and cost prediction fidelity required to design Six Sigma products. They are also frequently incompatible with the tools used in detailed design, leading to a great deal of rework and lost or discarded data in the transition from preliminary to detailed design. Thus, enhanced preliminary design tools are needed in order to produce adequate financial returns to the business. To achieve this goal, GEAE has focused on...
Topics: INSTRUMENT APPROACH, GLOBAL POSITIONING SYSTEM, FLIGHT TESTS, COLLISIONS, AIRPORTS, SPACING,...
351
351
Jul 11, 2010
07/10
by
NON
texts
eye 351
favorite 0
comment 0
No Abstract Available
Topics: BOUNDARY LAYER TRANSITION, FLIGHT TESTS, SUPERSONIC SPEED, HEAT TRANSFER, SUBLIMATION,...
297
297
May 31, 2011
05/11
by
Harik, V. M.; Gates, T. S.; Nemeth, M. P
texts
eye 297
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Validity of the assumptions relating the applicability of continuum shell theories to the global mechanical behavior of carbon nanotubes is examined. The present study focuses on providing a basis that can be used to qualitatively assess the appropriateness of continuum-shell models for nanotubes. To address the effect of nanotube structure on their deformation, all nanotube geometries are divided into four major classes that require distinct models. Criteria for the applicability of continuum...
Topics: FLIGHT TESTS, FUEL FLOW, DRAG, AUTONOMY, FORMATION FLYING, TRANSONIC SPEED, MACH NUMBER
449
449
Jul 11, 2010
07/10
by
Mckenzie, R. L
texts
eye 449
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A semiclassical collision model is applied to the study of energy transfer rates between a vibrationally excited diatomic molecule and a structureless atom. The molecule is modeled as an anharmonic oscillator with a multitude of dynamically coupled vibrational states. Three main aspects in the prediction of vibrational energy transfer rates are considered. The applicability of the semiclassical model to an anharmonic oscillator is first evaluated for collinear encounters. Second, the collinear...
Topics: FLIGHT TESTS, HIGH ALTITUDE, PARACHUTES, VIKING LANDER SPACECRAFT, NASA PROGRAMS, PERFORMANCE,...
An ongoing joint NASA/Army program to study the effects of ice accretion on unprotected helicopter rotor aerodynamic performance is discussed. This program integrates flight testing, wind tunnel testing, and analytical modeling. Results are discussed for helicopter flight testing in the Canadian NRC hover spray rig facility to measure rotor aero performance degradation and document rotor ice accretion characteristics. The results of dry wind tunnel testing of airfoil sections with artificial...
Topics: NASA Technical Reports Server (NTRS), FLIGHT TESTS, HELICOPTERS, ICE FORMATION, ROTOR AERODYNAMICS,...
273
273
May 30, 2011
05/11
by
Reynolds, Gregory A
texts
eye 273
favorite 0
comment 0
Aerodynamic noise sources become important when propulsion noise is relatively low, as during aircraft landing. Under these conditions, aerodynamic noise from high-lift systems can be significant. The research program and accomplishments described here are directed toward reduction of this aerodynamic noise. Progress toward this objective include correction of flow quality in the Low Turbulence Water Channel flow facility, development of a test model and traversing mechanism, and improvement of...
Topics: FLIGHT TESTS, TRAJECTORY MEASUREMENT, TRAJECTORIES, FILTRATION, GLOBAL POSITIONING SYSTEM, SENSORS,...
240
240
Jul 11, 2010
07/10
by
Todd, P
texts
eye 240
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Plant and certain animal embryos appear to be responsive to the gravity vector during early stages of development. The convection of particle sedimentation as the basis for the sensing of gravity is investigated using the cells of wheat seedlings, amphibian embryos, and mammals. Exploration of the mammalian cell for sedimenting particles reveals that their existence is unlikely, especially in the presence of a network of microtubules and microfilaments considered to be responsible for...
Topics: DIGITAL SYSTEMS, MULTIPLEXING, DATA ACQUISITION, ENVIRONMENTAL TESTS, FLIGHT TESTS, PULSE CODE...
In the late 1960s, efforts to advance the state-of-the-art in rotor systems technology indicated a significant gap existed between our ability to accurately predict the characteristics of a complex rotor system and the results obtained through flight verification. Even full scale wind tunnel efforts proved inaccurate because of the complex nature of a rotating, maneuvering rotor system. The key element missing, which prevented significant advances, was our inability to precisely measure the...
Topics: NASA Technical Reports Server (NTRS), FLIGHT TESTS, ROTOR SYSTEMS RESEARCH AIRCRAFT, ROTORS, WIND...
