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Miniature Bearings Play a Major Role in Mars 2020 Mission

  • Magazine Article
  • TBMG-34392
Published 2019-05-01 by Tech Briefs Media Group in United States

Timken North Canton, OH

 

NASA Marshall Space Flight Center

  • Magazine Article
  • TBMG-34394
Published 2019-05-01 by Tech Briefs Media Group in United States

Founded on July 1, 1960, Marshall Space Flight Center in Huntsville, AL is one of NASA’s largest field centers. Marshall engineers designed, built, tested, and helped launch the Saturn V rocket that carried Apollo astronauts to the Moon. Marshall developed new rocket engines and tanks for the fleet of space shuttles, built sections of the International Space Station (ISS), and now manages all the science work of the astronauts aboard the ISS from a 24/7 Payload Operations Integration Center. Marshall also manages NASA’s Michoud Assembly Facility in New Orleans — the agency’s premier site for the manufacture and assembly of large-scale space structures and systems.

 

INSULATION SLEEVING, ELECTRICAL, HEAT SHRINKABLE, POLYVINYL CHLORIDE, SEMI RIGID, CROSSLINKED AND NON-CROSSLINKED

AE-8D Wire and Cable Committee
  • Aerospace Standard
  • AS23053/3
  • Current
Published 2019-04-08 by SAE International in United States
No Abstract Available.
Datasets icon
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INSULATION SLEEVING, ELECTRICAL, HEAT SHRINKABLE, POLYVINYL CHLORIDE, SEMI RIGID, CROSSLINKED AND NON-CROSSLINKED

AE-8D Wire and Cable Committee
  • Aerospace Standard
  • AS23053/2
  • Current
Published 2019-04-08 by SAE International in United States
No Abstract Available.
Datasets icon
Annotation icon
 

Lockheed Martin Explores a Different Kind of Space for NASA

  • Magazine Article
  • TBMG-34163
Published 2019-04-01 by Tech Briefs Media Group in United States

Protolabs Maple Plain, MN

 

Pre-Treatment Solution for Water Recovery

  • Magazine Article
  • TBMG-34169
Published 2019-04-01 by Tech Briefs Media Group in United States

The Pre-Treatment Solution for Water Recovery technology was developed by NASA Johnson Space Center innovators to increase the amount of potable water recovered from the International Space Station’s urine processor assembly system. The solution increased the water recovery rate in the ISS distiller from 75 to 90 percent, doubled the volume of feed processed per cycle, reduced the volume of brine by half, and eliminated the formation of precipitate up to 90% water recovery.

 

Sublimable Propellant Source for Iodine-Fed Ion Propulsion System

  • Magazine Article
  • TBMG-33932
Published 2019-03-01 by Tech Briefs Media Group in United States

NASA Marshall has developed a system for generating iodine vapor from solid iodine for use as a propellant in a Hall or ion thruster propulsion system. Xenon has generally been the preferred propellant for these spacecraft ion propulsion systems but more recently, iodine-based systems have gained significant attention due to comparable performance to xenon, and the system-level advantages of low storage pressure and higher storage density with more propellant per unit volume.

 

Flexible, Spinning Heat Shield for Spacecraft

  • Magazine Article
  • TBMG-33912
Published 2019-03-01 by Tech Briefs Media Group in United States

Heat shields are essentially used as the brakes to stop spacecraft from burning up and crashing on entry and reentry into a planet's atmosphere. Current spacecraft heat shield methods include huge inflatables and mechanically deployed structures that are often heavy and complicated to use.

 

Effects of Reynolds and Mach Numbers in Large Eddy Simulation of Supersonic Round Jets

  • Magazine Article
  • TBMG-33937
Published 2019-03-01 by Tech Briefs Media Group in United States

Rockets/landers arrive on the Moon with supersonic speed and impact lunar regolith. There is no reliable software to computationally simulate in an effective way the supersonic plumes escaping from these rockets/devices. A Large Eddy Simulation (LES) model and hybrid WENO (weighted essentially non-oscillatory) scheme numerical method were developed to address this problem.

 

Real-Time, Fuel-Optimal, Powered Descent Guidance Using Interpolated Time-of-Flight and Propellant Mass

  • Magazine Article
  • TBMG-33926
Published 2019-03-01 by Tech Briefs Media Group in United States

Soft landing using rockets requires a trajectory to be planned for the lander from rocket ignition — typically several kilometers in altitude and moving at up to 200 m/s — to the point near the surface with near-zero velocity. The exact initial and possibly final points are not known beforehand, so the trajectory must be found onboard a landing spacecraft in near real time. An algorithm to find such a trajectory is called powered descent guidance (PDG). The previous state-of-the-art had been the computationally fast but suboptimal Polynomial PDG of Apollo heritage. In the last decade, a previous technology advance that transforms the PDG problem into a convex optimization problem that can be solved efficiently formed the basis of the Guidance for Fuel Optimal Large Diverts (G-FOLD) PDG algorithm. While G-FOLD finds the constrained optimal PDG trajectory, it still requires a search to find the optimal time-of-flight, which in turn can typically require 10 trajectory optimizations. While a PDG trajectory for a single time-of-flight can be found in near real time, having to evaluate 10 trajectories while running in the background on a 200-MHz flight processor would take too long.