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A Guide for the Selection of Quick-Disconnect Couplings for Aerospace Fluid Systems

G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
  • Aerospace Standard
  • AIR1047E
  • Current
Published 2020-03-10 by SAE International in United States
The factors involved in the selection of a quick-disconnect are grouped into the following classifications for the purpose of discussion: a Functional considerations. b Weight considerations. c Environmental performance factors. d End fitting types. e Additional considerations. A quick-disconnect coupling as used in this AIR is one that can be rapidly and repetitively connected and disconnected without excessive fluid loss. The relative importance of the design factors depends upon the fluid medium of the particular system in which quick-disconnect is to be used. The effect of the fluid media on each factor is discussed in this report where applicable.
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Celebrating Women in Engineering & Science: Jasmin Moghbeli, NASA Astronaut

  • Magazine Article
  • TBMG-36166
Published 2020-03-01 by Tech Briefs Media Group in United States

Jasmin Moghbeli’s astronaut class graduated in January 2020 — the first class to graduate since the agency announced the Artemis program. She holds a BS degree in aerospace engineering with information technology from the Massachusetts Institute of Technology and a MS in engineering science in aerospace engineering from the Naval Postgraduate School. Moghbeli was commissioned as a Second Lieutenant in the United States Marine Corps in 2005 upon completion of her undergraduate degree. An AH-1W Super Cobra helicopter pilot and Marine Corps test pilot, Moghbeli served in Operation Enduring Freedom in Afghanistan from 2009 to 2010. At the time of her selection as an astronaut candidate, Moghbeli was testing H-1 helicopters. She has accumulated more than 150 combat missions and 2,000 hours of flight time in more than 25 different aircraft. She is eligible for assignment to missions destined for the International Space Station, the Moon, and ultimately, Mars.

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Electrically Non-Conductive Ladder Fall Protection

  • Magazine Article
  • TBMG-36194
Published 2020-03-01 by Tech Briefs Media Group in United States

NASA’s Kennedy Space Center developed an electrically non-conductive ladder fall protection system for the Launch Complex (LC) 39B lightning towers. The towers include a 100-foot fiberglass mast at the top of the tower structure. The fiberglass masts insulate the metallic tower structure from the lightning strike protection system that is housed at the top of the fiberglass masts.

Facility Focus: NASA Goddard Space Flight Center

  • Magazine Article
  • TBMG-35969
Published 2020-02-01 by Tech Briefs Media Group in United States

Dr. Robert Hutchings Goddard is considered the father of modern rocket propulsion. A physicist, Goddard also had a unique genius for invention. It is in his honor that NASA's Goddard Space Flight Center in Greenbelt, MD, was established on May 1, 1959 as NASA's first space flight complex.

Modified Fittings Enhance Industrial Safety

  • Magazine Article
  • TBMG-36000
Published 2020-02-01 by Tech Briefs Media Group in United States

NASA's Kennedy Space Center in Florida is home to one of the largest buildings in the world — the massive Vehicle Assembly Building — and also hosts a number of one-of-a-kind facilities. The more than 30-mile-long campus has witnessed every launch from the Space Shuttle Launch Pad as well as many homecomings at the Shuttle Landing Facility. Just as important, the Space Station Processing Facility (SSPF) has seen each element of the International Space Station (ISS) that passes through Kennedy before it goes into orbit.

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Terminal Junction System (TJS), Environment Resistant General Specification For

AE-8C2 Terminating Devices and Tooling Committee
  • Aerospace Standard
  • AS81714C
  • Current
Published 2020-01-31 by SAE International in United States
AS81714 covers Terminal Junction System (TJS) components which are used for interconnection of wiring and incorporation of passive components (see 6.1). These environment resistant components have in common the use of crimp type external pin contacts in accordance with AS39029/1 for Series I or crimp type external socket contacts in accordance with AS39029/22 for Series II. This family of TJS components is designed to operate continuously over a temperature range of -65 to 200 °C, using any combination of temperatures generated by the electrical load and ambient temperature so that the maximum internal hot spot, combined temperature, will not exceed the maximum specified for the class of TJS component, unless otherwise specified (1.2, 3.1). The maximum continuous temperature established by the electronic components in a component module (block) shall be limited to the block maximum continuous temperature. The components making up the system and covered by AS81714 include: a Terminal junction bussing blocks (6.12.2) 1 Feedback type (6.12.2.1) 2 Feedthrough type (6.12.2.2) b Racks (mounting holders) for blocks (6.12.3) c Brackets, block mounting (6.12.4) d…
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Mathematical Model of Heat-Controlled Accumulator (HCA) for Microgravity Conditions

National Aerospace University Kharkiv Aviation Institute, Ukraine-Gorbenko Gennadiy Olexandrovich, Koval Polina Sergeevna, Yepifanov Konstantin Sergeevich, Gakal Pavlo Grigorovich, Turna Rustem Yusufovich
  • Journal Article
  • 01-13-01-0001
Published 2020-01-20 by SAE International in United States
It is reasonable to use a two-phase heat transfer loop (TPL) in a thermal control system (TCS) of spacecraft with large heat dissipation. One of the key elements of TPL is a heat-controlled accumulator (HCA). The HCA represents a volume which is filled with vapor and liquid of a single working fluid without bellows. The pressure in a HCA is controlled by the heater. The heat and mass transfer processes in the HCA can proceed with a significant nonequilibrium. This has implications on the regulation of TPL. This article presents a mathematical model of nonequilibrium heat and mass transfer processes in an HCA for microgravity conditions. The model uses the equations of mass and energy conservation separately for the vapor and liquid phases. Interfacial heat and mass transfer is also taken into account. It proposes to use the convective component k for the level of nonequilibrium evaluation. The experiments were carried out in microgravity conditions for the estimation of the k value. The heating of the HCA was investigated in the flight experiments. The working…
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CubeSat Form Factor Thermal Control Louvers

  • Magazine Article
  • TBMG-35826
Published 2020-01-01 by Tech Briefs Media Group in United States

Thermal control of small spacecraft, including CubeSats, is a challenge for the next era of NASA spaceflight. Science objectives and components will still require strict thermal control while smaller volumes will inherently absorb and shed heat more quickly than a larger body. Thus, game-changing technologies must be developed to stabilize the thermal environment inside of small spacecraft.

NASA's Thirst for Water on Mars Quenched by Student Innovators

  • Magazine Article
  • TBMG-35794
Published 2020-01-01 by Tech Briefs Media Group in United States

Protolabs Maple Plain, MN

In-Situ Resource Utilization (ISRU): Methylotrophic Microorganisms Expressing Soluble Methane Monooxygenase Proteins

  • Magazine Article
  • TBMG-35812
Published 2020-01-01 by Tech Briefs Media Group in United States

Long-duration missions to planetary bodies and deep space will require new technological developments that support human habitation in transit and on distant bodies. Microorganisms are unique from the standpoint that they can be employed as self-replicating bio-factories to produce both native and engineered mission-relevant bio-products. Methane (CH4) usage in In-Space Manufacturing (ISM) platforms has been discussed previously for human exploration and has been proposed to be used in physicochemical systems as a propulsion fuel, supply gas, and in fuel cells.