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  • Launch Vehicles and Launch Operations  (22)
  • MECHANICAL ENGINEERING  (20)
  • 2005-2009  (22)
  • 1990-1994  (20)
  • 1
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    Constellation Launch Vehicles Overview (2009)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This slide presentation reviews the current status of the launch vehicles associated with the Constellation Program. These are the Ares I and the Ares V. An overview of the Ares launch vehicles is included. The presentation stresses that the major criteria for the Ares I launcher is the safety of the crew, and the presentation reviews the various features that are designed to assure that aim. The Ares I vehicle is being built on a foundation of proven technologies, and the Ares V will give NASA unprecedented performance and payload volume that can enable a range of future missions. The CDs contain videos of scenes from various activities surrounding the design, construction and testing of the vehicles.
    Keywords: Launch Vehicles and Launch Operations
    Type: Human Space Flight Review; Jul 29, 2009; Huntsville, AL; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Cryogenic mechanisms for scanning and interchange of the Fabry-Perot interferometers in the ISO long wavelength spectrometer (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The Infrared Space Observatory (ISO) is an ESA cornerstone mission for infrared astronomy. Schedules for launch in 1993, its four scientific instruments will provide unprecedented sensitivity and spectral resolution at wavelengths which are inaccessible using ground-based techniques. One of these, the Long Wavelength Spectrometer (LWS), will operate in the 45 to 180 micron region (Emery et. al., 1985) and features two Fabry-Perot interferometers mounted on an interchange mechanism. The entire payload module of the spacecraft, comprising the 60 cm telescope and the four focal plane instruments, is maintained at 2 to 4 K by an onboard supply of liquid helium. The mechanical design and testing of the cryogenic interferometer and interchange mechanisms are described.
    Keywords: MECHANICAL ENGINEERING
    Type: JPL, The 25th Aerospace Mechanisms Symposium; p 151-159
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Robotic control and inspection verification (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Three areas of possible commercialization involving robots at the Kennedy Space Center (KSC) are discussed: a six degree-of-freedom target tracking system for remote umbilical operations; an intelligent torque sensing end effector for operating hand valves in hazardous locations; and an automatic radiator inspection device, a 13 by 65 foot robotic mechanism involving completely redundant motors, drives, and controls. Aspects concerning the first two innovations can be integrated to enable robots or teleoperators to perform tasks involving orientation and panal actuation operations that can be done with existing technology rather than waiting for telerobots to incorporate artificial intelligence (AI) to perform 'smart' autonomous operations. The third robot involves the application of complete control hardware redundancy to enable performance of work over and near expensive Space Shuttle hardware. The consumer marketplace may wish to explore commercialization of similiar component redundancy techniques for applications when a robot would not normally be used because of reliability concerns.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA, Washington, Technology 2000, Volume 2; p 298-307
    Format: application/pdf
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  • 4
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    Large-gap magnetic positioning system having advantageous configuration (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: A magnetic configuration was devised in which the positioned object is maintained in a stable orientation and position on one side of an opaque plane surface entirely by means of magnetic components on the other side of the plane. The system is effective with or without gravity, and can operate in any orientation. In this system, the positioned object need only contain a simple dipole magnet. The positioning components consist of a group of permanent magnets creating a magnetic field configuration which stabilizes the levitated dipole in all but one degree of freedom, and a magnetic position sensing and force feedback system to actively stabilize the object in the one unstable direction. The system utilizes very low power at equilibrium and can maintain gaps of 50 mm.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Langley Research Center, International Symposium on Magnetic Suspension Technology, Part 2; p 941-953
    Format: text
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  • 5
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    Coarse-fine residual gravity cancellation system with magnetic levitation (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: Aircraft flight along parabolic trajectories have been proposed and executed in order to achieve low cost, near free fall conditions of moderate duration. This paper describes a six degree of freedom experiment isolation system designed to cancel out residual accelerations due to mechanical vibrations and errors in aircraft trajectory. The isolation system consists of a fine motion magnetic levitator whose stator is transported by a conventional coarse motion stage. The levitator uses wide gap voice coil actuators and has the dual purpose of isolating the experiment platform from aircraft vibrations and actively cancelling residual accelerations through feedback control. The course motion stage tracks the levitated platform in order to keep the levitator's coils centered within their matching magnetic gaps. Aspects of system design, an analysis of the proposed control strategy and simulation results are presented. Feasibility experiments are also discussed.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Langley Research Center, International Symposium on Magnetic Suspension Technology, Part 1; p 473-492
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  • 6