251
251
May 30, 2011
05/11
by
Soriano, J. Francisco; Coquilla, Rachael V.; Wilson, Gregory R.; Seiff, Alvin; Rivell, Toma
texts
eye 251
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The primary focus of this study was to determine the accuracy of the Mars Pathfinder lander local pressure readings in accordance with the actual ambient atmospheric pressures of Mars during parachute descent. In order to obtain good measurements, the plane of the lander pressure sensor opening should ideally be situated so that it is parallel to the freestream. However, due to two unfavorable conditions, the sensor was positioned in locations where correction factors are required. One of these...
Topics: FLIGHT CONTROL, FLIGHT SAFETY, PILOT INDUCED OSCILLATION, FLIGHT TESTS, SIMULATION, CONFERENCES,...
267
267
Jun 3, 2011
06/11
by
Nachtsheim, Philip R
texts
eye 267
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comment 0
This paper describes a method to solve a system of N linear equations in N steps. A quadratic form is developed involving the sum of the squares of the residuals of the equations. Equating the quadratic form to a constant yields a surface which is an ellipsoid. For different constants, a family of similar ellipsoids can be generated. Starting at an arbitrary point an orthogonal basis is constructed and the center of the family of similar ellipsoids is found in this basis by a sequence of...
Topics: AERODYNAMIC LOADS, ROTARY WING AIRCRAFT, FLIGHT TESTS, FLIGHT CONDITIONS, LOADS (FORCES), DATA BASES
232
232
Jul 26, 2010
07/10
by
Herr, Joel L
texts
eye 232
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The NASA Charging Analyzer Program (NASCAP) computer code is a three dimensional finite element charging code designed to analyze spacecraft charging in the magnetosphere. Because of the characteristics of this problem, NASCAP can use an quasi-static approach to provide a spacecraft designer with an understanding of how a specific spacecraft will interact with a geomagnetic substorm. The results of the simulation can help designers evaluate the probability and location of arc discharges of...
Topics: EURECA (ESA), FLIGHT TESTS, GRAVITY GRADIOMETERS, MAGNETOMETERS, SPACEBORNE EXPERIMENTS,...
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225
Jun 9, 2011
06/11
by
Fischer, Karen E.; Rock, Kenneth E
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The level of nitric oxide contamination in the test gas of the NASA Langley Research Center Arc-Heated Scramjet Test Facility and the effect of the contamination on scramjet test engine performance were investigated analytically. The study was conducted for standard facility conditions corresponding to Mach 6, 7, and 8 flight simulations. The analytically determined levels of nitric oxide produced in the facility are compared with experimentally measured levels. Results of the analysis indicate...
Topics: NONLINEAR SYSTEMS, AERODYNAMIC STABILITY, SYSTEMS ENGINEERING, STABILITY TESTS, GENERAL AVIATION...
The Data Analysis Plan (DAP) describes the data analysis that the C3 Work Package (WP) will perform in support of the Access 5 Step 1 C3 flight demonstration objectives as well as the processes that will be used by the Flight IPT to gather and distribute the data collected to satisfy those objectives. In addition to C3 requirements, this document will encompass some Human Systems Interface (HSI) requirements in performing the C3 flight demonstrations. The C3 DAP will be used as the primary...
Topics: NASA Technical Reports Server (NTRS), FLIGHT PLANS, FLIGHT TESTS, AIRSPACE, ORGANIZATIONS, DATA...
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354
Jun 1, 2011
06/11
by
Tam, C. K. W.; Ju, H.; Jones, M. G.; Watson, W. R.; Parrott, T. L
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Computational and experimental studies are carried out to offer validation of the results obtained from direct numerical simulation (DNS) of the flow and acoustic fields of slit resonators. The test cases include slits with 90-degree corners and slits with 45-degree bevel angle housed inside an acoustic impedance tube. Three slit widths are used. Six frequencies from 0.5 to 3.0 kHz are chosen. Good agreement is found between computed and measured reflection factors. In addition, incident sound...
Topics: BLUFF BODIES, WINDSHIELDS, FLIGHT TESTS, AERODYNAMIC DRAG, NOSE CONES, SUPERSONIC SPEED,...
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282
Jun 21, 2010
06/10
by
Baber, H. T., Jr.; Moul, M. T
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No Abstract Available
Topics: AIRCRAFT CONFIGURATIONS, DRAG MEASUREMENT, TRANSONIC FLIGHT, FLIGHT TESTS, ROCKET FLIGHT, TRANSONIC...
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379
Sep 20, 2010
09/10
by
NON
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The Space Station Freedom Furnace (SSFF) Project is divided into two phases: phase 1, a definition study phase, and phase 2, a design and development phase. TBE was awarded a research study entitled, 'Space Station Furnace Facility Requirements Definition and Conceptual Design Study' on June 2, 1989. This report addresses the definition study phase only. Phase 2 is to be complete after completion of phase 1. The contract encompassed a requirements definition study and culminated in...
Topics: COMPOSITE MATERIALS, MISSION PLANNING, REUSABLE LAUNCH VEHICLES, THERMAL PROTECTION, FLIGHT TESTS,...
