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Lewis, James

Publications and source records attributed to Lewis, James.

7 records
All sourcesNASA NTRSDOE OSTI
DOE OSTI2019

The Relation between Galaxy ISM and Circumgalactic O vi Gas Kinematics Derived from Observations and ΛCDM Simulations

We introduce the first galaxy–O vi absorption kinematic study for 20 absorption systems (EW > 0.1 Å) associated with isolated galaxies (0.15 ≤ z ≤ 0.55) that have accurate redshifts and rotation curves obtained using Keck/ESI. Our sample is split into two azimuthal angle bins: major axis (Φ < 25°) and minor axis (Φ > 33°). O vi absorption along the galaxy major axis is not correlated with galaxy rotation kinematics, with only 1/10 of systems that could be explained with rotation/accretion models. This is in contrast to corotation commonly observed for Mg ii absorption. O vi along the minor axis could be modeled by accelerating outflows, but only for small opening angles, while the majority of the O vi is decelerating. Along both axes, stacked O vi profiles reside at the galaxy systemic velocity with the absorption kinematics spanning the entire dynamical range of their galaxies. The O vi found in AMR cosmological simulations exists within filaments and in halos of ~50 kpc surrounding galaxies. Simulations show that major-axis O vi gas inflows along filaments and decelerates as it approaches the galaxy, while increasing in its level of corotation. Minor-axis outflows in the simulations are effective within 50–75 kpc; beyond that they decelerate and fall back onto the galaxy. While the simulations show clear O vi kinematic signatures, they are not directly comparable to observations. When we compare kinematic signatures integrated through the entire simulated galaxy halo, we find that these signatures are washed out owing to full velocity distribution of O vi throughout the halo. We illustrate that O vi alone does not serve as a useful kinematic indicator of gas accretion, outflows, or star formation and likely best probes the halo virial temperature.

79 ASTRONOMY AND ASTROPHYSICS↗
NASA NTRS2016

L-8: Docking Systems and Other Attachment/Release Mechanisms and Related Technologies

We are sharpening our focus on Human Space Flight (HSF) Exploration Beyond Low Earth Orbit. We want to ensure that HSF technologies are ready to take Humans to Mars in the 2030s. Various Roadmaps define the needed technologies. We are attempting to define our activities and dependencies. Our Goal: Get within 8 years of launching humans to Mars (L-8) by 2025. Develop and Mature the technologies and systems needed. Develop and Mature the personnel needed. We need collaborators to make it happen, and we think they can benefit by working with us.

Lewis, James↗
NASA NTRS2011

NASA Docking System (NDS) Interface Definitions Document (IDD)

The NASA Docking System (NDS) mating system supports low approach velocity docking and provides a modular and reconfigurable standard interface, supporting crewed and autonomous vehicles during mating and assembly operations. The NDS is NASA s implementation for the International Docking System Standard (IDSS) using low impact docking technology. All NDS configurations can mate with the configuration specified in the IDSS Interface Definition Document (IDD), Revision A, released May 13, 2011. The NDS evolved from the Low Impact Docking System (LIDS). The term (and its associated acronym), international Low Impact Docking System (iLIDS) is also used to describe this system. NDS and iLIDS may be used interchangeability. Some of the heritage documentation and implementations (e.g., software command names) used on the NDS will continue to use the LIDS acronym.

Lewis, James↗
NASA NTRS2006

Advanced Docking Berthing System Update

In FY05 the Exploration Systems Technology Maturation Program selected the JSC advanced mating systems development to continue as an in-house project. In FY06, as a result of ESAS Study (60 Day Study) the CEV Project (within the Constellation Program) has chosen to continue the project as a GFE Flight Hardware development effort. New requirement for CEV to travel and dock with the ISS in 2011/12 in support of retiring the Shuttle and reducing the gap of time where US does not have any US based crew launch capability. As before, long-duration compatible seal-on-seal technology (seal-on-seal to support androgynous interface) has been identified as a risk mitigation item.

Lewis, James↗
NASA NTRS1996

NASA space shuttle lightweight seat

The Space Shuttle Lightweight Seat-Mission Specialist (LWS-MS) is a crew seat for the mission specialists who fly aboard the Space Shuttle. The LWS-MS is a lightweight replacement for the mission specialist seats currently flown on the Shuttle. Using state-of-the-art analysis techniques, a team of NASA and Lockheed engineers from the Johnson Space Center (JSC) designed a seat that met the most stringent requirements demanded of the new seats by the Shuttle program, and reduced the weight of the seats by 52%.

Hansen, Chris↗