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    Eccentricity effects upon the flow field inside a whirling annular seal (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The flow field inside a whirling annular seal operating at a Reynolds number of 24,000 and a Taylor number of 6600 has been measured using a 3-D laser Doppler anemometer system. Two eccentricity ratios were considered, 0.10 and 0.50. The seal has a diameter of 164 mm, is 37.3 mm long, and has a clearance of 1.27 mm. The rotor was mounted eccentrically on the shaft such that the whirl ratio is 1.0 and the rotor follows a circular orbit. The mean axial velocity is not uniform around the circumference of the seal; near the inlet a region characterized by high velocity of the seal. By the exit, another region of high axial velocity is not uniform around the circumference of the seal; near the inlet a region characterized by high velocity of the seal. By the exit, another region of high axial velocity has developed, this time on the suction side of the seal. The magnitude and azimuthal distance of the migration increased with increasing whirl amplitude (eccentricity). Throughout the seal length, the azimuthal mean velocity varied inversely with the mean axial velocity. Increasing the whirl amplitude did not increase the magnitude of the azimuthal velocity at the seal exit.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Lewis Research Center, Rotordynamic Instability Problems in High-Performance Turbomachinery, 1993; p 101-112
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Extraterrestrial surface propulsion systems (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Lunar traction systems, Mars oxygen production, and Mars methane engine operation were the three topics studied during 1992. An elastic loop track system for lunar construction operations was redesigned and is being tested. A great deal of work on simulating the lunar environment to facilitate traction testing has been reported. Operation of an oxygen processor under vacuum conditions has been the focus of another design team. They have redesigned the processor facility. This included improved seals and heat shields. Assuming methane and oxygen can be produced from surface resources on Mars, a third design team has addressed the problem of using Mars atmospheric carbon dioxide to control combustion temperatures in an internal combustion engine. That team has identified appropriate tests and instrumentation. They have reported on the test rig that they designed and the computer-based system for acquiring data.
    Keywords: MECHANICAL ENGINEERING
    Type: USRA, Proceedings of the 8th Annual Summer Conference: NASA(USRA Advanced Design Program; p 209-215
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    NASA TECHNICAL REPORTS
  • 8
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    Linear mass actuator (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A linear mass actuator includes an upper housing and a lower housing connectable to each other and having a central passageway passing axially through a mass that is linearly movable in the central passageway. Rollers mounted in the upper and lower housings in frictional engagement with the mass translate the mass linearly in the central passageway and drive motors operatively coupled to the roller means, for rotating the rollers and driving the mass axially in the central passageway.
    Keywords: MECHANICAL ENGINEERING
    Format: application/pdf
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  • 9
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    Jet Propulsion Laboratory/Kennedy Space Center telerobotic inspection and manipulation demonstration (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-01-25
    Description: The goal of this effort is to demonstrate telerobotic inspection and mainpulation of space shuttle payloads in the presence of substantial communications time delays between the operator station and the robotic work space. The processing of space shuttle payloads provides a variety of tasks which are typical of both space shuttle ground operations and Space Station in-flight operations, and communications time delays are inevitable in space operations where the operator station will be light-seconds away from the telerobot. With this demonstration we hope to show the efficacy and safety of robotic technology for ground and space operations. Our approach is to develop an experimental telerobotic system with the remote sensing, actuation and reflex portions located at KSC in Florida, while the operator control station will be located at Jet Propulsion Laboratory (JPL) in California. The JPL portion of the system includes a high-level operator interface, intelligent spatial planning and machine vision, while the KSC portion includes the robot arm, end effectors, cameras and proximity sensors, and the necessary control and communications computers and software. The communications between JPL and KSC are over a limited-bandwidth network channel (19200 baud) with unpredictable and unrepeatable time delays. In FY89 we integrated a basic version of the robotic, communications, and computer hardware, and we developed the software to perform an operator-supervised inspection of a PAM-D satellite upper stage rocket motor and its shuttle support cradle. The demonstration, though severely limited by the bulk of the available computer arm, showed the potential of telerobotics for inspection tasks. In the future, we plan to develop additional capabilities which will allow manipulation tasks to be performed, including removal of dust covers and lens caps, insertion of connectors and batteries, and installation of payload objects.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Johnson Space Center, Space Station Evolution Conference: Abstracts for Technical Sessions; p 54
    Format: text
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  • 10
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    Wear reduction in ceramic bearings by surface generated pyrolytic carbon continuously replenished by ethylene gas (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Sliding tests with a pin-on-disc tribometer and both sliding and rolling tests with a modified four-ball tester at bulk temperatures of about 500 C and contact pressures of about 2.2 GPa have demonstrated up to 80% reductions of friction and wear with silicon nitride surfaces when a stream of ethylene is directed into the conjunction region. The effects are even more pronounced when the ethylene is prenucleated by a flow over a coil of nichrome wire electrically heated to about 800 C and located about 30 cm upstream of the exit nozzle. Steel and Ni-plated steel are lubricated by this method even more efficiently at lower temperatures.
    Keywords: MECHANICAL ENGINEERING
    Type: AD-A278264 , NASA-CR-189214 , NAS 1.26:189214 , EDR-16732 , AVSCOM-TR-92-C-032
    Format: application/pdf
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